AMETANK REPORT Page: 1/53 TABLE OF CONTENTS SUMMARY OF DESIGN DATA AND REMARKS ROOF DESIGN ROOF SUMMARY OF RESULTS SHELL COURSE DESIGN SHELL SUMMARY OF RESULTS BOTTOM DESIGN BOTTOM SUMMARY OF RESULTS WIND MOMENT SEISMIC SITE GROUND MOTION SEISMIC CALCULATIONS ANCHOR BOLT DESIGN ANCHOR BOLT SUMMARY OF RESULTS CAPACITIES AND WEIGHTS MAWP & MAWV SUMMARY Page: 2/53 No Warnings!! SUMMARY OF DESIGN DATA AND REMARKS Back Job : Fame Analysis Tank 500 MT Date of Calcs. : 27-Aug-2020 Mfg. or Insp. Date : Designer : WRK Project : Proyek Pembangunan Pabrik Biodiesel Plant Kapasitas 1500TPD termasuk Pre-treatment Tag Number : 220-TK-115 Plant Location : Kalimantan Selatan Site : Batulicin Design Basis : API-650 12th Edition, March 2013 1 Design Internal Pressure = 7.5 KPa or 764.8575 mmh2o Design External Pressure = -0 KPa or -0 mmh2o MAWP = 8.1534 KPa or 831.4938 mmh2o MAWV = -1.015 KPa or -103.5101 mmh2o D of Tank = 7.7 m OD of Tank = 7.716 m ID of Tank = 7.7 m CL of Tank = 7.708 m Shell Height = 14.7 m S.G of Contents = 1 Max Liq. Level = 13.9 m Min Liq. Level = 0.6 m Design Temperature = 90 ºC Tank Joint Efficiency = 0.85 Ground Snow Load = 0 KPa Roof Live Load = 1 KPa Additional Roof Dead Load = 0 KPa Basic Wind Velocity = 120 kph Wind Importance Factor = 1 Using Seismic Method: API-650 - ASCE7 Mapped(Ss & S1) Seismic Use Group = II Site Class = E T_L (sec) = 4 Ss (g) = 0.12 S1 (g) = 0.05 Av (g) = 0.1 Q = 0.67 Importance Factor = 1 DESIGNER REMARKS Remarks or Comments Page: 3/53 SUMMARY OF SHELL RESULTS Shell Width CA Material # (mm) (mm) JE Min t-min Tensile t-min t-min Yield Sd St Weight Weight t-Des t-Test ExtStrength Erection Seismic Strength (MPa) (MPa) (N) CA (N) (mm) (mm) Pe (MPa) (mm) (mm) (MPa) (mm) 1 1800 A283MC 1.7 0.85 205 380 137 154 26,759 21,078 6 5.6562 3.3322 4.384 2 1800 A283MC 1.7 0.85 205 380 137 154 26,759 21,078 5 5.1605 2.8912 3 1800 A283MC 1.7 0.85 205 380 137 154 20,075 14,390 4 1800 A283MC 1.7 0.85 205 380 137 5 1500 A283MC 1.7 0.85 205 380 6 1500 A283MC 1.7 0.85 205 7 1500 A283MC 1.7 0.85 8 1500 A283MC 9 1500 A283MC 6 8 OK 4.0317 NA 5.1605 8 OK 5 4.6648 2.4502 3.5017 NA 5 6 OK 154 20,075 14,390 5 4.1691 2.0092 3.1821 NA 5 6 OK 137 154 16,729 11,991 5 3.6733 1.5682 2.8632 NA 5 6 OK 380 137 154 16,729 11,991 5 3.2602 1.2007 2.5977 NA 5 6 OK 205 380 137 154 16,729 11,991 5 2.8471 0.8332 2.3284 NA 5 6 OK 1.7 0.85 205 380 137 154 16,729 11,991 5 2.434 0.4657 2.0551 NA 5 6 OK 1.7 0.85 205 380 137 154 16,729 11,991 5 2.0209 0.0982 1.7851 NA 5 6 OK Total Weight of Shell = 177,316.3901 N CONE ROOF Plates Material = A283M-C Structural Material = A36M t.required = 6 mm t.actual = 6 mm Roof corrosion allowance = 1 mm Roof Joint Efficiency = 0.85 Plates Overlap Weight = 443.4819 N Plates Weight = 22,201.2901 N RAFTERS: Qty At Radius (m) Size Length (m) W (N/m) Ind. Weight (N) Total Weight (N) 12 3.85 IPE120 3.5243 101.9891 359.4483 4,313.3802 Rafters Total Weight = 4,313.3802 N Bottom Type : Cone-Up Bottom Floor Bottom Material = A283M-C t.required = 7.7 mm t.actual = 8 mm Bottom corrosion allowance = 1.7 mm Bottom Joint Efficiency = 0.85 Total Weight of Bottom = 29,517.6312 N ANCHOR BOLT : (10) M33 mm UNC Bolts, A36M Page: 4/53 NA tt-min Actual Status (mm) (mm) TOP END STIFFENER : Detail B Size = l200x200x15 1 Material = A36M Weight = 11,102.9272 N INTERMEDIATE STIFFENERS QTY (: 2) Stiffener Size Elevation (m) Z-Req'd (cm3) Z-Actual (cm3) Weight (N) 1 l76x76x12.7 8 6.3673 48.5332 3,349.1878 2 l76x76x12.7 11 4.6605 48.5332 3,349.1878 TANK NAMEPLATE INFORMATION Pressure Combination Factor 0.4 Design Standard API-650 12th Edition, March 2013 Appendices Used E, F Roof A283M-C : 6 mm Shell (1) A283M-C : 8 mm Shell (2) A283M-C : 8 mm Shell (3) A283M-C : 6 mm Shell (4) A283M-C : 6 mm Shell (5) A283M-C : 6 mm Shell (6) A283M-C : 6 mm Shell (7) A283M-C : 6 mm Shell (8) A283M-C : 6 mm Shell (9) A283M-C : 6 mm Bottom A283M-C : 8 mm Page: 5/53 STRUCTURALLY SUPPORTED CONICAL ROOF Back A = Actual Part. Area of Roof-to-shell Juncture per API-650 (cm^2) A-min = Minimum participating area (cm^2) per API-650 5.10.5.2 a-min-A = Minimum participating area due to full design pressure per API-650 F.5.1 (cm^2) a-min-Roof = Minimum participating area per API-650 App. F.5.2 (cm^2) Add-DL = Added Dead load (kPa) Alpha = 1/2 the included apex angle of cone (degrees) Aroof = Contributing Area due to roof plates (cm^2) Ashell = Contributing Area due to shell plates (cm^2) CA = Roof corrosion allowance (mm) D = Tank Nominal Diameter per API-650 5.6.1.1 Note 1 (m) density = Density of roof (kg/mm3) DL = Dead load (kPa) e.1b = Gravity Roof Load (1) - Balanced (kPa) e.1u = Gravity Roof Load (1) - Unbalanced (kPa) e.2b = Gravity Roof Load (2) - Balanced (kPa) e.2u = Gravity Roof Load (2) - Unbalanced (kPa) Fp = Pressure Combination Factor Fy = smallest of the yield strength (MPa) Fy-roof = Minimum yield strength for shell material (Table 5-2a) (MPa) Fy-shell = Minimum yield strength for shell material (Table 5-2a) (MPa) Fy-stiff = Minimum yield strength for stiffener material (Table 5-2a) (MPa) hr = Roof height (m) ID = Tank Inner Diameter (m) Insulation = Roof Insulation (m) JEr = Roof joint efficiency Lr = Entered Roof Live Load (kPa) Lr-1 = Computed Roof Live Load, including External Pressure Max-p = Max Roof Load due to participating Area (kPa) Net-Uplift = Uplift due to internal pressure minus nominal weight of shell, roof and attached framing (N), per API-650 F.1.2 P = Minimum participating area (kPa) P-ext-2 = Max external pressure due to roof shell joint area (kPa) P-F41 = Max design pressure limited by the roof-to-shell joint (kPa) P-F42 = Max design pressure due to Uplift per API-650 F.4.2 (kPa) P-F51 = Max design pressure reversing a-min-A calculation (kPa) P-max-ext-T = Total max external pressure due to roof actual thickness and roof participating area (kPa) P-max-internal = Maximum design pressure and test procedure per API-650 F.4, F.5. (kPa) P-Std = Max pressure pressure allowed per API-650 App. F.1 & F.7 (kPa) P-Uplift = Uplift case per API-650 1.1.1 (N) P-weight = Dead load of roof plate (kPa) Pe = External Pressure (kPa) pt = Roof cone pitch (mm) rise per 12 (mm) Pv = Internal Pressure (kPa) R = Roof horizontal radius (m) Ra = Roof surface area (cm^2) Roof-wc = Weight corroded of roof plates (N) S = Ground Snow Load per ASCE 7-05 Fig 7-1 (kPa) Sb = Balanced Design Snow Load per API-650 Section 5.2.1.h.1 (kPa) Shell-wc = Weight corroded of shell (N) Su = Unbalanced Design Snow Load per API-650 Section 5.2.1.h.2 (kPa) T = Balanced Roof Design Load per API-650 Appendix R (kPa) t-calc = Minimum nominal roof plates thickness per API-650 Section 5.10.5.1 (mm) t-Ins = thickness of Roof Insulation (m) Theta = Angle of cone to the horizontal (degrees) U = Unbalanced Roof Design Load per API-650 Appendix R (kPa) Wc = Maximum width of participating shell per API-650 Fig. F-2 (mm) Wh = Maximum width of participating roof per API-650 Fig. F-2 (mm) Page: 6/53 Roof Design Per API-650 Note: Tank Pressure Combination Factor Fp = 0.4 D = 7.7 m ID = 7.7 m CA = 1 mm R = 3.9098 m Fp = 0.4 JEr = 0.85 JEs = 0.85 JEst = 0.85 Insulation = 0 m Add-DL = 0 kPa Lr = 1 kPa S = 0 kPa Sb = 0 kPa Su = 0 kPa density = 0.000007841 kg/mm3 P-weight = 0.4768 KPa Pe = 0 kPa pt = 0.75 mm rise per 12 mm t-actual = 6 mm Fy-roof = 205 MPa Fy-shell = 205 MPa Fy-stiff = 250 MPa Shell-wc = 130,896.6472 N Roof-wc = 18,501.0751 N P-Std = 18 kPa, Per API-650 F.1.3 t-1 = 6 mm CA-1 = 1.7 mm Sd = 137 MPa Theta = TAN^-1 (pt/12) Theta = TAN^-1 (0.75/12) Theta = 3.5763 degrees Alpha = 90 - Theta Alpha = 90 - 3.5763 Alpha = 86.4237 degrees Ap-Vert = D^2 * TAN(Theta)/4 Ap-Vert = 7.7^2 * TAN(3.5763)/4 Ap-Vert = 0.9264 m^2 Horizontal Projected Area of Roof per API-650 5.2.1.f Xw = D * 0.5 Xw = 7.7 * 0.5 Xw = 3.85 m Ap = PI * (D/2)^2 Ap = PI * (7.7/2)^2 Ap = 46.5662 m^2 DL = Insulation + P-weight + Add-DL DL = 0 + 0.4768 + 0 Page: 7/53 DL = 0.4768 kPa Roof Loads per API-650 5.2.2 e.1b = DL + MAX(Sb , Lr) + (0.4 * Pe) e.1b = 0.4768 + MAX(0 , 1) + (0.4 * 0) e.1b = 1.4768 kPa e.2b = DL + Pe + (0.4 * MAX(Sb , Lr)) e.2b = 0.4768 + 0 + (0.4 * MAX(0 , 1)) e.2b = 0.8768 kPa T = MAX(e.1b , e.2b) T = MAX(1.4768 , 0.8768) T = 1.4768 kPa e.1u = DL + MAX(Su , Lr) + (0.4 * Pe) e.1u = 0.4768 + MAX(0 , 1) + (0.4 * 0) e.1u = 1.4768 kPa e.2u = DL + Pe + (0.4 * MAX(Su , Lr)) e.2u = 0.4768 + 0 + (0.4 * MAX(0 , 1)) e.2u = 0.8768 kPa U = MAX(e.1u , e.2u) U = MAX(1.4768 , 0.8768) U = 1.4768 kPa Lr-1 = MAX(T , U) Lr-1 = MAX(1.4768 , 1.4768) Lr-1 = 1.4768 kPa Ra = PI * R * SQRT(R^2 + hr^2) Ra = PI * 3.9098 * SQRT(3.9098^2 + 0.2444^2) Ra = 481,165.4422 cm^2 or 48.1165 m^2 Roof Plates Weight = density * Ra * t-actual Roof Plates Weight = 0.000007841 * 481,165.4422 * 6 Roof plates Weight = 22,201.2901 N STRUCTURE CALCULATIONS Area = Area per rafter = (m^2) CRR = Center Ring Outside Radius = (mm) D = Tank Nominal Size = (m) G = Total Rafter Weight = (N) h = rise = (m) ID = Inside Diameter = (m) l = Horizontal Rafter Length = (m) l1 = Actual Rafter Length = (m) n = Number of Rafters OD = Outside Diameter = (m) Pt = Pitch of Roof q = Roof Design Load = (kPa) QQ = Total Load per Rafter = (N) R = Inside Radius = (m) rft-S = Rafter Section Modulus = (cm^3) Page: 8/53 rft-r = Rafter Radius of Gyration = (mm) rft-wgt = Rafter Weight = (kg/m) rft-A = Rafter Area = (mm^2) RL = Roof Load = (kPa) Sd = Allowable Stress = (pa) T = Balanced Roof Load = (kPa) Theta = Angle of Cone to the Horizontal = (degrees) t-1 = Top Shell Thickness = (mm) U = Unbalanced Roof Load = (kPa) D = 7.7 m OD = 7.716 m ID = 7.7 m IR = 3.85 m t-1 = 6 mm T = 1.4767 kPa U = 1.4767 kPa Pt = 0.75 n = 12 Rafter Type = IPE120 rft-S = 52.96 cm^3 rft-r = 14.5 mm rft-wgt = 10.4 kg/m rft-A = 1,320 mm^2 Sd = 160 MPa CRR = 664.9707 mm Compression Ring Material = A36 Compression-Ring-Sd = 160 MPa Area-Crown = Area Crown Ring = m^2 Z-Crown = Section Modulus Crown Ring = m^3 phi = 1/2 of angle between rafters = (degrees) S-actual-between-rafters = Total Compressive Stress = Pa Calculated Variables Fa = Sd = 160,000,000 Pa Fbx = Sd = 160,000,000 Pa Theta = ATAN (PI / 12) = 3.5763 (degrees) RL = MAX(U , T) RL = MAX(1.4767 , 1.4767) RL = 1.4767 kPa Area = PI * OD^2 / 4 / n Area = PI * 7.716^2 / 4 / 12 Area = 3.8966 m^2 l = IR - CRR / 2 / 1000 l = 3.85 - 664.9707 / 2 / 1000 l = 3.5175 m l1 = l / COS(Theta) l1 = 3.5175 / COS(3.5763) l1 = 3.5243 m h = l * TAN(Theta) h = 3.5175 * TAN(3.5763) Page: 9/53 h = 0.2198 m Rafter Weight Load (Uniform Load) G = rft-wgt * l1 G = 10.4 * 3.5243 G = 36.6535 kg or 359.4483 N H-GB = G / 2 *( l / h) H-GB = 359.4483 / 2 *( 3.5175 / 0.2198) H-GB = 2,875.5868 N M-G-Max = G * l / 8 M-G-Max = 359.4483 * 3.5175 / 8 M-G-Max = 158.0456 N-m N-G-Max = G * SIN(Theta) + H-GB * COS(Theta) N-G-Max = 359.4483 * SIN(3.5763) + 2,875.5868 * COS(3.5763) N-G-Max = 2,892.4086 N Design Load (Dead Load + Live Load + Snow Load + Roof Plates) q = RL = 1.4767 kPa or 1,476.7677 Pa QQ = Area * q QQ = 3.8966 * 1,476.7677 QQ = 5,730.6289 N H-QB = (QQ / 3) * (l / h) H-QB = (5,730.6289 / 3) * (3.5175 / 0.2198) H-QB = 30,563.3543 N M-Q-Max = 0.128 * QQ * l M-Q-Max = 0.128 * 5,730.6289 * 3.5175 M-Q-Max = 2,580.169 N-m N-Q-Max = QQ * SIN(Theta) + H-QB * COS(Theta) N-Q-Max = 5,730.6289 * SIN(3.5763) + 30,563.3543 * COS(3.5763) N-Q-Max = 30,861.3014 N Hmax = H-GB + H-QB Hmax = 2,875.5868 + 30,563.3543 Hmax = 33,438.9411 N Mmax = M-G-Max + M-Q-Max Mmax = 158.0456 + 2,580.169 Mmax = 2,738.2146 N-m Section Modulus Reqd = Mmax * 1000 / Fbx Section Modulus Reqd = 2,738.2146 * 1000 / 160 Section Modulus Reqd = 17,113.8418 mm^3 or 17.1138 cm^3 Nmax = N-G-Max + N-Q-Max Nmax = 2,892.4086 + 30,861.3014 Nmax = 33,753.71 N Area-Reqd = Nmax / Fa Page: 10/53 Area-Reqd = 33,753.71 / 160 Area-Reqd = 210.9606 mm^2 fa = Nmax / rft-A fa = 33,753.71 / 1,320 fa = 25,570,992.4717 Pa or 25.5709 MPa fbx = Mmax / rft-S fbx = 2,738.2146 / 0.00005296 fbx = 51,703,449.6267 Pa or 51.7034 MPa Criteria = fa / Fa + fbx / Fbx Criteria = 25,570,992.4717 / 160,000,000 + 51,703,449.6267 / 160,000,000 Criteria = 0.4829 Long & Garner - Guide to Storage Tanks & Equipment (Page 126) Area-Crown = 0.0066 m^2 or 6,617 mm^2 Z-Crown = 0.0001 m^3 or 149,123.9932 mm^3 phi = 360/n/2 phi = 360/12/2 phi = 15 (degrees) phi = 0.2617 (radians) Force Between the Rafters Mo = Hmax * CRR/2 * (1 / SIN(phi) - 1 / phi) Mo = 33,438.9411 * 664.9707/2 * (1 / SIN(0.2617) - 1 / 0.2617) Mo = 98,175.955 N-mm No = Hmax / 2 * (1 / SIN(phi)) No = 33,438.9411 / 2 * (1 / SIN(0.2617)) No = 64,599.0738 N S-actual-between-rafters = Mo / Z-Crown + No / Area-Crown S-actual-between-rafters = 98,175.955 / 149,123.9932 + 64,599.0738 / 6,617 S-actual-between-rafters = 10.4209 MPa Force-Between-Rafters-Test = S-Actual-Between-Rafters / Compression-Ring-Sd Force-Between-Rafters-Test = 10.4209 / 160 Force-Between-Rafters-Test = 0.0651 <= 1.0 => Crown ring size is acceptable Cross-Sectional-Area-Required = No / (Compression-Ring-Sd - Mo / Z-Crown) Cross-Sectional-Area-Required = 64,599.0738 / (160 - 98.1759 / 149,123.9932) Cross-Sectional-Area-Required = 405.4123 mm^2 Section-Modulus-Required = Mo / (Compression-Ring-Sd - No / Area-Crown) Section-Modulus-Required = 98.1759 / (160 - 64,599.0738 / 6,617) Section-Modulus-Required = 653.4721 mm^3 Forces at rafters Mi = Hmax * CRR / 2 * (1 / phi - 1 / TAN(phi)) Mi = 33,438.9411 * 664.9707 / 2 * (1 / 0.2617 - 1 / TAN(0.2617)) Mi = 195,678.9132 N-mm Ni = Hmax / 2 * (1 / TAN(phi)) Page: 11/53 Ni = 33,438.9411 / 2 * (1 / TAN(0.2617)) Ni = 62,397.9137 N Total-Tensile-Stress = Mi / Z-Crown + Ni / A-Crown Total-Tensile-Stress = 195,678.9132 / 149,123.9932 + 62,397.9137 / 6,617 Total-Tensile-Stress = 10.7421 Mpa Forces-at-Rafters-Test = Total-Tensile-Stress / Sd Forces-at-Rafters-Test = 10.7421 / 160 Forces-at-Rafters-Test = 0.0671 <= 1.0 => Crown ring size is acceptable Cross-Sectional-Area-Required = Ni / (Sd - Mi / Z-Crown) Cross-Sectional-Area-Required = 62,397.9137 / (160 - 195,678.9132 / 149,123.9932) Cross-Sectional-Area-Required = 393.2117 mm^2 Section-Modulus-Required = Mi / (Sd - Ni / Area-Crown) Section-Modulus-Required = 195,678.9132 / (160 - 62,397.9137 / 6,617) Section-Modulus-Required = 1,299.5871 mm^3 TOP MEMBER DESIGN CA_roof (Thickness of roof plate) = 1 mm CA_shell (Thickness of shell plate) = 1.7 mm D (Shell nominal diameter) = 7.708 m ID (Shell inside diameter) = 7.7 m Theta angle (Angle between the roof and a horizontal plane at the roof-to-shell junction) = 3.5763 deg tc (Thickness of shell plate) = 6 mm th (Thickness of roof plate) = 6 mm Shell inside radius Rc = ID / 2 = 7700.0 / 2 = 3850.0 mm Shell nominal diameter (D) = 7.708 m Length of normal to roof R2 = Rc / SIN(Theta angle) = 3850.0 / SIN(3.5763) = 61720.1952 mm Thickness of corroded roof plate th_corroded = th - CA_roof = 6 - 1 = 5 mm Thickness of corroded shell plate tc_corroded = tc - CA_shell = 6 - 1.7 = 4.3 mm CA_stiff > 0 Note: The calculation does not take into account the stiffener corrosion allowance, make sure to pick a stiffener size that make up the difference in the thicknesses (corroded vs nominal). Maximum width of participating roof API-650 Figure F-2 Wh = MIN((0.3 * SQRT((R2 * th_corroded))) , 300) = MIN((0.3 * SQRT((61720.1952 * 5))) , 300) = 166.6556 mm Maximum width of participating shell API-650 Figure F-2 Wc = 0.6 * SQRT((Rc * tc_corroded)) = 0.6 * SQRT((3850.0 * 4.3)) = 77.1997 mm Nominal weight of shell plates and framing DLS = Ws + W_framing = 177316.3902 + 21705.7193 = 199022.1094 N Nominal weight of roof plates and attached structural Page: 12/53 DLR = Wr + W_structural = 22201.2901 + 7522.843 = 29724.1331 N Compression Ring Detail b Properties ID (Shell inside diameter) = 7.7 m Size (Compression ring size) = l200x200x15 Wc (Length of contributing shell) = 77.1997 mm Wh (Length of contributing roof) = 166.6556 mm h (Top angle to top shell distance) = 4.3 mm tc (Thickness of shell plate) = 4.3 mm th (Thickness of roof plate) = 5 mm Angle vertical leg size (l_vert) = 200 mm Angle horizontal leg size (l_horz) = 200 mm Angle thickness (t_angle) = 15.0 mm Angle area (A_angle) = 5810.0 mm^2 Angle centroid (c_angle) = 54.8 mm Angle moment of inertia (I_angle) = 2.209E7 mm^4 Length of contributing shell reduced wc_reduced = Wc - h = 77.1997 - 4.3 = 72.8997 mm Contributing shell moment of inertia I_shell = (wc_reduced * (tc_corroded^3)) / 12 = (72.8997 * (4.3^3)) / 12 = 483.0033 mm^4 Contributing shell area A_shell = wc_reduced * tc_corroded = 72.8997 * 4.3 = 313.4689 mm^2 Contributing roof area A_roof = Wh * th_corroded = 166.6556 * 5 = 833.278 mm^2 Detail total area A_detail = A_shell + A_roof + A_angle = 313.4689 + 833.278 + 5810.0 = 6956.7469 mm^2 Find combined moment of inertia about shell inside axis with negative value toward center Description Variable Equation Value Unit Shell centroid d_shell tc_corroded / 2 2.1500 mm Stiffener centroid d_stiff c_angle + tc_corroded 59.1000 mm moment of inertia of first body I_1 I_angle + (A_angle * (d_stiff^2)) 42383226.1000 mm^4 moment of inertia of second body I_2 I_shell + (A_shell * (d_shell^2)) 1932.0132 mm^4 Total area A_sum A_angle + A_shell 6123.4689 mm^2 Sum of moments of inertia's I_sum I_1 + I_2 42385158.1132 mm^4 Combined centroid c_combined ((d_stiff * A_angle) + (d_shell * 56.1847 A_shell)) / (A_angle + A_shell) Page: 13/53 mm Combined moment of I_sum - (A_sum * I_combined inertia (c_combined^2)) 23055112.4478 mm^4 Distance from neutral e1 axis to edge 1 (inside) c_combined 56.1847 mm Distance from neutral e2 axis to edge 2 (outside) (tc_corroded + l_horz) - e1 148.1153 mm Combined stiffener shell section modulus I_combined / MAX(e1 , e2) 155656.4698 mm^3 S Roof Design Requirements Appendix F Requirements A_actual (Area resisting compressive force) = 6956.7469 mm^2 D (Tank nominal diameter) = 7.708 m DLR (Nominal weight of roof plates and attached structural) = 29724.1331 N DLS (Nominal weight of shell plates and framing) = 199022.1094 N Fy (Minimum specified yield-strength of the materials in the roof-to-shell junction) = 205 MPa ID (Tank inside diameter) = 7.7 m Mw (Wind moment) = 388376.1052 N.m P (Design pressure) = 7.5 kPa Theta angle (Angle between the roof and a horizontal plane at the roof-to-shell junction) = 3.5763 deg W_framing (Weight of framing supported by the shell and roof) = 21705.7193 N W_structural (Weight of roof attached structural) = 7522.843 N Wr (Roof plates weight) = 22201.2901 N Ws (Shell plates weight) = 177316.3902 N Uplift due to internal pressure API-650 F.1.2 P_uplift = P * pi * ((ID^2) / 4) = 7500.0 * pi * ((7.7^2) / 4) = 349246.9283 N Weight of roof shell and attached-framing W_total = Wr + Ws + W_framing = 22201.2901 + 177316.3902 + 21705.7193 = 221223.3996 N Net uplift due to internal pressure Net_uplift = MAX((P_uplift - W_total) , 0) = MAX((349246.9283 - 221223.3996) , 0) = 128023.5287 N P_uplift > W_total , Tank design should meet F.2 and F.7 requirements. Required area API 650 F.5.1 A_F51 = ((200 * (D^2)) * (P - ((0.00127 * DLR) / (D^2)))) / (Fy * TAN(Theta angle)) = ((200 * (7.708^2)) * (7.5 - ((0.00127 * 29724.1331) / (7.708^2)))) / (205 * TAN(3.5763)) = 6366.4364 mm^2 A_actual >= A_F51 ==> Compression region actual cross sectional area is sufficient. Maximum allowable internal pressure for the actual resisting area API 650 F.5.1 P_F51 = ((Fy * TAN(Theta angle) * A_actual) / (200 * (D^2))) + ((0.00127 * DLR) / (D^2)) = ((205 * TAN(3.5763) * 6956.7469) / (200 * (7.708^2))) + ((0.00127 * 29724.1331) / (7.708^2)) = 8.1365 kPa Page: 14/53 Maximum allowable internal pressure P_max_internal = MIN(P_std , P_F51) = MIN(18 , 8.1365) = 8.1365 kPa SUMMARY OF ROOF RESULTS Back Material = A283M-C Structural Material = A36M t-actual = 6 mm t-required = 6 mm t-calc = 5.4177 mm P-Max-Internal = 8.1365 kPa P-Max-External = 0 kPa Roof Plates Weight = 22,201.2901 N Weight of Rafters = 4,313.3802 N Weight of Girders = 0 N Weight of Columns = 0 N Page: 15/53 SHELL COURSE DESIGN (Bottom course is #1) Back API-650 ONE FOOT METHOD D = Tank Nominal diameter (m) per API-650 5.6.1.1 Note 1 H = Max liquid level (m) I-p = Design internal pressure (kPa) L = Factor I-p = 7.5 kPa D = 7.7 m H = 13.9 m L = (500 * D (t-1 - Ca-1))^0.5 L = (500 * 7.7 (8 - 1.7))^0.5 = 155.7402 Course # 1 Ca-1 = Corrosion allowance per API-650 5.3.2 (mm) G = Design specific gravity of the liquid to be stored H' = Effective liquid head at design pressure (m) hmax-1 = Max liquid level based on shell thickness (m) JE = Joint efficiency pmax-1 = Max pressure at design (kPa) pmax-int-shell-1 = Max internal pressure at design (kPa) Sd = Allowable design stress for the design condition per API-650 Table 5-2b (MPa) St = Allowable stress for the hydrostatic test condition per API-650 5.6.2.2 (MPa) t-1 = Shell actual thickness (mm) t-calc-1 = Shell thickness design condition td (mm) t-seismic-1 = See E.6.2.4 table in SEISMIC calculations. t-test-1 = Shell thickness hydrostatic test condition (mm) Material = A283M-C Width = 1.8 m Ca-1 = 1.7 mm JE = 0.85 t-1 = 8 mm Sd = 137 MPa St = 154 MPa Design Condition G = 1 (per API-650) H' = H + (I-p/(9.8 * G)) (per API-650 F.2) H' = 13.9 + (7.5 / (9.8 * 1)) H' = 14.6653 m t-calc-1 = (4.9 * D * (H' - 0.3) * G)/Sd + Ca-1 (per API-650 5.6.3.2) t-calc-1 = (4.9 * 7.7 * (14.6653 - 0.3) * 1)/137 + 1.7 t-calc-1 = 5.6562 mm hmax-1 = Sd * (t-1 - CA-1)/(2.6 * D * G) + 1 hmax-1 = 137 * (8 - 1.7)/(2.6 * 7.7 * 1) + 1 hmax-1 = 23.1752 m pmax-1 = (hmax-1 - H) * 9.8 * G pmax-1 = (23.1752 - 14.6653) * 9.8 * 1 pmax-1 = 90.8972 kPa pmax-int-shell-1 = pmax-1 Page: 16/53 pmax-int-shell-1 = 90.8972 kPa Hydrostatic Test Condition G = 1 H' = H + (I-p/(9.8 * 1)) H' = 13.9 + (7.5/(9.8 * 1)) H' = 13.9008 m t-test-1 = (* 4.9 D (H' - 0.3))/St t-test-1 = (* 4.9 7.7 (13.9008 - 0.3))/154 t-test-1 = 3.3322 mm Course # 2 Ca-2 = Corrosion allowance per API-650 5.3.2 (mm) G = Design specific gravity of the liquid to be stored H' = Effective liquid head at design pressure (m) hmax-2 = Max liquid level based on shell thickness (m) JE = Joint efficiency pmax-2 = Max pressure at design (kPa) pmax-int-shell-2 = Max internal pressure at design (kPa) Sd = Allowable design stress for the design condition per API-650 Table 5-2b (MPa) St = Allowable stress for the hydrostatic test condition per API-650 5.6.2.2 (MPa) t-2 = Shell actual thickness (mm) t-calc-2 = Shell thickness design condition td (mm) t-seismic-2 = See E.6.2.4 table in SEISMIC calculations. t-test-2 = Shell thickness hydrostatic test condition (mm) Material = A283M-C Width = 1.8 m Ca-2 = 1.7 mm JE = 0.85 t-2 = 8 mm Sd = 137 MPa St = 154 MPa Design Condition G = 1 (per API-650) H' = H + (I-p/(9.8 * G)) (per API-650 F.2) H' = 12.1 + (7.5 / (9.8 * 1)) H' = 12.8653 m t-calc-2 = (4.9 * D * (H' - 0.3) * G)/Sd + Ca-2 (per API-650 5.6.3.2) t-calc-2 = (4.9 * 7.7 * (12.8653 - 0.3) * 1)/137 + 1.7 t-calc-2 = 5.1605 mm hmax-2 = Sd * (t-2 - CA-2)/(2.6 * D * G) + 1 hmax-2 = 137 * (8 - 1.7)/(2.6 * 7.7 * 1) + 1 hmax-2 = 23.1752 m pmax-2 = (hmax-2 - H) * 9.8 * G pmax-2 = (23.1752 - 12.8653) * 9.8 * 1 pmax-2 = 108.5372 kPa pmax-int-shell-2 = MIN(pmax-int-shell-1 pmax-2) pmax-int-shell-2 = MIN(90.8972 108.5372) pmax-int-shell-2 = 90.8972 kPa Page: 17/53 Hydrostatic Test Condition G = 1 H' = H + (I-p/(9.8 * 1)) H' = 12.1 + (7.5/(9.8 * 1)) H' = 12.1008 m t-test-2 = (* 4.9 D (H' - 0.3))/St t-test-2 = (* 4.9 7.7 (12.1008 - 0.3))/154 t-test-2 = 2.8912 mm Course # 3 Ca-3 = Corrosion allowance per API-650 5.3.2 (mm) G = Design specific gravity of the liquid to be stored H' = Effective liquid head at design pressure (m) hmax-3 = Max liquid level based on shell thickness (m) JE = Joint efficiency pmax-3 = Max pressure at design (kPa) pmax-int-shell-3 = Max internal pressure at design (kPa) Sd = Allowable design stress for the design condition per API-650 Table 5-2b (MPa) St = Allowable stress for the hydrostatic test condition per API-650 5.6.2.2 (MPa) t-3 = Shell actual thickness (mm) t-calc-3 = Shell thickness design condition td (mm) t-seismic-3 = See E.6.2.4 table in SEISMIC calculations. t-test-3 = Shell thickness hydrostatic test condition (mm) Material = A283M-C Width = 1.8 m Ca-3 = 1.7 mm JE = 0.85 t-3 = 6 mm Sd = 137 MPa St = 154 MPa Design Condition G = 1 (per API-650) H' = H + (I-p/(9.8 * G)) (per API-650 F.2) H' = 10.3 + (7.5 / (9.8 * 1)) H' = 11.0653 m t-calc-3 = (4.9 * D * (H' - 0.3) * G)/Sd + Ca-3 (per API-650 5.6.3.2) t-calc-3 = (4.9 * 7.7 * (11.0653 - 0.3) * 1)/137 + 1.7 t-calc-3 = 4.6648 mm hmax-3 = Sd * (t-3 - CA-3)/(2.6 * D * G) + 1 hmax-3 = 137 * (6 - 1.7)/(2.6 * 7.7 * 1) + 1 hmax-3 = 15.9148 m pmax-3 = (hmax-3 - H) * 9.8 * G pmax-3 = (15.9148 - 11.0653) * 9.8 * 1 pmax-3 = 55.0248 kPa pmax-int-shell-3 = MIN(pmax-int-shell-2 pmax-3) pmax-int-shell-3 = MIN(90.8972 55.0248) pmax-int-shell-3 = 55.0248 kPa Hydrostatic Test Condition G = 1 Page: 18/53 H' = H + (I-p/(9.8 * 1)) H' = 10.3 + (7.5/(9.8 * 1)) H' = 10.3008 m t-test-3 = (* 4.9 D (H' - 0.3))/St t-test-3 = (* 4.9 7.7 (10.3008 - 0.3))/154 t-test-3 = 2.4502 mm Course # 4 Ca-4 = Corrosion allowance per API-650 5.3.2 (mm) G = Design specific gravity of the liquid to be stored H' = Effective liquid head at design pressure (m) hmax-4 = Max liquid level based on shell thickness (m) JE = Joint efficiency pmax-4 = Max pressure at design (kPa) pmax-int-shell-4 = Max internal pressure at design (kPa) Sd = Allowable design stress for the design condition per API-650 Table 5-2b (MPa) St = Allowable stress for the hydrostatic test condition per API-650 5.6.2.2 (MPa) t-4 = Shell actual thickness (mm) t-calc-4 = Shell thickness design condition td (mm) t-seismic-4 = See E.6.2.4 table in SEISMIC calculations. t-test-4 = Shell thickness hydrostatic test condition (mm) Material = A283M-C Width = 1.8 m Ca-4 = 1.7 mm JE = 0.85 t-4 = 6 mm Sd = 137 MPa St = 154 MPa Design Condition G = 1 (per API-650) H' = H + (I-p/(9.8 * G)) (per API-650 F.2) H' = 8.5 + (7.5 / (9.8 * 1)) H' = 9.2653 m t-calc-4 = (4.9 * D * (H' - 0.3) * G)/Sd + Ca-4 (per API-650 5.6.3.2) t-calc-4 = (4.9 * 7.7 * (9.2653 - 0.3) * 1)/137 + 1.7 t-calc-4 = 4.1691 mm hmax-4 = Sd * (t-4 - CA-4)/(2.6 * D * G) + 1 hmax-4 = 137 * (6 - 1.7)/(2.6 * 7.7 * 1) + 1 hmax-4 = 15.9148 m pmax-4 = (hmax-4 - H) * 9.8 * G pmax-4 = (15.9148 - 9.2653) * 9.8 * 1 pmax-4 = 72.6648 kPa pmax-int-shell-4 = MIN(pmax-int-shell-3 pmax-4) pmax-int-shell-4 = MIN(55.0248 72.6648) pmax-int-shell-4 = 55.0248 kPa Hydrostatic Test Condition G = 1 H' = H + (I-p/(9.8 * 1)) H' = 8.5 + (7.5/(9.8 * 1)) Page: 19/53 H' = 8.5008 m t-test-4 = (* 4.9 D (H' - 0.3))/St t-test-4 = (* 4.9 7.7 (8.5008 - 0.3))/154 t-test-4 = 2.0092 mm Course # 5 Ca-5 = Corrosion allowance per API-650 5.3.2 (mm) G = Design specific gravity of the liquid to be stored H' = Effective liquid head at design pressure (m) hmax-5 = Max liquid level based on shell thickness (m) JE = Joint efficiency pmax-5 = Max pressure at design (kPa) pmax-int-shell-5 = Max internal pressure at design (kPa) Sd = Allowable design stress for the design condition per API-650 Table 5-2b (MPa) St = Allowable stress for the hydrostatic test condition per API-650 5.6.2.2 (MPa) t-5 = Shell actual thickness (mm) t-calc-5 = Shell thickness design condition td (mm) t-seismic-5 = See E.6.2.4 table in SEISMIC calculations. t-test-5 = Shell thickness hydrostatic test condition (mm) Material = A283M-C Width = 1.5 m Ca-5 = 1.7 mm JE = 0.85 t-5 = 6 mm Sd = 137 MPa St = 154 MPa Design Condition G = 1 (per API-650) H' = H + (I-p/(9.8 * G)) (per API-650 F.2) H' = 6.7 + (7.5 / (9.8 * 1)) H' = 7.4653 m t-calc-5 = (4.9 * D * (H' - 0.3) * G)/Sd + Ca-5 (per API-650 5.6.3.2) t-calc-5 = (4.9 * 7.7 * (7.4653 - 0.3) * 1)/137 + 1.7 t-calc-5 = 3.6733 mm hmax-5 = Sd * (t-5 - CA-5)/(2.6 * D * G) + 1 hmax-5 = 137 * (6 - 1.7)/(2.6 * 7.7 * 1) + 1 hmax-5 = 15.9148 m pmax-5 = (hmax-5 - H) * 9.8 * G pmax-5 = (15.9148 - 7.4653) * 9.8 * 1 pmax-5 = 90.3048 kPa pmax-int-shell-5 = MIN(pmax-int-shell-4 pmax-5) pmax-int-shell-5 = MIN(55.0248 90.3048) pmax-int-shell-5 = 55.0248 kPa Hydrostatic Test Condition G = 1 H' = H + (I-p/(9.8 * 1)) H' = 6.7 + (7.5/(9.8 * 1)) H' = 6.7008 m Page: 20/53 t-test-5 = (* 4.9 D (H' - 0.3))/St t-test-5 = (* 4.9 7.7 (6.7008 - 0.3))/154 t-test-5 = 1.5682 mm Course # 6 Ca-6 = Corrosion allowance per API-650 5.3.2 (mm) G = Design specific gravity of the liquid to be stored H' = Effective liquid head at design pressure (m) hmax-6 = Max liquid level based on shell thickness (m) JE = Joint efficiency pmax-6 = Max pressure at design (kPa) pmax-int-shell-6 = Max internal pressure at design (kPa) Sd = Allowable design stress for the design condition per API-650 Table 5-2b (MPa) St = Allowable stress for the hydrostatic test condition per API-650 5.6.2.2 (MPa) t-6 = Shell actual thickness (mm) t-calc-6 = Shell thickness design condition td (mm) t-seismic-6 = See E.6.2.4 table in SEISMIC calculations. t-test-6 = Shell thickness hydrostatic test condition (mm) Material = A283M-C Width = 1.5 m Ca-6 = 1.7 mm JE = 0.85 t-6 = 6 mm Sd = 137 MPa St = 154 MPa Design Condition G = 1 (per API-650) H' = H + (I-p/(9.8 * G)) (per API-650 F.2) H' = 5.2 + (7.5 / (9.8 * 1)) H' = 5.9653 m t-calc-6 = (4.9 * D * (H' - 0.3) * G)/Sd + Ca-6 (per API-650 5.6.3.2) t-calc-6 = (4.9 * 7.7 * (5.9653 - 0.3) * 1)/137 + 1.7 t-calc-6 = 3.2602 mm hmax-6 = Sd * (t-6 - CA-6)/(2.6 * D * G) + 1 hmax-6 = 137 * (6 - 1.7)/(2.6 * 7.7 * 1) + 1 hmax-6 = 15.9148 m pmax-6 = (hmax-6 - H) * 9.8 * G pmax-6 = (15.9148 - 5.9653) * 9.8 * 1 pmax-6 = 105.0048 kPa pmax-int-shell-6 = MIN(pmax-int-shell-5 pmax-6) pmax-int-shell-6 = MIN(55.0248 105.0048) pmax-int-shell-6 = 55.0248 kPa Hydrostatic Test Condition G = 1 H' = H + (I-p/(9.8 * 1)) H' = 5.2 + (7.5/(9.8 * 1)) H' = 5.2008 m t-test-6 = (* 4.9 D (H' - 0.3))/St t-test-6 = (* 4.9 7.7 (5.2008 - 0.3))/154 Page: 21/53 t-test-6 = 1.2007 mm Course # 7 Ca-7 = Corrosion allowance per API-650 5.3.2 (mm) G = Design specific gravity of the liquid to be stored H' = Effective liquid head at design pressure (m) hmax-7 = Max liquid level based on shell thickness (m) JE = Joint efficiency pmax-7 = Max pressure at design (kPa) pmax-int-shell-7 = Max internal pressure at design (kPa) Sd = Allowable design stress for the design condition per API-650 Table 5-2b (MPa) St = Allowable stress for the hydrostatic test condition per API-650 5.6.2.2 (MPa) t-7 = Shell actual thickness (mm) t-calc-7 = Shell thickness design condition td (mm) t-seismic-7 = See E.6.2.4 table in SEISMIC calculations. t-test-7 = Shell thickness hydrostatic test condition (mm) Material = A283M-C Width = 1.5 m Ca-7 = 1.7 mm JE = 0.85 t-7 = 6 mm Sd = 137 MPa St = 154 MPa Design Condition G = 1 (per API-650) H' = H + (I-p/(9.8 * G)) (per API-650 F.2) H' = 3.7 + (7.5 / (9.8 * 1)) H' = 4.4653 m t-calc-7 = (4.9 * D * (H' - 0.3) * G)/Sd + Ca-7 (per API-650 5.6.3.2) t-calc-7 = (4.9 * 7.7 * (4.4653 - 0.3) * 1)/137 + 1.7 t-calc-7 = 2.8471 mm hmax-7 = Sd * (t-7 - CA-7)/(2.6 * D * G) + 1 hmax-7 = 137 * (6 - 1.7)/(2.6 * 7.7 * 1) + 1 hmax-7 = 15.9148 m pmax-7 = (hmax-7 - H) * 9.8 * G pmax-7 = (15.9148 - 4.4653) * 9.8 * 1 pmax-7 = 119.7048 kPa pmax-int-shell-7 = MIN(pmax-int-shell-6 pmax-7) pmax-int-shell-7 = MIN(55.0248 119.7048) pmax-int-shell-7 = 55.0248 kPa Hydrostatic Test Condition G = 1 H' = H + (I-p/(9.8 * 1)) H' = 3.7 + (7.5/(9.8 * 1)) H' = 3.7008 m t-test-7 = (* 4.9 D (H' - 0.3))/St t-test-7 = (* 4.9 7.7 (3.7008 - 0.3))/154 t-test-7 = 0.8332 mm Page: 22/53 Course # 8 Ca-8 = Corrosion allowance per API-650 5.3.2 (mm) G = Design specific gravity of the liquid to be stored H' = Effective liquid head at design pressure (m) hmax-8 = Max liquid level based on shell thickness (m) JE = Joint efficiency pmax-8 = Max pressure at design (kPa) pmax-int-shell-8 = Max internal pressure at design (kPa) Sd = Allowable design stress for the design condition per API-650 Table 5-2b (MPa) St = Allowable stress for the hydrostatic test condition per API-650 5.6.2.2 (MPa) t-8 = Shell actual thickness (mm) t-calc-8 = Shell thickness design condition td (mm) t-seismic-8 = See E.6.2.4 table in SEISMIC calculations. t-test-8 = Shell thickness hydrostatic test condition (mm) Material = A283M-C Width = 1.5 m Ca-8 = 1.7 mm JE = 0.85 t-8 = 6 mm Sd = 137 MPa St = 154 MPa Design Condition G = 1 (per API-650) H' = H + (I-p/(9.8 * G)) (per API-650 F.2) H' = 2.2 + (7.5 / (9.8 * 1)) H' = 2.9653 m t-calc-8 = (4.9 * D * (H' - 0.3) * G)/Sd + Ca-8 (per API-650 5.6.3.2) t-calc-8 = (4.9 * 7.7 * (2.9653 - 0.3) * 1)/137 + 1.7 t-calc-8 = 2.434 mm hmax-8 = Sd * (t-8 - CA-8)/(2.6 * D * G) + 1 hmax-8 = 137 * (6 - 1.7)/(2.6 * 7.7 * 1) + 1 hmax-8 = 15.9148 m pmax-8 = (hmax-8 - H) * 9.8 * G pmax-8 = (15.9148 - 2.9653) * 9.8 * 1 pmax-8 = 134.4048 kPa pmax-int-shell-8 = MIN(pmax-int-shell-7 pmax-8) pmax-int-shell-8 = MIN(55.0248 134.4048) pmax-int-shell-8 = 55.0248 kPa Hydrostatic Test Condition G = 1 H' = H + (I-p/(9.8 * 1)) H' = 2.2 + (7.5/(9.8 * 1)) H' = 2.2008 m t-test-8 = (* 4.9 D (H' - 0.3))/St t-test-8 = (* 4.9 7.7 (2.2008 - 0.3))/154 t-test-8 = 0.4657 mm Course # 9 Page: 23/53 Ca-9 = Corrosion allowance per API-650 5.3.2 (mm) G = Design specific gravity of the liquid to be stored H' = Effective liquid head at design pressure (m) hmax-9 = Max liquid level based on shell thickness (m) JE = Joint efficiency pmax-9 = Max pressure at design (kPa) pmax-int-shell-9 = Max internal pressure at design (kPa) Sd = Allowable design stress for the design condition per API-650 Table 5-2b (MPa) St = Allowable stress for the hydrostatic test condition per API-650 5.6.2.2 (MPa) t-9 = Shell actual thickness (mm) t-calc-9 = Shell thickness design condition td (mm) t-seismic-9 = See E.6.2.4 table in SEISMIC calculations. t-test-9 = Shell thickness hydrostatic test condition (mm) Material = A283M-C Width = 1.5 m Ca-9 = 1.7 mm JE = 0.85 t-9 = 6 mm Sd = 137 MPa St = 154 MPa Design Condition G = 1 (per API-650) H' = H + (I-p/(9.8 * G)) (per API-650 F.2) H' = 0.7 + (7.5 / (9.8 * 1)) H' = 1.4653 m t-calc-9 = (4.9 * D * (H' - 0.3) * G)/Sd + Ca-9 (per API-650 5.6.3.2) t-calc-9 = (4.9 * 7.7 * (1.4653 - 0.3) * 1)/137 + 1.7 t-calc-9 = 2.0209 mm hmax-9 = Sd * (t-9 - CA-9)/(2.6 * D * G) + 1 hmax-9 = 137 * (6 - 1.7)/(2.6 * 7.7 * 1) + 1 hmax-9 = 15.9148 m pmax-9 = (hmax-9 - H) * 9.8 * G pmax-9 = (15.9148 - 1.4653) * 9.8 * 1 pmax-9 = 149.1048 kPa pmax-int-shell-9 = MIN(pmax-int-shell-8 pmax-9) pmax-int-shell-9 = MIN(55.0248 149.1048) pmax-int-shell-9 = 55.0248 kPa Hydrostatic Test Condition G = 1 H' = H + (I-p/(9.8 * 1)) H' = 0.7 + (7.5/(9.8 * 1)) H' = 0.7008 m t-test-9 = (* 4.9 D (H' - 0.3))/St t-test-9 = (* 4.9 7.7 (0.7008 - 0.3))/154 t-test-9 = 0.0982 mm SUMMARY OF SHELL RESULTS Back t-min-Seismic = See API-650 E.6.1.4, table in SEISMIC calculations. Page: 24/53 Shell API-650 Summary (Bottom is 1) Shell Width CA Material # (mm) (mm) Min t-min Tensile t-min t-min Yield Sd St Weight Weight t-Des t-Test ExtJE Strength Erection Seismic Strength (MPa) (MPa) (N) CA (N) (mm) (mm) Pe (MPa) (mm) (mm) (MPa) (mm) 1 1800 A283MC 1.7 0.85 205 380 137 154 26,759 21,078 6 5.6562 3.3322 4.384 2 1800 A283MC 1.7 0.85 205 380 137 154 26,759 21,078 5 5.1605 2.8912 3 1800 A283MC 1.7 0.85 205 380 137 154 20,075 14,390 4 1800 A283MC 1.7 0.85 205 380 137 5 1500 A283MC 1.7 0.85 205 380 6 1500 A283MC 1.7 0.85 205 7 1500 A283MC 1.7 0.85 8 1500 A283MC 9 1500 A283MC 6 8 OK 4.0317 NA 5.1605 8 OK 5 4.6648 2.4502 3.5017 NA 5 6 OK 154 20,075 14,390 5 4.1691 2.0092 3.1821 NA 5 6 OK 137 154 16,729 11,991 5 3.6733 1.5682 2.8632 NA 5 6 OK 380 137 154 16,729 11,991 5 3.2602 1.2007 2.5977 NA 5 6 OK 205 380 137 154 16,729 11,991 5 2.8471 0.8332 2.3284 NA 5 6 OK 1.7 0.85 205 380 137 154 16,729 11,991 5 2.434 0.4657 2.0551 NA 5 6 OK 1.7 0.85 205 380 137 154 16,729 11,991 5 2.0209 0.0982 1.7851 NA 5 6 OK Total Weight = 177,316.3901 N INTERMEDIATE STIFFENER CALCULATIONS PER API-650 Section 5.9.7 D = Nominal diameter of the tank shell (m) Hu = Vertical Distance Between the Intermediate Stiffener (Per API-650 5.9.7) (m) L_act = Actual Transform Height Spacing between Stiffeners (m) L_0 = Uniform Maximum Transform Height Spacing between Stiffineres (m) V = Design wind speed (km/h) Wtr = Transposed width of each shell course (m) Zi = Required Intermediate Stiffener Section Modulus (per API-650 5.9.6.1) (cm^3) Zi-actual = Actual Top Comp Ring Section Modulus (cm^3) D = 7.7 m V = 120 km/h ME = 1 Hu = ME * 9.47 * tsmin * (SQRT (tsmin / D)^3) * (190 / V)^2 Hu = 1 * 9.47 * 6 * (SQRT (6 / 7.7)^3) * (190 / 120)^2 Hu = 97.9798 m (Maximum Height of Unstiffened Shell) Transforming courses (1) to (9) Wtr = Course-width * (SQRT (t-uniform / t-course)^5) Wtr-1 = 1.8 * (SQRT (6 / 8)^5) = 0.8769 m Wtr-2 = 1.8 * (SQRT (6 / 8)^5) = 0.8769 m Wtr-3 = 1.8 * (SQRT (6 / 6)^5) = 1.8 m Wtr-4 = 1.8 * (SQRT (6 / 6)^5) = 1.8 m Wtr-5 = 1.5 * (SQRT (6 / 6)^5) = 1.5 m Wtr-6 = 1.5 * (SQRT (6 / 6)^5) = 1.5 m Wtr-7 = 1.5 * (SQRT (6 / 6)^5) = 1.5 m Wtr-8 = 1.5 * (SQRT (6 / 6)^5) = 1.5 m Page: 25/53 NA tt-min Actual Status (mm) (mm) Wtr-9 = 1.5 * (SQRT (6 / 6)^5) = 1.5 m Wtr = SUM(Wtr-n) Wtr = 12.8537 m For uniformly spaced stiffeners L_0 = Hts/# of Stiffeners + 1 L_0 = 12.8537/(2 + 1) L_0 = 4.2846 m Actual Stiffener Elevations: Stiffener Size Elevation (m) Transformed Elevation (m) 1 l76x76x12.7 8 6.1537 2 l76x76x12.7 11 9.1537 L_act = Max((Wrt - Elev-trans-n) , (Elev-trans-n - Elev-trans-n-1) , Elev-trans-n-1) L_act = Max((12.8537 - 9.1537) , (9.1537 - 6.1537) , 6.1537) L_act = 6.1537 m Number of Intermediate Stiffeners Sufficient Since Hu >= L_act Required section modulus: Size Spacing below (m) (transformed height) 1 l76x76x12.7 2 l76x76x12.7 Stiffener Spacing above (m) (transformed height) Average spacing (m) (transformed height) Required Zi (cm3) (D^2*H/17 )*(V/190)^2 6.1537 3 4.5768 6.3673 3 3.7 3.35 4.6605 SUMMARY OF SHELL STIFFENING RESULTS Stiffener Size Elevation (m) Z-Req'd (cm3) Z-Actual (cm3) Weight (N) 1 l76x76x12.7 8 6.3673 48.5332 3,349.1878 2 l76x76x12.7 11 4.6605 48.5332 3,349.1878 FLAT BOTTOM: NON ANNULAR PLATE DESIGN Back Ba = Area of bottom (cm^2) Bottom-OD = Bottom diameter (m) c = Factor ca-1 = Bottom (1st) shell course corrosion allowance (mm) Ca-bottom = Bottom corrosion allowance (mm) D-bottom = Density of bottom (kg/mm3) G = Design specific gravity of the liquid to be stored H = Max liquid level (m) H' = Effective liquid head at design pressure (m) JE = Bottom joint efficiency S = Maximum Stress in first shell course per API 650 Table 5.1.a S1 = Product stress in the first shell course per API 650 Table 5.1.a S2 = Hydrostatic test stress in the first shell course per API 650 Table 5.1.a t-1 = Bottom (1st) shell course thickness (mm) Page: 26/53 t-actual = Actual bottom thickness (mm) t-calc = Minimum nominal bottom plates thickness per API-650 5.4.1 (mm) t-min = Minimum nominal bottom plates thickness per API-650 5.4.1 (mm) t-test-1 = Bottom (1st) shell course test thickness (mm) t-vac = Vacuum calculations per ASME section VIII Div. 1 (mm) td-1 = Bottom (1st) shell course design thickness (mm) Material = A283M-C t-actual = 8 mm t-min = 6.0 + Ca-bottom t-min = 6.0 + 1.7 t-min = 7.7 mm t-calc = t-min t-calc = 7.7 mm Calculation of Hydrostatic Test Stress & Product Stress (per API-650 Section 5.5.1) Bottom-OD = 7.816 m JE = 0.85 D-bottom = 0.00000784 kg/mm3 t-1 = 8 mm ca-1 = 1.7 mm G=1 H = 13.9 m H' = 14.6653 m St = 154 MPa Sd = 137 MPa Ca-bottom = 1.7 mm Product stress in first shell course S1 = ((td-1 - ca-1) / (t-1 - ca-1)) * Sd S1 = ((5.6562 - 1.7) / (8 - 1.7)) * 137 S1 = 86.0322 MPa Hydrostatic test stress in first shell course S2 = (t-test-1 / t-1) * St S2 = (3.3322 / 8) * 154 S2 = 64.1446 MPa S = Max (S1, S2) S = Max (86.0322 , 64.1446) S = 86.0322 MPa ABS(E-p) < P-btm Then there is no uplift SUMMARY OF BOTTOM RESULTS Back Material = A283M-C t-actual = 8 mm t-req = 7.7 mm NET UPLIFT DUE TO INTERNAL PRESSURE Page: 27/53 Net-Uplift = 128,023.5287 N, (See roof report for calculations) WIND MOMENT (Per API-650 SECTION 5.11) Back A = Area resisting the compressive force, as illustrated in Figure F.1 P-F41 = Design pressure determined in F.4.1 P-v = Internal pressure Wind Velocity per API-650 ASCE 7-05 V_entered = 120 kph I=1 Vs (Wind Velocity) = SQRT(I) * V_entered = 120 kph Vf = (Vs / 190)^2 Vf = (120 / 190)^2 Vf (Velocity Factor) = 0.3989 PWS = 0.86 * Vf PWS = 0.343 kPa PWR = 1.44 * Vf PWR = 0.5744 kPa API-650 5.2.1.k Uplift Check P-F41 = (A * Fy * TAN(Theta))/(200 * D^2) + (0.00127 * DLR)/D^2 P-F41 = (6956.75 * 205 * TAN(3.5763))/(200 * 7.7^2) + ((0.00127 * 29724) / 7.7^2) P-F41 = 8.1534 kPa Wind-Uplift = MIN(PWR , (1.6 * P-F41 - Pv)) Wind-Uplift = MIN(0.5744 , 5.5455) Wind-Uplift = 0.5744 kPa Ap-Vert (Vertical Projected Area of Roof) = 0.9264 m^2 Horizontal Projected Area of Roof (Per API-650 5.2.1.f) Xw (Moment Arm of UPLIFT wind force on roof) = 3.85 m Ap (Projected Area of roof for wind moment) = 46.5663 m^2 M-roof (Moment Due to Wind Force on Roof) = Wind-Uplift * Ap * Xw M-roof = (574.4044 * 46.5663 * 3.85) M-roof = 102,979 N-m Xs (Height from bottom to the Shell's center of gravity) = Shell Height/2 Xs = (14.7/2) Xs = 7.35 m As (Projected Area of Shell) = Shell Height * (D + 2 * t-ins) As = 14.7 * (7.7 + 2 * 0) As = 113.19 m^2 M-Shell (Moment Due to Wind Force on Shell) = (PWS * As * (Shell Height / 2)) M-Shell = (0.343 * 113.19 * (14.7 / 2)) Page: 28/53 M-Shell = 285,397 N-m Mw (Wind moment) = M-roof + M-shell Mw = 102,979 + 285,397 Mw = 388,376.1052 N-m RESISTANCE TO OVERTURNING (per API-650 5.11.2) DLR = Nominal weight of roof plate plus weight of roof plates overlap plus any attached structural. DLS = Nominal weight of the shell and any framing (but not roof plates) support by the shell and roof. F-friction = Maximum of 40% of weight of tank MDL = Moment about the shell-to-bottom joint from the nominal weight of the shell MDLR = Moment about the shell-to-bottom joint from the nominal weight of the roof plate plus any attached structural. MF = Stabilizing moment due to bottom plate and liquid weight MPi = Destabilizing moment about the shell-to-bottom joint from design pressure Mw = Destabilizing wind moment tb = Bottom plate thickness less C.A. wl = Circumferential loading of contents along shell-to-bottom joint An unanchored tank must meet these three criteria: Mw = 388,376 m-N DLS = 199,022.1094 N DLR = 29,724.1331 N MPi = P * (Pi * D^2 / 4) * (D / 2) MPi = 7.5 * (3.1416 * 7.7^2 / 4) * (7.7 / 2) MPi = 1,344.6007 m-N MDL = DLS * (D/2) MDL = 199,022.1094 * 7.7/2 MDL = 766,235 N-m MDLR = DLR * (D/2) MDLR = 29,724.1331 * 7.7/2 MDLR = 114,438 N-m tb = 6.3 mm wl = (min [59 * tb * SQRT(fy-btm * H-liq)] [140.8 * H-liq * D]) wl = (min [59 * 6.3 * SQRT(205 * 13.9)] [140.8 * 13.9 * 7.7]) wl = 15,069.824 N/m MF = (D/2) * wl * Pi * D MF = 3.85 * 15,069.824 * 3.1416 * 7.7 MF = 1,403,491 m-N Criteria 1 0.6 * Mw + MPi < MDL / 1.5 + MDLR 0.6 * 388,376 + 1,344.6007 < 766,235 / 1.5 + 114,438 Since 234,370 < 625,261, Tank is stable Criteria 2 Page: 29/53 Mw + Fp * MPi < (MDL + MF) / 2 + MDLR 388,376 + 0.4 * 1,344.6007 < (766,235 + 1,403,491) / 2 + 114,438 Since 388,914 < 1,199,301, Tank is stable Criteria 3 M-shell + Fp * Mpi < MDL /1.5 + MDLR 285,396.827 + 0.4 * 1,344.6007 < 766,235 / 1.5 + 114,438 Since 285,935 < 625,261, Tank is stable RESISTANCE TO SLIDING (per API-650 5.11.4) F-wind = Vf * 18 * As F-wind = 0.3989 * 18 * 113.19 F-wind = 37,665 N F-friction = 0.4 * [(W-roof-corroded * g) + (W-shell-corroded * g) + (W-btm-corroded * g) + (W-roofstruct * g)] F-friction = 0.4 * [(1,886.5846 * 9.8) + (13,348 * 9.8) + (2,370.3441 * 9.8) + (2,963.9383 * 9.8)] F-friction = 80,684 N No anchorage needed to resist sliding since F-friction > F-wind Anchorage Requirement Tank must be anchored by The design load, per API 650 Table E-6 Page: 30/53 Back SITE GROUND MOTION CALCULATIONS Anchorage_System (Anchorage System) = mechanically anchored D (Nominal Tank Diameter) = 7.7 m Fa (Site Acceleration Coefficient) = 2.5 Fv (Site Velocity Coefficient) = 3.5 H (Maximum Design Product Level) = 13.9 m I (Importance Factor) = 1.25 K (Spectral Acceleration Adjustment Coefficient) = 1.5 Q (MCE to Design Level Scale Factor) = 0.6667 Rwc (Convective Force Reduction Factor) = 2 Rwi (Impulsive Force Reduction Factor) = 4 S1 (Spectral Response Acceleration at a Period of One Second) = 0.05 Seismic_Site_Class (Seismic Site Class) = seismic site class e Seismic_Use_Group (Seismic Use Group) = seismic use group ii Ss (Spectral Response Acceleration Short Period) = 0.12 TL (Regional Dependent Transistion Period for Longer Period Ground Motion) = 4 sec Design Spectral Response Acceleration at Short Period API 650 Sections E.4.6.1 and E.2.2 SDS = Q * Fa * Ss = 0.6667 * 2.5 * 0.12 = 0.2 Design Spectral Response Acceleration at a Period of One Second API 650 Sections E.4.6.1 and E.2.2 SD1 = Q * Fv * S1 = 0.6667 * 3.5 * 0.05 = 0.1167 Sloshing Coefficient API 650 Section E.4.5.2 Ks = 0.578 / SQRT(TANH(((3.68 * Liq_max) / D))) = 0.578 / SQRT(TANH(((3.68 * 13.9) / 7.7))) = 0.578 Convective Natural Period API 650 Section E.4.5.2 Tc = 1.8 * Ks * SQRT(D) = 1.8 * 0.578 * SQRT(7.7) = 2.887 sec Impulsive Design Response Spectrum Acceleration Coefficient API 650 Sections E.4.6.1 Ai = SDS * (I / Rwi) = 0.2 * (1.25 / 4) = 0.0625 API 650 Sections E.4.6.1 Ai = MAX(Ai , 0.007) = MAX(0.0625 , 0.007) = 0.0625 Tc <= TL Convective Design Response Spectrum Acceleration Coefficient API 650 Sections E.4.6.1 Ac = K * SD1 * (1 / Tc) * (I / Rwc) = 1.5 * 0.1167 * (1 / 2.887) * (1.25 / 2) = 0.0379 Ac = MIN(Ac , Ai) = MIN(0.0379 , 0.0625) = 0.0379 Vertical Ground Acceleration Coefficient API 650 Section E.6.1.3 and E.2.2 Av = (2 / 3) * 0.7 * SDS = (2 / 3) * 0.7 * 0.2 = 0.0933 Vertical Ground Acceleration Coefficient Specified by user (Av) = 0.0933 Page: 31/53 SEISMIC CALCULATIONS Back < Mapped ASCE7 Method > Ac = Convective spectral acceleration parameter Ai = Impulsive spectral acceleration parameter Av = Vertical Earthquake Acceleration Coefficient Ci = Coefficient for impulsive period of tank system (Fig. E-1) D/H = Ratio of Tank Diameter to Design Liquid Level Density = Density of tank product (SG * 62.42786) Fc = Allowable longitudinal shell-membrane compressive stress Fty = Minimum specified yield strength of shell course Fy = Minimum yield strength of bottom annulus Ge = Effective specific gravity including vertical seismic effects I = Importance factor defined by Seismic Use Group k = Coefficient to adjust spectral acceleration from 5% - 0.5% damping L = Required Annular Ring Width Ls = Actual Annular Plate Width Mrw = Ringwall moment-portion of the total overturning moment that acts at the base of the tank shell perimeter Ms = Slab moment (used for slab and pile cap design) Pa = Anchorage chair design load Pab = Anchor seismic design load Q = Scaling factor from the MCE to design level spectral accelerations RCG = Height from Top of Shell to Roof Center of Gravity Rwc = Force reduction factor for the convective mode using allowable stress design methods (Table E-4) Rwi = Force reduction factor for the impulsive mode using allowable stress design methods (Table E4) S0 = Design Spectral Response Param. (5% damped) for 0-second Periods (T = 0.0 sec) Sd1 = The design spectral response acceleration param. (5% damped) at 1 second based on ASCE7 methods per API 650 E.2.2 Sds = The design spectral response acceleration param. (5% damped) at short periods (T = 0.2 sec) based on ASCE7 methods per API 650 E.2.2 SigC = Maximum longitudinal shell compression stress SigC-anchored = Maximum longitudinal shell compression stress SUG = Seismic Use Group (Importance factors depends on SUG) T-L = Regional Dependent Transition Period for Long Period Ground Motion (Per ASCE 7-05, fig. 2215) ta = Actual Annular Plate Thickness less C.A. ts1 = Thickness of bottom Shell course minus C.A. tu = Equivalent uniform thickness of tank shell V = Total design base shear Vc = Design base shear due to convective component from effective sloshing weight Vi = Design base shear due to impulsive component from effective weight of tank and contents wa = Force resisting uplift in annular region Wab = Design uplift load on anchor per unit circumferential length Wc = Effective Convective (Sloshing) Portion of the Liquid Weight Weff = Effective Weight Contributing to Seismic Response Wf = Weight of Floor (Incl. Annular Ring) Wi = Effective Impulsive Portion of the Liquid Weight wint = Uplift load due to design pressure acting at base of shell Wp = Total weight of Tank Contents based on S.G. Wr = Weight Fixed Roof, framing and 10 % of Design Snow Load & Insul. Wrs = Roof Load Acting on Shell, Including 10% of Snow Load Ws = Weight of Shell (Incl. Shell Stiffeners & Insul.) wt = Shell and roof weight acting at base of shell Xc = Height to center of action of the lateral seismic force related to the convective liquid force for ringwall moment Xcs = Height to center of action of the lateral seismic force related to the convective liquid force for the slab moment Page: 32/53 Xi = Height to center of action of the lateral seismic force related to the impulsive liquid force for ringwall moment Xis = Height to center of action of the lateral seismic force related to the impulsive liquid force for the slab moment Xr = Height from Bottom of Shell to Roof Center of Gravity Xs = Height from Bottom to the Shell's Center of Gravity g = 9.8 m/s^2 WEIGHTS Ws = 19,855 kgf or 194,708.7291 N Wf = 3,009.9607 kgf or 29,517.6312 N Wr = 2,263.9016 kgf or 22,201.2901 N EFFECTIVE WEIGHT OF PRODUCT D/H = 0.554 Wp = 647,271 kgf Wi = (1 - (0.218 * D/H)) * Wp Wi = (1 - (0.218 * 0.554)) * 647,271 Wi = 569,105 kgf Wc = 0.23 * D/H * TANH (3.67 * H/D) * Wp Wc = 0.23 * 0.554 * TANH (3.67 * 1.8052) * 647,271 Wc = 82,469 kgf Weff = Wi + Wc Weff = 569,105 + 82,469 Weff = 651,573.432 kgf Wrs = 2,263.9016 kgf DESIGN LOADS Vi = Ai * (Ws + Wr + Wf + Wi) Vi = 0.0625 * (19,855 + 2,263.9016 + 3,009.9607 + 569,105) Vi = 37,140 kgf Vc = Ac * Wc Vc = 0.0379 * 82,469 Vc = 3,125.5582 kgf V = SQRT (Vi^2 + Vc^2) V = SQRT (37,140^2 + 3,125.5582^2) V = 37,270.8808 kgf CENTER OF ACTION FOR EFFECTIVE LATERAL FORCES Xs = 6.95 m RCG = 1/3 * R * (TAND (Theta)) RCG = 1/3 * 3909.75 * (TAND (3.5763)) RCG = 81.4531 mm or 0.0815 m Xr = Shell Height + RCG Xr = 14.7 + 0.0815 Xr = 14.7815 m Page: 33/53 CENTER OF ACTION FOR RINGWALL OVERTURNING MOMENT Xi = (0.5 - (0.094 * D/H)) * H Xi = (0.5 - (0.094 * 0.554)) * 13.9 Xi = 6.2262 m Xc = (1 - (COSH (3.67 * H/D) - 1) / ((3.67 * H/D) * SINH (3.67 * H/D))) * H Xc = (1 - (COSH (3.67 * 1.8052) - 1) / ((3.67 * 1.8052) * SINH (3.67 * 1.8052))) * 13.9 Xc = 11.8075 m CENTER OF ACTION FOR SLAB OVERTURNING MOMENT Xis = (0.5 + (0.06 * D/H)) * H) Xis = (0.5 + (0.06 * 0.554)) * 13.9) Xis = 7.412 m Xcs = (1 - (COSH (3.67 * H/D) - 1.937) / ((3.67 * H/D) * SINH(3.67 * H/D))) * H Xcs = (1 - (COSH (3.67 * 1.8052) - 1.937) / ((3.67 * 1.8052) * SINH(3.67 * 1.8052))) * 13.9 Xcs = 11.8127 m Dynamic Liquid Hoop Forces SHELL Width (m) Y (m) Ni (N/mm) Nc (N/mm) Nh (N/mm) = 1.85 * Ac * G * D^2 * = 2.6 * Ai * = 4.9011293 * (COSH (3.68 * (H - Y)) / D) / G * D^2 Y*D*G (COSH (3.68 * H / D)) SUMMARY SigT+ (MPa) SigT- (MPa) = (+ Nh (SQRT (Ni^2 = (- Nh (SQRT (Ni^2 + + Nc^2 + (Av * Nh / Nc^2 + (Av * Nh / 2.5)^2))) / t-n 2.5)^2))) / t-n Shell 1 1.8 13.5952 9.6346 0.0109 513.0651 66.8125 61.4537 Shell 2 1.8 11.7952 9.6346 0.0167 445.1354 58.0424 53.2414 Shell 3 1.8 9.9952 9.6346 0.0358 377.2058 65.7107 60.0245 Shell 4 1.8 8.1952 9.6346 0.0831 309.2761 54.0518 49.0401 Shell 5 1.5 6.3952 9.6346 0.1957 241.3465 42.4228 38.0259 Shell 6 1.5 4.8952 9.4472 0.4007 184.7384 32.7401 28.8393 Shell 7 1.5 3.3952 8.0292 0.8205 128.1304 22.9186 19.7915 Shell 8 1.5 1.8952 5.3063 1.6804 71.5223 12.9492 10.8915 Shell 9 1.5 0.3952 1.2784 3.4416 14.9143 3.1046 1.8668 Overturning Moment Mrw = ((Ai * [(Wi * g) * Xi + (Ws * g) * Xs + (Wr * g) * Xr])^2 + [Ac * (Wc * g) * Xc]^2)^0.5 Mrw = ((0.0625 * [(569,105 * 9.8) * 6.2262 + (19,855 * 9.8) * 6.95 + (2,263.9016 * 9.8) * 14.7815])^2 + [0.0379 * (82,469 * 9.8) * 11.8075]^2)^0.5 Mrw = 2,305,452.3565 N-m Ms = ((Ai * [(Wi * g) * Xis + (Ws * g) * Xs + (Wr * g) * Xr])^2 + [Ac * (Wc * g) * Xcs]^2)^0.5 Ms = ((0.0625 * [(569,105 * 9.8) * 7.412 + (19,855 * 9.8) * 6.95 + (2,263.9016 * 9.8) * 14.7815])^2 + [0.0379 * (82,469 * 9.8) * 11.8127]^2)^0.5 Ms = 2,714,744.7893 N-m RESISTANCE TO DESIGN LOADS Fy = 205 MPa Ge = S.G. * (1- 0.4 * Av) Page: 34/53 Ge = 1 * (1- 0.4 * 0.0933) Ge = 0.9627 wa = MIN (99 * ta * (Fy * H * Ge)^0.5 , 201.1 * H * D * Ge) wa = MIN (99 * 6.3 * (205 * 13.9 * 0.9627)^0.5) , 201.1 * 13.9 * 7.7 * 0.9627) wa = MIN ( 32,666.3829 , 20,720.4672) wa = 20,720.4672 N/m wt = (Wrs + Ws) / (Pi * D) wt = (2,263.9016 + 19,855) / (3.1416 * 7.7) wt = 8,966.8316 N/m wint = P * (Pi * D^2 / 4) / (Pi * D) wint = 7500 * (3.1416 * 7.7^2 / 4) / (3.1416 * 7.7) wint = 14438 N/m Anchorage Ratio J = Mrw / (D^2 * [wt * (1 - 0.4 * Av)] + wa - 0.4 * wint J = 2,305,452.3565 / (7.7^2 * [8,966.8316 * (1 - 0.4 * 0.0933)] + 20,720.4672 - 0.4 * 14,438 J = 1.6492 Since J > 1.54 The tank is not stable and cannot be self-anchored for the design load, per API 650 Table E-6 Maximum Longitudinal Shell-Membrane Compressive Stress ts1 = 6.3 mm SigC = ((wt * (1 + (0.4 * Av)) + wa) / (0.607 - (0.18667 * J^2.3)) - wa) * (1 / (1,000 * ts)) SigC = ((8,966.8316 * (1 + (0.4 * 0.0933)) + 20,720.4672) / (0.607 - (0.18667 * 1.6492^2.3)) 20,720.4672) * (1 / (1,000 * 6.3)) SigC = 275.9758 MPa Allowable Longitudinal Shell-Membrane Compression Stress Fty = 205 MPa Criteria for Fc Since [G * H * D^2 / ts1^2] < 44 Since [1 * 13.9 * 7.7^2 / 6.3^2] < 44 Since 20.7642 < 44 Then Fc = (83 * ts) / (2.5 * D) + (7.5 * SQRT(G * H)) Fc = (83 * ts) / (2.5 * D) + (7.5 * SQRT(SG * H)) Fc = (83 * 6.3) / (2.5 * 7.7) + (7.5 * SQRT(1 * 13.9)) Fc = 55.1256 MPa Hoop Stresses SHELL SUMMARY SigT+ Sd * 1.333 Fy * 0.9 * E Allowable Membrane t-Min Shell Ok Shell 1 66.8125 182.621 156.825 156.825 4.384 OK Shell 2 58.0424 182.621 156.825 156.825 4.0316 OK Page: 35/53 Shell 3 Shell 4 Shell 5 Shell 6 Shell 7 Shell 8 Shell 9 65.7107 54.0518 42.4228 32.7401 22.9186 12.9492 3.1046 182.621 182.621 182.621 182.621 182.621 182.621 182.621 156.825 156.825 156.825 156.825 156.825 156.825 156.825 156.825 156.825 156.825 156.825 156.825 156.825 156.825 3.5017 3.182 2.8631 2.5977 2.3284 2.055 1.7851 OK OK OK OK OK OK OK Mechanically Anchored Number of anchor = 10 Max spacing = 3 m Actual spacing = 2.4969 m Minimum # anchor = 9 Wab = (1.273 * Mrw) / D^2 - wt * (1 - 0.4 * Av) + wint Wab = (1.273 * 2,305,452.3565) / 7.7^2 - 8,966.8316 * (1 - 0.4 * 0.0933) + 14438 Wab = 55,305 N/m Pab = Wab * Pi * D / Na Pab = 55,305 * 3.1416 * 7.7 / 10 Pab = 133,784.4257 N Pa = 3 * Pab Pa = 3 * 133,784.4257 Pa = 401,353.2772 N Shell Compression in Mechanically-Anchored Tanks SigC-anchored = [Wt * (1 + (0.4 * Av)) + (1.273 * Mrw) / D^2] * (1 / (1,000 * ts)) SigC-anchored = [8,966.8316 * (1 + (0.4 * 0.0933)) + (1.273 * 2,305,452.3565) / 7.7^2] * (1 / (1,000 * 6.3)) SigC-anchored = 9.3335 MPa Fc = 55.1256 MPa SigC-anchored <= Fc Then the design is acceptable. Detailing Requirements (Anchorage) SUG = II Sds = 0.2 g or 20 %g Freeboard - Sloshing TL-sloshing = 4 sec I-sloshing = 1.25 Tc = 2.887 k = 1.5 Sd1 = 0.1167 g or 11.67 %g Af = 0.0758 g per API 650 E.7.2 Delta-s = 0.42 * D * Af Delta-s = 0.42 * 7.7 * 0.0758 Page: 36/53 Delta-s = 0.2451 m 0.7 * Delta-s = 0.1716 m Since Sds < 0.33g and SUG = II per API 650 Table E-7. a. A freeboard of O.7*Delta-s is recommended for economic considerations but not required. Sliding Resistance mu = 0.4 (friction coefficient) V = 37,270.8808 kgf Vs = mu * (Ws + Wr + Wf + Wp) * (1 - 0.4 * Av) Vs = 0.4 * (19,855 + 2,263.9016 + 3,009.9607 + 647,271) * (1 - 0.4 * 0.0933) Vs = 258,922.2691 kgf Since V <= Vs Then the tank will not experience major sliding and does not require additional lateral anchorage, per API 650 E.7.6. Local Shear Transfer Vmax = 2 * V / (Pi * D) Vmax = 2 * 37,270.8808 / (3.1416 * 7.7) Vmax = 3,081.4778 kgf/m Page: 37/53 ANCHOR BOLT DESIGN Back Bolt Material : A36M Sy = 250 MPa UPLIFT LOAD CASES, PER API-650 TABLE 5-21b A-s-r = Bolt Root Area Req'd bt = Uplift load per bolt D = Tank D (m) Fp = Pressure Combination Factor Mrw = Seismic Ringwall Moment (Nm) N = Anchor bolt quantity P = Design pressure (pa) Pf = Failure pressure per F.6 (KPa) Pt = Test pressure per F.7.6 = 1.25 * P = 9.375 (pa) sd = Allowable Anchor Bolt Stress (MPa) Shell-sd-at-anchor = Allowable Shell Stress at Anchor Attachment (MPa) t-actual = Actual Roof plate thickness (mm) t-h = Roof plate thickness less CA (mm) Vf = Velocity factor (kph) W1 = Dead Load of Shell minus C.A. and Any Dead Load minus C.A. other than Roof Plate Acting on Shell W2 = Dead Load of Shell minus C.A. and Any Dead Load minus C.A. including Roof Plate minus C.A. Acting on Shell W3 = Dead Load of New Shell and Any Dead Load other than Roof Plate Acting on Shell For Tank with Structural Supported Roof W1 = W-shell-corroded + Shell Insulation W1 = 130,896.6472 + 0 W1 = 130,896.6472 N W2 = W-shell-corroded + Shell Insulation + Corroded Roof Plates Supported by Shell + Roof Dead Load Supported by Shell W2 = 130,896.6472 + 0 + 18,501.0751 + 0 W2 = 149,397.7223 N W3 = New Shell + Shell Insulation W3 = 177,316.3901 + 0 W3 = 177,316.3901 N Uplift Case 1: Design Pressure Only U = [(P - 0.08 * t-h) * D^2 * 785] - W1 U = [(7.5 - 0.08 * 5) * 7.7^2 * 785] - 130,896.6472 U = 199,556.1677 N bt = U/N bt = 19,955.6167 N sd = 104.1666 MPa Shell-sd-at-anchor = 136.6666 MPa A-s-r = bt / sd A-s-r = 19,955.6167 / 104.1666 A-s-r = 191.5739 mm^2 Page: 38/53 Uplift Case 2: Test Pressure Only U = [(Pt - 0.08 * t-h) * D^2 * 785] - W1 U = [(9.375 - 0.08 * 5) * 7.7^2 * 785] - 130,896.6472 U = 286,823.6365 N bt = U/N bt = 28,682.3636 N sd = 138.8888 MPa Shell-sd-at-anchor = 170.8333 MPa A-s-r = bt / sd A-s-r = 28,682.3636 / 138.8888 A-s-r = 206.513 mm^2 Uplift Case 3: Failure Pressure Only Not applicable since if there is a knuckle on tank roof, or tank roof is not frangible. Pf (failure pressure per F.6) = N.A. Uplift Case 4: Wind Load Only PWR = Wind-Uplift per API 650 Table 5-21a, 5-21b PWS = Wind-Pressure per API 650 Table 5-21a, 5-21b PWR = 0.5744 KPa PWS = 343.047 N/m^2 MWH = PWS * D * (H^2 / 2) per API 650 Table 5-21a, 5-21b MWH = 343.047 * 7.7 * (14.7^2 / 2) MWH = 285,396.827 Nm U = PWR * D^2 * 785 + (4 * MWH / D) - W2 U = 0.5744 * 7.7^2 * 785 + (4 * 285,396.827 / 7.7) - 149,397.7223 U = 25,594.674 N bt = U/N bt = 2,559.4674 N sd = 200 MPa Shell-sd-at-anchor = 170.8333 MPa A-s-r = bt / sd A-s-r = 2,559.4674 / 200 A-s-r = 12.7973 mm^2 Uplift Case 5: Seismic Load Only U = [4 * Mrw / D] - W2 * (1 - 0.4 * Av) U = [4 * 2,305,452 / 7.7] - 149,397.7223 * (1 - 0.4 * 0.0933) U = 1,053,815.3884 N bt = U/N bt = 105,381.5388 N sd = 200 MPa Shell-sd-at-anchor = 170.8333 MPa Page: 39/53 A-s-r = bt / sd A-s-r = 105,381.5388 / 200 A-s-r = 526.9076 mm^2 Uplift Case 6: Design Pressure + Wind Load U = [(Fp * P + PWR - 0.08 * t-h) * D^2 * 785] + [4 * MWH / D] - W1 U = [(0.4 * 7.5 + 0.5744 - 0.08 * 5) * 7.7^2 * 785] + [4 * 285,396.827 / 7.7] - 130,896.6472 U = 165,106.6391 N bt = U/N bt = 16,510.6639 N sd = 138.8888 MPa Shell-sd-at-anchor = 170.8333 MPa A-s-r = bt / sd A-s-r = 16,510.6639 / 138.8888 A-s-r = 118.8767 mm^2 Uplift Case 7: Design Pressure + Seismic Load U = [(Fp * P - 0.08 * t-h) * D^2 * 785] + [4 * Mrw / D] - W1 * (1 - 0.4 * Av) U = [(0.4 * 7.5 - 0.08 * 5) * 7.7^2 * 785] + [4 * 2,305,452 / 7.7] - 130,896.6472 * (1 - 0.4 * 0.0933) U = 1,192,636.8934 N bt = U/N bt = 119,263.6893 N sd = 200 MPa Shell-sd-at-anchor = 170.8333 MPa A-s-r = bt / sd A-s-r = 119,263.6893 / 200 A-s-r = 596.3184 mm^2 Uplift Case 8: Frangibility Pressure Not applicable since if there is a knuckle on tank roof, or tank roof is not frangible. Pf (failure pressure per F.6) = N.A. Page: 40/53 ANCHOR BOLT SUMMARY Back Bolt Root Area Req'd = 596.3184 mm^2 Bolt Diameter (d) = 33 mm (M33) Threads per centimeters (n) = 0.2857 A-s = Actual Bolt Root Area A-s = (pi / 4) * (d - 33.02 / n)^2 A-s = 0.7854 * (33 - 33.02 / 0.2857)^2 A-s = 635.7047 mm^2 Exclusive of Corrosion Bolt Diameter Req'd = 31.8486 mm (per ANSI B1.1) Actual Bolt Diameter = 33 mm (M33) Bolt Diameter Meets Requirements ANCHORAGE REQUIREMENTS Wind or Uplift calculations require anchorage Minimum # Anchor Bolts = 9 per API-650 5.12.3 Actual # Anchor Bolts = 10 Anchorage Meets Spacing Requirements ANCHOR CHAIR DESIGN (from AISI 'Steel Plate Engr Data' Dec. 92, Vol. 2, Part VII) Entered Parameters Chair Material : A36M Top Plate Type : DISCRETE Chair Style : VERT. TAPERED Top Plate Width (a) : 300 mm Top Plate Length (b) : 200 mm Vertical Plate Width (k) : 125 mm Top Plate Thickness (c) : 22 mm Bolt Eccentricity (e) : 102 mm Outside of Top Plate to Hole Edge (f) : 74.5 mm Distance Between Vertical Plates (g) : 100 mm Chair Height (h) : 400 mm Vertical Plates Thickness (j) : 16 mm Bottom Plate thickness (m) : 8 mm Shell Course + Repad Thickness (t) : 22 mm Nominal Radius to Tank Centerline (r) : 3854 mm Design Load per Bolt (P) : 178896 N Bolt Diameter (d) = 33 mm (M33) Threads per unit length (n) = 0.2857 Bolt Yield Load = A-s * Sy Bolt Yield Load = 635.7047 * 250 Bolt Yield Load = 158,926.1809 N Seismic Design Bolt Load (Pa) = 401,353.2772 N Anchor Chairs will be designed to withstand Design Load per Bolt Anchor Chair Design Load, (P) : 178,895.534 N Page: 41/53 For anchor Chair Material: A36M (per API-650 Table 5-2b, Sd-Chair = 160 MPa Since bottom t <= 10 mm, and Seismic anchorage required (J) > 1.45, or Wind Speed is > 160.9344 kph, h-min is 305 mm. For Discrete Top Plate, Max. Chair Height Recommended : h <= 3 * a h-max = 3 * a h-max = 3 * 300 = 900 mm. h-actual = 400 mm. e-min = 0.886 * d + 15 e-min = 0.886 * 33 + 15 = 44.238 mm. e-actual = 102 mm. g-min = d + 26 g-min = 33 + 26 = 59 mm. g-actual = 100 mm. f-min = d/2 + 4 f-min = 33/2 + 4 = 20.5 mm. c-min = SQRT[P / Sd-Chair / f * (0.375 * g - 0.22 * d)] c-min = SQRT[178,895.534 / 160 / 74.5 * (0.375 * 100 - 0.22 * 33)] = 21.3035 mm. c-actual = 22 mm. j-min = MAX(13, [0.04 * (h - c)]) j-min = MAX(13, [0.04 * (400 - 22)]) = 15.12 mm. j-actual = 16 mm. b-min = e-min + d + 7 b-min = 44.238 + 33 + 7 = 84.238 mm. Stress due to Top Plate Thickness S-actual-Top-Plate = P / (f * c^2) * (0.375 * g - 0.22 * d) S-actual-Top-Plate = 178,895.534 / (74.5 * 22^2) * (0.375 * 100 - 0.22 * 33) = 150.0305 MPa Repad-t = 14 mm t-shell-1 = 8 mm ClearX = Minimum Clearance of Repad from Anchor chair ClearX = MAX(51, 6 * Repad-t, 6 * t-shell-1) ClearX = MAX(51, 6 * 14, 6 * 8) = 84 mm Minimum Height = h + ClearX Minimum Height = 400 + 84 = 484 mm Page: 42/53 Minimum Width = a + 2 * ClearX Minimum Width = 300 + 2 * 84 = 468 mm Shell Stress due to Chair Height (For discrete Top Plate) S-actual-ChairHeight = P * e / t^2 * F3 Where F3 = F1 + F2 now F1 = (1.32 * z) / (F6 + F7) where F6 = (1.43 * a * h^2) / (r * t) and F7 = (4 * a * h^2)^(1/3) and z = 26 / (F4 * F5 + 26) where F4 = (0.177 * a * m) / SQRT(r * t) and F5 = (m / t)^2 yields F5 = (8 / 22)^2 F5 = 0.1322 yields F4 = (0.177 * 300 * 8) / SQRT(3,850 * 22) F4 = 1.4596 yields z = 26 / (1.4596 * 0.1322 + 26) z = 0.9926 yields F7 = (4 * 300 * 400^2)^(1/3) F7 = 576.8998 yields F6 = (1.43 * 300 * 400^2) / (3,850 * 22) F6 = 810.3896 yields F1 = (1.32 * 0.9926) / (810.3896 + 576.8998) F1 = 0.0009 now F2 = 0.031 / SQRT(r * t) yields F2 = 0.031 / SQRT(3,850 * 22) F2 = 0.0034 yields F3 = 0.0009 + 0.0034 F3 = 0.0043 yields S-actual-ChairHeight = 178,895.534 * 102 / 22^2 * 0.0043 yields S-actual-ChairHeight = 165.1507 MPa Maximum Recommended Stress is 170 MPa for the Shell (per API-650 E.6.2.1.2) Sd-ChairHeight = 170 MPa ANCHOR CHAIR SUMMARY S-actual-Top-Plate Meets Design Calculations (within 105% of Sd-Chair) S-actual-Top-Plate/Sd-Chair 150.0305/160 = 93.76% S-actual-ChairHeight Meets Design Calculations (within 105% of Sd-ChairHeight) S-actual-ChairHeight/Sd-ChairHeight 165.1507/170 = 97.14% Page: 43/53 Page: 44/53 PLAN VIEW APPURTENANCE MARK CUST. MARK DESCRIPTION 1 1/2" 3000# LIQUID LEVEL GAUGE 24" ROOF MANWAY 4" ROOF NOZZLE 8" ROOF NOZZLE 2" ROOF NOZZLE 10" GOOSENECK ROOF VENT WINGRAIL LLG01A RM01 RN01 RN02 RN03 RV01 WR01A INSIDE RADIUS REF PROJ ORIENT REMARKS (mm) DWG (mm) OUTSIDE PROJ (mm) -- -- 317' 3398mm 280mm 0mm 0' 3300mm 178mm 203mm 152mm 0mm 0mm 0mm 65' 3400mm 308.5' 3300mm 222.5' 3350mm 229mm 0mm -- -- 0' RM99 0mm 0' 3773mm ELEVATION VIEW APPURTENANCE MARK CUST. DESCRIPTION MARK AC01A NP01A SM01 SN01 SN01 OUTSIDE PROJ (mm) ANCHOR CHAIRS STD API 24" SHELL MANWAY 3" SHELL NOZZLE 3" SHELL NOZZLE --- INSIDE ELEVATION REF PROJ ORIENT REMARKS (mm) DWG (mm) SEE --TABLE -0' 1016mm 271mm 0mm 225' 750mm W/ DAVIT 175mm 0mm [0'] 240mm HILLSIDE 175mm 0mm [0'] 450mm HILLSIDE Nozzle Nozzle-0001 Reinforcement Requirements (Per API-650 and other references below) NOZZLE Description : 4 in SCH 80 TYPE RFSO t_rpr = (Re Pad Required Thickness) t_n = (Thickness of Neck) Sd_n = (Stress of Neck Material) Sd_s = (Stress of Roof Material) CA = (Corrosion Allowance of Neck) MOUNTED ON ROOF: Elevation = 14.742 ft ROOF PARAMETERS: t-calc = 6 mm t_cr = 5 mm (Roof t-calc less C.A) t_c = 6 mm Page: 45/53 t_Basis = 5 mm (FOR ROOF NOZZLE,REF. API-650 FIG 5-19, TABLE 5-14 AND FOOTNOTE A OF TABLE 5-14, or API-650 FIG 5-20, TABLE 5-15 AND FOOTNOTE A OF TABLE 5-15) Required Area = t_Basis * D Required Area = 5 * 114.3 Required Area = 571.5 mm^2 Available Roof Area = (t_c - t_Basis) * D Available Roof Area = (6 - 5) * 114.3 Available Roof Area = 114.3 mm^2 Available Nozzle Neck Area = [4 * (t_n - CA) + t_c] * (t_n - ca) * MIN((Sd_n/Sd_s) 1) Available Nozzle Neck Area = [4 * (8.5598 - 1.7) + 6] * (8.5598 - 1.7) * MIN((103.4213/137) 1) Available Nozzle Neck Area = 266.3762 mm^2 A-rpr = (Required Area - Available Roof Area - Available Nozzle Neck Area) A-rpr = 571.5 - 114.3 - 266.3762 A-rpr = 190.8238 mm^2 t_rpr = (A_rpr / D) + repad_CA t_rpr = (190.8238 / 114.3) + 1.7 t_rpr = 3.3695 mm Reinforcement Pad is required. Based on Roof Nozzle Size of 4 in Repad Size (OD) Must be 275 mm Nozzle sampling Reinforcement Requirements (Per API-650 and other references below) NOZZLE Description : 8 in SCH 80 TYPE RFSO t_rpr = (Re Pad Required Thickness) t_n = (Thickness of Neck) Sd_n = (Stress of Neck Material) Sd_s = (Stress of Roof Material) CA = (Corrosion Allowance of Neck) MOUNTED ON ROOF: Elevation = 14.748 ft ROOF PARAMETERS: t-calc = 6 mm t_cr = 5 mm (Roof t-calc less C.A) t_c = 6 mm t_Basis = 5 mm (FOR ROOF NOZZLE,REF. API-650 FIG 5-19, TABLE 5-14 AND FOOTNOTE A OF TABLE 5-14, or API-650 FIG 5-20, TABLE 5-15 AND FOOTNOTE A OF TABLE 5-15) Required Area = t_Basis * D Required Area = 5 * 219.075 Required Area = 1095.375 mm^2 Available Roof Area = (t_c - t_Basis) * D Page: 46/53 Available Roof Area = (6 - 5) * 219.075 Available Roof Area = 219.075 mm^2 Available Nozzle Neck Area = [4 * (t_n - CA) + t_c] * (t_n - ca) * MIN((Sd_n/Sd_s) 1) Available Nozzle Neck Area = [4 * (12.7 - 1.7) + 6] * (12.7 - 1.7) * MIN((103.4213/137) 1) Available Nozzle Neck Area = 564.6656 mm^2 A-rpr = (Required Area - Available Roof Area - Available Nozzle Neck Area) A-rpr = 1095.375 - 219.075 - 564.6656 A-rpr = 311.6344 mm^2 t_rpr = (A_rpr / D) + repad_CA t_rpr = (311.6344 / 219.075) + 1.7 t_rpr = 3.1225 mm Reinforcement Pad is required. Based on Roof Nozzle Size of 8 in Repad Size (OD) Must be 450 mm Nozzle LSHL Reinforcement Requirements (Per API-650 and other references below) NOZZLE Description : 2 in SCH 80 TYPE RFSO t_rpr = (Re Pad Required Thickness) t_n = (Thickness of Neck) Sd_n = (Stress of Neck Material) Sd_s = (Stress of Roof Material) CA = (Corrosion Allowance of Neck) MOUNTED ON ROOF: Elevation = 14.7451 ft ROOF PARAMETERS: t-calc = 6 mm t_cr = 5 mm (Roof t-calc less C.A) t_c = 6 mm t_Basis = 5 mm (FOR ROOF NOZZLE,REF. API-650 FIG 5-19, TABLE 5-14 AND FOOTNOTE A OF TABLE 5-14, or API-650 FIG 5-20, TABLE 5-15 AND FOOTNOTE A OF TABLE 5-15) Required Area = t_Basis * D Required Area = 5 * 60.325 Required Area = 301.625 mm^2 Available Roof Area = (t_c - t_Basis) * D Available Roof Area = (6 - 5) * 60.325 Available Roof Area = 60.325 mm^2 Available Nozzle Neck Area = [4 * (t_n - CA) + t_c] * (t_n - ca) * MIN((Sd_n/Sd_s) 1) Available Nozzle Neck Area = [4 * (5.5372 - 1.7) + 6] * (5.5372 - 1.7) * MIN((103.4213/137) 1) Available Nozzle Neck Area = 113.9818 mm^2 A-rpr = (Required Area - Available Roof Area - Available Nozzle Neck Area) A-rpr = 301.625 - 60.325 - 113.9818 A-rpr = 127.3182 mm^2 Page: 47/53 Since Nozzle size <= NPS 2 (per API-650 5.7.2), t_rpr = 0 No Reinforcement Pad required. Nozzle outlet Reinforcement Requirements NOZZLE Description : 3 in SCH 80 TYPE RFSO t_rpr = (Re Pad Required Thickness) t_n = (Thickness of Neck) Sd_n = (Stress of Neck Material) Sd_s = (Stress of Shell Course Material) CA = (Corrosion Allowance of Neck) MOUNTED ON SHELL 1 : Elevation = 0.45 ft COURSE PARAMETERS: t-calc = 6 mm t_cr = 4.3 mm (Course t-calc less C.A) t_c = 6.3 mm (Course t less C.A.) t_Basis = 4.3 mm (SHELL NOZZLE REF. API-650 TABLE 5-6, TABLE 3-6 AND FOOTNOTE A OF TABLE 5-7) Required Area = t_Basis * D Required Area = 4.3 * 88.9 Required Area = 382.27 mm^2 Available Shell Area = (t_c - t_Basis) * D Available Shell Area = (6.3 - 4.3) * 88.9 Available Shell Area = 177.8 mm^2 Available Nozzle Neck Area = [4 * (t_n - CA) + t_c] * (t_n - CA) * MIN((Sd_n/Sd_s) 1) Available Nozzle Neck Area = [4 * (7.62 - 1.7) + 6.3] * (7.62 - 1.7) * MIN((103.4213/137) 1) Available Nozzle Neck Area = 218.4453 mm^2 A-rpr = (Required Area - Available Shell Area - Available Nozzle Neck Area) A-rpr = 382.27 - 177.8 - 218.4453 A-rpr = -13.9753 mm^2 Since A-rpr <= 0, t_rpr = 0 No Reinforcement Pad required. Nozzle drawoff Reinforcement Requirements NOZZLE Description : 3 in SCH 80 TYPE RFSO t_rpr = (Re Pad Required Thickness) t_n = (Thickness of Neck) Sd_n = (Stress of Neck Material) Sd_s = (Stress of Shell Course Material) Page: 48/53 CA = (Corrosion Allowance of Neck) MOUNTED ON SHELL 1 : Elevation = 0.24 ft COURSE PARAMETERS: t-calc = 6 mm t_cr = 4.3 mm (Course t-calc less C.A) t_c = 6.3 mm (Course t less C.A.) t_Basis = 4.3 mm (SHELL NOZZLE REF. API-650 TABLE 5-6, TABLE 3-6 AND FOOTNOTE A OF TABLE 5-7) Required Area = t_Basis * D Required Area = 4.3 * 88.9 Required Area = 382.27 mm^2 Available Shell Area = (t_c - t_Basis) * D Available Shell Area = (6.3 - 4.3) * 88.9 Available Shell Area = 177.8 mm^2 Available Nozzle Neck Area = [4 * (t_n - CA) + t_c] * (t_n - CA) * MIN((Sd_n/Sd_s) 1) Available Nozzle Neck Area = [4 * (7.62 - 1.7) + 6.3] * (7.62 - 1.7) * MIN((103.4213/137) 1) Available Nozzle Neck Area = 218.4453 mm^2 A-rpr = (Required Area - Available Shell Area - Available Nozzle Neck Area) A-rpr = 382.27 - 177.8 - 218.4453 A-rpr = -13.9753 mm^2 Since A-rpr <= 0, t_rpr = 0 No Reinforcement Pad required. Manway Circular-Manway-0001 Reinforcement Requirements MANWAY Description : 24 in SCH -t_rpr = (Re Pad Required Thickness) t_n = (Thickness of Neck) Sd_n = (Stress of Neck Material) Sd_s = (Stress of Shell Course Material) CA = (Corrosion Allowance of Neck) MOUNTED ON SHELL 1 : Elevation = 0.75 ft COURSE PARAMETERS: t-calc = 6 mm t_cr = 4.3 mm (Course t-calc less C.A) t_c = 6.3 mm (Course t less C.A.) t_Basis = 4.3 mm (SHELL MANWAY REF. API-650 TABLE 5-6, TABLE 3-6 AND FOOTNOTE A OF TABLE 5-7) Required Area = t_Basis * D Required Area = 4.3 * 635 Required Area = 2730.5 mm^2 Page: 49/53 Available Shell Area = (t_c - t_Basis) * D Available Shell Area = (6.3 - 4.3) * 635 Available Shell Area = 1270 mm^2 Available Manway Neck Area = [4 * (t_n - CA) + t_c] * (t_n - CA) * MIN((Sd_n/Sd_s) 1) Available Manway Neck Area = [4 * (12.7 - 1.7) + 6.3] * (12.7 - 1.7) * MIN((137/137) 1) Available Manway Neck Area = 761.2 mm^2 A-rpr = (Required Area - Available Shell Area - Available Manway Neck Area) A-rpr = 2730.5 - 1270 - 761.2 A-rpr = 699.3 mm^2 t_rpr = (A_rpr / D) + repad_CA t_rpr = (699.3 / 635) + 1.7 t_rpr = 2.8013 mm Reinforcement Pad is required. Based on Shell Manway Size of 24 in Repad Size (L x W) Must be 1257.3 x 1524 mm Manway Circular-Manway-0001 Reinforcement Requirements (Per API-650 Section 5.8.4 and other references below) MANWAY Description : 24 in SCH -- TYPE t_rpr = (Re Pad Required Thickness) MOUNTED ON ROOF: Elevation = 14.7473 ft ROOF PARAMETERS: t-calc = 6 mm t_cr = 5 mm (Roof t-calc less C.A) t_c = 6 mm t_Basis = 5 mm (FOR ROOF MANWAY,REF. API-650 FIG 5-16, TABLE 5-13) Required Area = t_Basis * D Required Area = 5 * 623.6 Required Area = 3118 mm^2 Available Roof Area = (t_c - t_Basis) * D Available Roof Area = (6 - 5) * 623.6 Available Roof Area = 623.6 mm^2 Available Manway Neck Area = [4 * (t_n - CA) + t_c] * (t_n - ca) * MIN((Sd_n/Sd_s) 1) Available Manway Neck Area = [4 * (7 - 1.7) + 6] * (7 - 1.7) * MIN((137/137) 1) Available Manway Neck Area = 198.09 mm^2 A-rpr = (Required Area - Available Roof Area - Available Manway Neck Area) A-rpr = 3118 - 623.6 - 198.09 A-rpr = 2296.31 mm^2 t_rpr = (A_rpr / D) + repad_CA t_rpr = (2296.31 / 623.6) + 1.7 t_rpr = 5.3823 mm Page: 50/53 Reinforcement Pad is required. Based on Roof Manway Size of 24 in Repad Size (OD) Must be 1150 mm Page: 51/53 CAPACITIES and WEIGHTS Back Maximum Capacity (to Max Liq Level) : 644 M^3 Capacity to Top of Shell (to Tank Height) : 682 M^3 Working Capacity (to Normal Working Level) : 584 M^3 Net working Capacity (Working Capacity - Min Capacity) : 558 M^3 Minimum Capacity (to Min Liq Level) : 25 M^3 Component New Condition (N) New Condition (Kg) Corroded (N) Corroded (Kg) SHELL 177,317 18,082 130,897 13,348 ROOF 22,202 2,264 18,502 1,887 RAFTERS 4,314 440 4,314 440 GIRDERS 0 0 0 0 FRAMING 0 0 0 0 COLUMNS 0 0 0 0 BOTTOM 29,518 3,010 23,246 2,371 STAIRWAYS 20,359 2,076 20,359 2,076 STIFFENERS 17,802 1,817 17,801 1,816 WIND GIRDERS 0 0 0 0 ANCHOR CHAIRS 2,942 300 2,942 300 INSULATION 0 0 0 0 TOTAL 274,454 27,989 218,061 22,238 Weight of Tank, Empty : 274,454 N Weight of Tank, Full of Product (SG = 1) : 6,622,014.1521 N Weight of Tank, Full of Water : 6,622,013.8952 N Net Working Weight, Full of Product : 6,348,018.504 N Net Working Weight Full of Water : 6,348,018.504 N Foundation Area Req'd : 47.9798 m^2 Foundation Loading, Empty : 5,720.1916 N/m^2 Foundation Loading, Full of Product : 132,296.3439 N/m^2 Foundation Loading, Full of Water : 132,296.3385 N/m^2 SURFACE AREAS Roof : 48.1165 m^2 Shell : 355.5968 m^2 Bottom : 47.9798 m^2 Wind Moment : 388,376.1052 N-m Seismic Moment : 2,714,744.7893 N-m MISCELLANEOUS ATTACHED ROOF ITEMS MISCELLANEOUS ATTACHED SHELL ITEMS Page: 52/53 MAWP & MAWV SUMMARY Back MAWP = Maximum calculated internal pressure MAWV = Maximum calculated external pressure MAXIMUM CALCULATED INTERNAL PRESSURE MAWP = 18 kPa or 1,835.658 mmh2o (per API-650 App. F.1.3 & F.7) MAWP = 90.8972 kPa or 9,269.7874 mmh2o (due to shell) MAWP = 8.1534 kPa or 831.4919 mmh2o (due to roof) TANK MAWP = 8.1534 kPa or 831.4939 mmh2o MAXIMUM CALCULATED EXTERNAL PRESSURE MAWV = -6.9 kPa or -703.6689 mmh2o (per API-650 V.1) MAWV = N/A (due to shell) (API-650 App.V not applicable) MAWV = -1.015 kPa or -103.5107 mmh2o (due to roof) TANK MAWV = -1.015 kPa or -103.5101 mmh2o Page: 53/53