TRAINING MANUAL CFM56-5C BASIC ENGINE JANUARY 2002 CTC-133 Level 3 CFM56-5C EF G TRAINING MANUAL BASIC ENGINE Published by CFMI CFMI Customer Training Center Snecma Services - Snecma Group Direction de l’Après-Vente Civile MELUN-MONTEREAU Aérodrome de Villaroche B.P. 1936 77019 - MELUN-MONTEREAU Cedex FRANCE EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION CFMI Customer Training Services GE Aircraft Engines Customer Technical Education Center 123 Merchant Street Mail Drop Y2 Cincinnati, Ohio 45246 USA GENERAL Page 1 Jan 02 CFM56-5C EF G TRAINING MANUAL THIS PAGE INTENTIONALLY LEFT BLANK EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION GENERAL Page 2 Jan 02 CFM56-5C EF G TRAINING MANUAL This CFMI publication is for Training Purposes Only. The information is accurate at the time of compilation; however, no update service will be furnished to maintain accuracy. For authorized maintenance practices and specifications, consult pertinent maintenance publications. The information (including technical data) contained in this document is the property of CFM International (GE and SNECMA). It is disclosed in confidence, and the technical data therein is exported under a U.S. Government license. Therefore, None of the information may be disclosed to other than the recipient. In addition, the technical data therein and the direct product of those data, may not be diverted, transferred, re-exported or disclosed in any manner not provided for by the license without prior written approval of both the U.S. Government and CFM International. COPYRIGHT 1998 CFM INTERNATIONAL EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION GENERAL Page 3 Jan 02 CFM56-5C EF G TRAINING MANUAL THIS PAGE INTENTIONALLY LEFT BLANK EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION GENERAL Page 4 Jan 02 CFM56-5C EFG TRAINING MANUAL TABLE OF CONTENTS EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION CONTENTS BASIC ENGINE Page 1 Jan 02 CFM56-5C EFG Chapter Section TRAINING MANUAL Page Table of Contents 1 to 2 Lexis 1 to 8 Intro 1 to 8 72-00-00 Engine General 1 to 10 72-20-00 Fan Section 1 to 24 72-00-02 Core Engine Major Module 1 to 4 72-30-00 High Pressure Compressor Section 1 to 6 72-40-00 Combustion Section 1 to 6 72-50-00 Turbine Section 1 to 12 72-60-00 Accessory Drive Section 1 to 12 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION CONTENTS BASIC ENGINE Page 2 Jan 02 CFM56-5C EFG TRAINING MANUAL ABBREVIATIONS & ACRONYMS EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION LEXIS Page 1 Jan 02 CFM56-5C EFG A A/C AC ACARS ACMS ACS ADC ADEPT ADIRS AGB AIDS ALF ALT AMB AMM AOG APU ARINC ATA ATHR ATO AIRCRAFT ALTERNATING CURRENT AIRCRAFT COMMUNICATION ADDRESSING and REPORTING SYSTEM AIRCRAFT CONDITION MONITORING SYSTEM AIRCRAFT CONTROL SYSTEM AIR DATA COMPUTER AIRLINE DATA ENGINE PERFORMANCE TREND AIR DATA AND INERTIAL REFERENCE SYSTEM ACCESSORY GEARBOX AIRCRAFT INTEGRATED DATA SYSTEM AFT LOOKING FORWARD ALTITUDE AMBIENT AIRCRAFT MAINTENANCE MANUAL AIRCRAFT ON GROUND AUXILIARY POWER UNIT AERONAUTICAL RADIO, INC. (SPECIFICATION) AIR TRANSPORT ASSOCIATION AUTO THRUST ABORTED TAKE OFF B BITE BMC BPRV BSI BSV BVCS C CBP CCDL CCFG CCU CCW CDP CFDIU CFDS CFMI Ch A Ch B CMC CMM CMS CG EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC TRAINING MANUAL BUILT IN TEST EQUIPMENT BLEED MONITORING COMPUTER BLEED PRESSURE REGULATING VALVE BORESCOPE INSPECTION BURNER STAGING VALVE BLEED VALVE CONTROL SOLENOID (HP) COMPRESSOR BLEED PRESSURE CROSS CHANNEL DATA LINK COMPACT CONSTANT FREQUENCY GENERATOR COMPUTER CONTROL UNIT COUNTER CLOCKWISE (HP) COMPRESSOR DISCHARGE PRESSURE CENTRALIZED FAULT DISPLAY INTERFACE UNIT CENTRALIZED FAULT DISPLAY SYSTEM JOINT GE/SNECMA COMPANY (CFM INTERNATIONAL) channel A channel B CENTRALIZED MAINTENANCE COMPUTER COMPONENT MAINTENANCE MANUAL CENTRAL MAINTENANCE SYSTEM CENTER OF GRAVITY LEXIS Page 2 Jan 02 EFG CFM56-5C cm.g CHATV CIP(HP) CIT(HP) CMS CODEP CPU CRT CSD CSI CSN Cu.Ni.In CW CENTIMETER x GRAMS CHANNEL ACTIVE COMPRESSOR INLET PRESSURE COMPRESSOR INLET TEMPERATURE CENTRALIZED MAINTENANCE SYSTEM HIGH TEMPERATURE COATING CENTRAL PROCESSING UNIT CATHODE RAY TUBE CONSTANT SPEED DRIVE CYCLES SINCE INSTALLATION CYCLES SINCE NEW COPPER.NICKEL.INDIUM CLOCKWISE D DC DCU DISC DIU DMC DMU DPU DRT DIRECT CURRENT DATA CONVERSION UNIT DISCRETE DIGITAL INTERFACE UNIT DISPLAY MANAGEMENT COMPUTER DATA MANAGEMENT UNIT DIGITAL PROCESSING MODULE DE-RATED TAKE-OFF E EBU ENGINE BUILDUP UNIT EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION TRAINING MANUAL ECAM ELECTRONIC CENTRALIZED AIRCRAFT MONITORING ECU ELECTRONIC CONTROL UNIT EFH ENGINE FLIGHT HOURS EFIS ELECTRONIC FLIGHT INSTRUMENT SYSTEM EGT EXHAUST GAS TEMPERATURE EICAS ENGINE INDICATING AND CREW ALERTING SYSTEM EIS ELECTRONIC INSTRUMENT SYSTEM EIVMU ENGINE INTERFACE AND VIBRATION MONITORING UNIT EMF ELECTROMOTIVE FORCE EMI ELECTRO MAGNETIC INTERFERENCE EMU ENGINE MAINTENANCE UNIT (E)EPROM (ELECTRICALLY) ERASABLE PROGRAMMABLE READ ONLY MEMORY ESN ENGINE SERIAL NUMBER F FAA FADEC FAR FDRS FDU FEDERAL AVIATION AGENCY FULL AUTHORITY DIGITAL ENGINE CONTROL FUEL/AIR RATIO FLIGHT DATA RECORDING SYSTEM FIRE DETECTION UNIT LEXIS Page 3 Jan 02 EFG FEIM CFM56-5C FRV FWC FWD FIELD ENGINEERING INVESTIGATION MEMO FAN FRAME/COMPRESSOR CASE VERTICAL (VIBRATION SENSOR) FLIGHT IDLE (F/I) FORWARD LOOKING AFT FLEXIBLE TAKE OFF FLIGHT MANAGEMENT AND GUIDANCE COMPUTER FLIGHT MANAGEMENT SYSTEM FUEL METERING VALVE FOREIGN OBJECT DAMAGE FRONT PANEL ASSEMBLY FLUORESCENT PENETRANT INSPECTION FUEL RETURN VALVE FAULT WARNING COMPUTER FORWARD G GE GEM GI g.in GMT GSE GENERAL ELECTRIC GROUND-BASED ENGINE MONITORING GROUND IDLE (G/I) GRAM x INCHES GREENWICH MEAN TIME GROUND SUPPORT EQUIPMENT H HCF HCU HIGH CYCLE FATIGUE HYDRAULIC CONTROL UNIT FFCCV FI FLA FLX TO FMGC FMS FMV FOD FPA FPI EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC HMU HDS HP HPC HPCR HPSOV HPT HPTC HPT(A)CC HPTCCV HPTR HPRV Hz I IDG ID PLUG IFSD IGB IGN IGV in. I/O IOM IPCV IR TRAINING MANUAL HYDROMECHANICAL UNIT HORIZONTAL DRIVE SHAFT HIGH PRESSURE HIGH PRESSURE COMPRESSOR HIGH PRESSURE COMPRESSOR ROTOR HIGH PRESSURE SHUTOFF VALVE HIGH PRESSURE TURBINE HIGH PRESSURE TURBINE CLEARANCE HIGH PRESSURE TURBINE (ACTIVE) CLEARANCE CONTROL HIGH PRESSURE TURBINE CLEARANCE CONTROL VALVE HIGH PRESSURE TURBINE ROTOR HIGH PRESSURE REGULATING VALVE HERTZ (CYCLES PER SECOND) INTEGRATED DRIVE GENERATOR IDENTIFICATION PLUG IN FLIGHT SHUT DOWN INLET GEARBOX IGNITION INLET GUIDE VANE INCH INPUT/OUTPUT INPUT OUTPUT MODULE INTERMEDIATE PRESSURE CHECK VALVE INFRA RED LEXIS Page 4 Jan 02 CFM56-5C EFG K K L lbs. LCF LE (L/E) L/H LP LPC LPT LPTC LPT(A)CC LPTR LRU LVDT M MO MCD MCDU MCL MCT MDDU MEC X 1000 POUNDS, WEIGHT LOW CYCLE FATIGUE LEADING EDGE LEFT HAND LOW PRESSURE LOW PRESSURE COMPRESSOR LOW PRESSURE TURBINE LOW PRESSURE TURBINE CLEARANCE LOW PRESSURE TURBINE (ACTIVE) CLEARANCE CONTROL LOW PRESSURE TURBINE ROTOR LINE REPLACEABLE UNIT LINEAR VARIABLE DIFFERENTIAL TRANSFORMER AIRCRAFT SPEED MACH NUMBER MAGNETIC CHIP DETECTOR MULTIPURPOSE CONTROL AND DISPLAY UNIT MAXIMUM CLIMB MAXIMUM CONTINUOUS MULTIPURPOSE DISK DRIVE UNIT MAIN ENGINE CONTROL EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION mm. MMEL MTBF MTBR TRAINING MANUAL MILLIMETERS MAIN MINIMUM EQUIPMENT LIST MEAN TIME BETWEEN FAILURES MEAN TIME BETWEEN REMOVALS N N1 (NL) LOW PRESSURE ROTOR ROTATIONAL SPEED N1ACT ACTUAL N1 N1DMD DEMANDED N1 N1CMD COMMANDED N1 N1TARGET TARGETED FAN SPEED N2 (NH) HIGH PRESSURE ROTOR ROTATIONAL SPEED N2ACT ACTUAL N2 NVM NON VOLATILE MEMORY O OAT OGV OSG P P0 P/T25 PCU OUTSIDE AIR TEMPERATURE OUTLET GUIDE VANE OVERSPEED GOVERNOR AMBIENT STATIC PRESSURE HP COMPRESSOR INLET TOTAL AIR PRESSURE/TEMPERATURE PRESSURE CONVERTER UNIT LEXIS Page 5 Jan 02 EFG PLA PMC PMUX PS12 PS13 PS3HP psi psia psid psig PSM PSS PSU PT PT2 Q QAD QTY R RAC/SB RACC RAM RCC CFM56-5C POWER LEVER ANGLE POWER MANAGEMENT CONTROL PROPULSION MULTIPLEXER FAN INLET STATIC AIR PRESSURE FAN OUTLET STATIC AIR PRESSURE COMPRESSOR DISCHARGE STATIC AIR PRESSURE POUNDS PER SQUARE INCH POUNDS PER SQUARE INCH ABSOLUTE POUNDS PER SQUARE INCH DIFFERENTIAL POUNDS PER SQUARE INCH GAGE POWER SUPPLY MODULE (ECU) PRESSURE SUB-SYSTEM POWER SUPPLY UNIT TOTAL PRESSURE FAN INLET TOTAL AIR PRESSURE (PRIMARY FLOW) QUICK ATTACH DETACH QUANTITY ROTOR ACTIVE CLEARANCE/START BLEED ROTOR ACTIVE CLEARANCE CONTROL RANDOM ACCESS MEMORY REMOTE CHARGE CONVERTER EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC RDS R/H RPM RTD RTV RVDT S SAV SB SCU SDI SDU SER SFC SG SLS SMM SMP S/N SNECMA SOL SOV S/R S/V TRAINING MANUAL RADIAL DRIVE SHAFT RIGHT HAND REVOLUTIONS PER MINUTE RESISTIVE THERMAL DEVICE ROOM TEMPERATURE VULCANIZING (MATERIAL) ROTARY VARIABLE DIFFERENTIAL TRANSFORMER STARTER AIR VALVE SERVICE BULLETIN SIGNAL CONDITIONING UNIT SOURCE/DESTINATION IDENTIFIER (BITS) (CF ARINC SPEC) SOLENOID DRIVER UNIT SERVICE EVALUATION REQUEST SPECIFIC FUEL CONSUMPTION SPECIFIC GRAVITY SEA LEVEL STANDARD (CONDITIONS : 29.92 in.Hg / 59°F) STATUS MATRIX SOFTWARE MANAGEMENT PLAN SERIAL NUMBER SOCIETE NATIONALE D’ETUDE ET DE CONSTRUCTION DE MOTEURS D’AVIATION SOLENOID SHUT-OFF VALVE SERVICE REQUEST SHOP VISIT LEXIS Page 6 Jan 02 EFG SVR SW CFM56-5C SHOP VISIT RATE SOFTWARE T T12 T3 FAN INLET TOTAL AIR TEMPERATURE HP COMPRESSOR DISCHARGE AIR TEMPERATURE T49.5 EXHAUST GAS TEMPERATURE T5 LOW PRESSURE TURBINE DISCHARGE TOTAL AIR TEMPERATURE TAT TOTAL AIR TEMPERATURE TBD TO BE DETERMINED T/E TRAILING EDGE T/C THERMOCOUPLE TC (T Case) HP TURBINE CASE TEMPERATURE TCC TURBINE CLEARANCE CONTROL TCJ TEMPERATURE COLD JUNCTION TECU ELECTRONIC CONTROL UNIT INTERNAL TEMPERATURE TGB TRANSFER GEARBOX Ti TITANIUM TLA THROTTLE LEVER ANGLE TM TORQUE MOTOR TMC TORQUE MOTOR CURRENT TO/GA TAKE OFF/GO AROUND T/O TAKE OFF T oil OIL TEMPERATURE EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION TPU T/R TRA TRDV TRAINING MANUAL TSI TSN TTL TRANSIENT PROTECTION UNIT THRUST REVERSER THROTTLE RESOLVER ANGLE THRUST REVERSER DIRECTIONAL VALVE THRUST REVERSER PRESSURIZING VALVE TIME SINCE INSTALLATION (HOURS) TIME SINCE NEW (HOURS) TRANSISTOR TRANSISTOR LOGIC U UER UNSCHEDULED ENGINE REMOVAL TRPV V VAC VBV VDC VDT VRT VSV VOLTAGE, ALTERNATING CURRENT VARIABLE BLEED VALVE VOLTAGE, DIRECT CURRENT VARIABLE DIFFERENTIAL TRANSFORMER VARIABLE RESISTANCE TRANSDUCER VARIABLE STATOR VANE W WDM WFM WOW WATCHDOG MONITOR WEIGHT OF FUEL METERED WEIGHT ON WHEEL LEXIS Page 7 Jan 02 CFM56-5C EFG TRAINING MANUAL ENGLISH/METRIC CONVERSIONS METRIC/ENGLISH CONVERSIONS 1 mile = 1.609 km 1 km = 0.621 mile 1 lb = 0.454 kg 1 kg =2.205 lbs 1 ft = 0.3048 m or 30.48 cm 1 m = 3.281 ft. or 39.37 in. 1 psi = 6.890 kPa or 6.89 x 10-2 bar 1 Pa = 1.45 x 10-4 psi 1 kPa = 0.145 psi or 0.01 bar 1 bar = 14.5 psi 1 in. = 0.0254 m or 2.54 cm 1 cm = 0.3937 in. 1 mil. = 25.4 10-6 m or 25.4mm 1 mm = 39.37 mils. °F = 1.8 x °C + 32 °C = ( °F - 32 ) /1.8 1 in.2 = 6.45 cm² 1 m² = 10.76 sq. ft. 1 cm² = 0.155 sq.in. 1 USG = 3.785 l ( dm³ ) 1 in.3 = 16.39 cm³ 1 m³ = 35.31 cu. ft. 1 dm³ = 0.264 US gallon 1 cm³ = 0.061 cu.in. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC LEXIS Page 8 Jan 02 CFM56-5C EF G TRAINING MANUAL INTRODUCTION TO THE CFM56 FAMILY EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION INTRO BASIC ENGINE Page 1 Jan 02 CFM56-5C EF G TRAINING MANUAL INTRODUCTION TO THE CFM56 FAMILY The CFM56 engine, a high by-pass, dual rotor, axial flow turbofan, was designed in the mid 70’s. It is a product of CFMI. CFM International is a company jointly owned by GENERAL ELECTRIC (GE) of the USA, and SOCIETE NATIONALE D’ETUDE ET DE CONSTRUCTION DE MOTEURS D’AVIATION (SNECMA) of France. CFMI, with the full backing of parent companies holding equal shares, has a dual function : - Overall program management, on behalf of both GE and SNECMA - Single interface with customers for marketing and product support EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC INTRO BASIC ENGINE Page 2 Jan 02 CFM56-5C EF G TRAINING MANUAL DESIGN DEVELOPMENT MANUFACTURING ASSEMBLY Jointly owned company Uses all GENERAL ELECTRIC and SNECMA resources... ...With work split 50/50 One program manager One customer interface MARKETING PRODUCT SUPPORT CUSTOMER SATISFACTION CTC-133-001-00 CFM INTERNATIONAL ORGANIZATION EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION INTRO BASIC ENGINE Page 3 Jan 02 CFM56-5C EF G TRAINING MANUAL INTRODUCTION TO THE CFM56 FAMILY Engine Applications The following chart shows the various engine models for the Airbus A340 aircraft. The engine used on this aircraft is the CFM56-5C, which has several different thrust ratings ranging from 31,200 to 34,000 lbs. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC INTRO BASIC ENGINE Page 4 Jan 02 CFM56-5C EF G TRAINING MANUAL CFM56-5C2 (31,200 lbs) CFM56-5C3 (32,500 lbs) CFM56-5C4 (34,000 lbs) CTC-133-002-00 CFM56-5C FOR AIRBUS APPLICATIONS EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION INTRO BASIC ENGINE Page 5 Jan 02 CFM56-5C EF G TRAINING MANUAL CFM56-5C MAIN CHARACTERISTICS Type of engine Turbo fan Arrangement Two spool axial flow Rotation Clockwise (ALF) Compressors Low Pressure: Fan Booster Stage 1 Stages 2 to 5 High Pressure: HP Compressor Stages 1 to 9 Combustion chamber Annular SAC Turbines - HP Turbine - LP Turbine Stage 1 Stages 1 to 5 Weight 3990 kg (8796 lbs) Overall dimensions - Length - Height - Width 2.99m (116.68 ins) 2.25m (88.6 ins) 1.98m (76.6 ins) EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC INTRO BASIC ENGINE Page 6 Jan 02 CFM56-5C EF G CFM56-5C CTC-133-003-00 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC TRAINING MANUAL CFMI PROPRIETARY INFORMATION INTRO BASIC ENGINE Page 7 Jan 02 CFM56-5C EF G TRAINING MANUAL THIS PAGE INTENTIONALLY LEFT BLANK EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC INTRO BASIC ENGINE Page 8 Jan 02 CFM56-5C EF G TRAINING MANUAL ENGINE GENERAL EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-00-00 BASIC ENGINE Page 1 Jan 02 CFM56-5C EF G TRAINING MANUAL ENGINE GENERAL CONCEPT The CFM56-5C engine is a high by-pass, dual rotor, axial flow turbofan. It is supported by the wing pylon and streamlined by cowlings. Air is sucked into the intake by the fan blades and split into two flow paths, the Primary and the Secondary. The primary airflow passes through the inner portion of the fan blades and is directed into a booster (LPC). The airflow then enters a High Pressure Compressor (HPC) and goes to a combustor. Mixed with fuel and ignited, the gas flow provides energy to a High Pressure Turbine (HPT) and a Low Pressure Turbine (LPT). The secondary airflow passes through the outer portion of the fan blades, the Outlet Guide Vanes (OGV’s) and exits through the nacelle discharge duct, producing approximately 80 % of the total thrust. It also plays a role in the thrust reverser system. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-00-00 BASIC ENGINE Page 2 Jan 02 CFM56-5C EF G TRAINING MANUAL SECONDARY FLOW PRIMARY FLOW THRUST REVERSER DESIGN AND OPERATION CTC-133-004-01 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-00-00 BASIC ENGINE Page 3 Jan 02 CFM56-5C EF G TRAINING MANUAL ENGINE GENERAL CONCEPT The CFM56-5C engine uses a maintenance concept called ‘On Condition Maintenance’. This means that the engine has no periodic overhaul schedules and can remain installed under the wing until something important occurs, or when lifetime limits of parts are reached. For this reason, to monitor and maintain the health of the engine, different tools are available, which are : - Engine performance trend monitoring - Borescope inspection - Lubrication particles analysis - Spectrometric oil analysis program (S.O.A.P) - Engine vibration monitoring system EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-00-00 BASIC ENGINE Page 4 Jan 02 CFM56-5C EF G TRAINING MANUAL TREND MONITORING VIBRATION MONITORING BORESCOPE INSPECTION LUBE PARTICLE ANALYSIS CONDITION MONITORING CTC-133-005-00 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC S.O.A.P. CFMI PROPRIETARY INFORMATION 72-00-00 BASIC ENGINE Page 5 Jan 02 CFM56-5C EF G TRAINING MANUAL ENGINE GENERAL CONCEPT The CFM56-5C engine consists of two independent rotating systems : - The low pressure system rotational speed is designated N1. - The high pressure system rotational speed is designated N2. The engine rotors are supported by 5 bearings, identified in manuals as numbers 1 thru 5, where No. 1 is the most forward and No. 5 the most aft. These bearings are housed in 2 dry sump cavities provided by the fan and turbine frames. Engine structural rigidity is obtained with short lengths between two main structures (frames). The accessory drive system uses energy from the high pressure compressor rotor to drive the engine and aircraft accessories. It also plays a major role in starting. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-00-00 BASIC ENGINE Page 6 Jan 02 CFM56-5C EF G TRAINING MANUAL 5 BEARINGS LP SYSTEM ACCESSORY DRIVE SYSTEM 2 FRAMES HP SYSTEM 2 SUMPS ENGINE GENERAL CONCEPT CTC-133-006-01 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-00-00 BASIC ENGINE Page 7 Jan 02 CFM56-5C EF G TRAINING MANUAL ENGINE GENERAL CONCEPT The CFM56-5C is a modular concept design engine. It has 17 different modules that are enclosed within three major modules and an accessory drive module. The 4 modules are : - The Fan Major Module - The Core Engine Major Module - The Low Pressure Turbine Major Module - The Accessory Drive Module EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-00-00 BASIC ENGINE Page 8 Jan 02 CFM56-5C EF G TRAINING MANUAL CORE ENGINE MAJOR MODULE FAN MAJOR MODULE LOW PRESSURE TURBINE MAJOR MODULE ACCESSORY DRIVE MODULE MODULAR DESIGN CTC-133-007-00 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-00-00 BASIC ENGINE Page 9 Jan 02 CFM56-5C EF G TRAINING MANUAL THIS PAGE INTENTIONALLY LEFT BLANK EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-00-00 BASIC ENGINE Page 10 Jan 02 CFM56-5C EF G TRAINING MANUAL FAN SECTION EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-20-00 BASIC ENGINE Page 1 Jan 02 CFM56-5C EF G TRAINING MANUAL FAN SECTION The fan section is at the front of the engine and, downstream from the air inlet cowl, the section includes the fan and booster module and fan frame module. The purposes of the fan and booster are : - to accelerate air overboard to generate thrust. - to increase the pressure of the air directed to the High Pressure Compressor (HPC). After entering the air inlet cowl, the total engine airflow passes through the fan rotor, which increases the air’s kinetic energy. Most of the airflow is ducted overboard producing approximately 80 % of the total thrust. The remainder is directed through the booster, where it is pressurized before entering the HPC. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-20-00 BASIC ENGINE Page 2 Jan 02 CFM56-5C EF G TRAINING MANUAL AIR INLET COWL FAN SECTION MODULE AIR OVERBOARD AIR TO THE BOOSTER FAN SECTION CTC-133-008-01 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-20-00 BASIC ENGINE Page 3 Jan 02 CFM56-5C EF G TRAINING MANUAL FAN AND BOOSTER MODULE The Fan and Booster module consists of : - a spinner front cone - a spinner rear cone - a single stage fan rotor - a four stage axial booster The spinner front cone is designed to minimize ice buildup and is attached to the spinner rear cone. The spinner rear cone holds the blades axially in position on the fan disk. The fan disk supports the mid-span shrouded fan blades and a booster spool. The booster spool accommodates booster blade stages, numbers 2 thru 5. The booster vane assembly stages, numbers 1 thru 5, are stacked and mounted on the fan frame. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-20-00 BASIC ENGINE Page 4 Jan 02 CFM56-5C EF G TRAINING MANUAL FAN ROTOR BOOSTER SPINNER REAR CONE SPINNER FRONT CONE FAN AND BOOSTER DESIGN CTC-133-009-00 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-20-00 BASIC ENGINE Page 5 Jan 02 CFM56-5C EF G TRAINING MANUAL FAN AND BOOSTER MODULE (CONTINUED) Spinner front cone Interference fit and single angular mounting positions are characteristics of the installation of the front and rear cone onto the fan disk. The spinner front cone has an offset hole on its rear flange, identified by an indent mark, to ensure correct alignment for installation onto the rear cone front flange. The rear flange has 6 mounting screw locations and 3 threaded inserts, located every 120°, for installation of jackscrews used in removal procedures. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-20-00 BASIC ENGINE Page 6 Jan 02 CFM56-5C EF G 6 MOUNTING SCREW LOCATIONS OFFSET HOLE INDENT MARK TRAINING MANUAL MOUNTING SCREW 3 JACKSCREW LOCATIONS SPINNER FRONT CONE CTC-133-010-00 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-20-00 BASIC ENGINE Page 7 Jan 02 CFM56-5C EF G TRAINING MANUAL FAN AND BOOSTER MODULE (CONTINUED) Spinner rear cone The front flange of the spinner rear cone has 6 line replaceable, crimped, self-locking nuts. The inner rear flange has 12 mounting screw holes, for installation onto the fan disk, and there are a further 6 threaded holes for the installation of jackscrews used in rear cone removal procedures. Both front and rear flanges have an offset hole to ensure correct installation and they are identified by indent marks. The rear cone also has an integrated air seal that is glued to its inner rear flange. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-20-00 BASIC ENGINE Page 8 Jan 02 CFM56-5C EF G TRAINING MANUAL REAR FLANGE GLUED SEAL CRIMPED SELF - LOCKING NUTS 12 MOUNTING SCREW HOLES JACKSCREW HOLE REAR CONE CTC-133-011-00 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-20-00 BASIC ENGINE Page 9 Jan 02 CFM56-5C EF G TRAINING MANUAL FAN AND BOOSTER MODULE (CONTINUED) Spinner rear cone (continued) The rear cone prevents axial disengagement of spacers used in the fan blade retention system. It also supports a series of balancing screws that are installed on its outer diameter. There are two sets of balancing screws available and the screws in each set are identified as either P01 to P07 or, P08 to P14. The numbers, which are engraved on the screw heads, are equivalent to various weights. An indent mark is located in between two balancing screws for correct installation of the rear cone onto the fan disk and for identification of fan blade No.1. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-20-00 BASIC ENGINE Page 10 Jan 02 CFM56-5C EF G TRAINING MANUAL FAN BLADE FAN BLADE SPACER FAN DISK BALANCING SCREWS BALANCING SCREWS SPACER REAR CONE CTC-133-012-00 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC INDENT MARK CFMI PROPRIETARY INFORMATION 72-20-00 BASIC ENGINE Page 11 Jan 02 CFM56-5C EF G TRAINING MANUAL FAN AND BOOSTER MODULE (CONTINUED) Fan disk The fan disk outer rim has 36 dovetail recesses for the installation of the fan blades. The inner front flange has an imprint to identify an offset hole for rear cone installation. There are also two identification marks engraved on either side of blade recesses No.1 and 5. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-20-00 BASIC ENGINE Page 12 Jan 02 CFM56-5C EF G TRAINING MANUAL SPHERICAL IMPRINT 1 1 5 5 OFFSET HOLE FAN DISK FRONT FLANGE CTC-133-013-00 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-20-00 BASIC ENGINE Page 13 Jan 02 CFM56-5C EF G TRAINING MANUAL FAN AND BOOSTER MODULE (CONTINUED) Fan blades There are 36 titanium alloy, mid-span shrouded fan blades. Each blade has a dovetail base that slides into a recess on the fan disk outer rim. A retainer lug, machined at the rear end of the blade root, engages the forward flange of the booster spool and limits axial movements. A spacer, installed underneath each blade, limits the radial movement. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-20-00 BASIC ENGINE Page 14 Jan 02 CFM56-5C EF G TRAINING MANUAL 36 FAN BLADES RETAINER LUG DISK SPACER FAN BLADES CTC-133-014-00 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-20-00 BASIC ENGINE Page 15 Jan 02 CFM56-5C EF G TRAINING MANUAL FAN AND BOOSTER MODULE (CONTINUED) Fan blades (continued) Each blade has specific indications engraved on the bottom of the root : - Part number - Serial number - Momentum weight - Manufacturer code The fan blade root faces have an anti-friction plasma coating (Cu-Ni-In) and a top coat of cured molybdenumbase film varnish, which acts as a lubricant. Lubrication of blade roots is further improved by the application of solid molybdenum-base lubricant before installation on the fan disk. The mid-span shroud contact surfaces have a tungstencarbide coating. They are also lubricated with solid molybdenum-base lubricant at blade installation. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-20-00 BASIC ENGINE Page 16 Jan 02 CFM56-5C EF G TRAINING MANUAL MANUFACTURER CODE PART NUMBER MOMENTUM WEIGHT F0301 337-000-114-0 206740 F0491 J023493 TUNGSTEN CARBIDE COATING SERIAL NUMBER SUB-CONTRACTOR NUMBER EXAMPLE SPECIFIC INDICATIONS FAN BLADE TUNGSTEN CARBIDE COATING Cu-Ni-In COATING AND MOLYBDENUM FILM SPECIFIC INDICATIONS FAN BLADE ROOT CTC-133-015-00 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC HARD COATING SURFACE CFMI PROPRIETARY INFORMATION 72-20-00 BASIC ENGINE Page 17 Jan 02 CFM56-5C EF G TRAINING MANUAL FAN FRAME MODULE The fan frame module is the main forward structure for mounting the engine onto the airframe. It supports the fan and booster module, the HPC and cowls. The fan frame module consists of the following 2 major assemblies : - The fan inlet case. - The fan frame. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-20-00 BASIC ENGINE Page 18 Jan 02 CFM56-5C EF G MOUNTING FLANGE TRAINING MANUAL FAN FRAME OUTER FLANGE OUTER RIBS OGV ASSEMBLY ACOUSTICAL PANELS FAN ABRADABLE RUB LAND AGB / TGB MOUNT FAN INLET CASE ASSEMBLY CTC-133-016-00 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-20-00 BASIC ENGINE Page 19 Jan 02 CFM56-5C EF G TRAINING MANUAL FAN FRAME MODULE (CONTINUED) Fan inlet case Fan frame The inner surface of the fan inlet case is lined with 6 forward acoustical panels, 24 aft acoustical panels and provides an abradable shroud which faces the fan blade tips. The fan frame has 12 radial hollow struts that house various equipment and lines. Compartments, formed between the adjacent struts, house Variable Bleed Valve (VBV) actuators which, under certain conditions, redirect primary air into the secondary airflow. The fan inlet case also houses the Outlet Guide Vane (OGV) assembly. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC The rear face of the fan frame provides the front mounts for the engine and the front flange for the High Pressure Compressor (HPC) section. 72-20-00 BASIC ENGINE Page 20 Jan 02 CFM56-5C EF G FAN INLET CASE TRAINING MANUAL FAN FRAME STRUT ABRADABLE SHROUD AFT ACOUSTICAL PANEL (24) FWD ACOUSTICAL PANEL (6) VBV ACTUATOR OUTLET GUIDE VANE (OGV) FRONT ENGINE MOUNT HPC MOUNTING POSITION FAN INLET CASE AND FRAME CTC-133-017-00 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-20-00 BASIC ENGINE Page 21 Jan 02 CFM56-5C EF G TRAINING MANUAL FAN FRAME MODULE (CONTINUED) The Outlet Guide Vane (OGV) assembly The fan OGV assembly consists of the inner shroud and 35 twin vanes. The inner shroud rear flange is bolted to the fan frame and has 35 apertures to allow passage of the vane inner platforms. The vane inner platforms are axially retained by the inner face of the fan OGV inner shroud. The vane outer platforms are bolted to the fan inlet case. A splitter fairing, which separates the primary and secondary airflows, is bolted onto the fan OGV inner shroud forward flange. There are 2 unplugged holes on the inner shroud, between the 4 and 5 o’clock positions, to enable borescope inspection of the booster vane assemblies. One is located between the OGV’s at the stage 3 vane assembly and the other at the stage 5 vane assembly. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-20-00 BASIC ENGINE Page 22 Jan 02 CFM56-5C EF G OUTER PLATFORM OUTLET GUIDE VANE TRAINING MANUAL UNPLUGGED BORESCOPE HOLE (S03) UNPLUGGED BORESCOPE HOLE (S05) OGV SPLITTER FAIRING OGV INNER SHROUD INNER PLATFORM FAN OUTLET GUIDE VANES CTC-133-018-00 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-20-00 BASIC ENGINE Page 23 Jan 02 CFM56-5C EF G TRAINING MANUAL THIS PAGE INTENTIONALLY LEFT BLANK EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-20-00 BASIC ENGINE Page 24 Jan 02 CFM56-5C EFG TRAINING MANUAL CORE ENGINE MAJOR MODULE EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-00-02 BASIC ENGINE Page 1 Jan 02 CFM56-5C EFG TRAINING MANUAL CORE ENGINE MAJOR MODULE The core engine is a high pressure, high speed, gas generator that produces the power to drive the engine. The core engine consists of the : - The High Pressure Compressor (HPC) section. - The Combustion section. - The High Pressure Turbine (HPT) section & the Low Pressure Turbine (LPT) stage 1 nozzle. Fan discharge air is compressed in the HPC section and heated and expanded in the combustion section. It is then directed to the HPT section. Energy not extracted from the gas stream by the HPT is used to drive the LPT, fan rotors and booster. The forward end of the core is supported by the No 3 ball and roller bearings and the aft end by the No 4 roller bearing. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-00-02 BASIC ENGINE Page 2 Jan 02 CFM56-5C EFG TRAINING MANUAL COMBUSTION CASE HIGH PRESSURE COMPRESSOR STATOR HPT SECTION COMBUSTION SECTION STAGE 1 LPT NOZZLES HIGH PRESSURE COMPRESSOR ROTOR #3 BEARING #4 BEARING HPC SECTION CORE ENGINE MAJOR MODULE CTC-133-019-01 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-00-02 BASIC ENGINE Page 3 Jan 02 CFM56-5C EFG TRAINING MANUAL THIS PAGE INTENTIONALLY LEFT BLANK EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-00-02 BASIC ENGINE Page 4 Jan 02 CFM56-5C EFG TRAINING MANUAL HIGH PRESSURE COMPRESSOR SECTION EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-30-00 BASIC ENGINE Page 1 Jan 00 CFM56-5C EFG TRAINING MANUAL THE HIGH PRESSURE COMPRESSOR (HPC) The High Pressure Compressor (HPC) is mounted between the fan frame module and the combustion case. The HPC, which has 9 stages, increases the pressure of the air as it passes from stage to stage, to supply the combustor section. It consists of the following modules : - The compressor rotor - The compressor stator The compressor stator is made up of two parts and the front is supported by the fan frame and the rear is attached to the combustion case. The HPC has pipe connections that duct bleed air for both engine and aircraft use. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-30-00 BASIC ENGINE Page 2 Jan 00 CFM56-5C EFG TRAINING MANUAL HIGH PRESSURE COMPRESSOR FRONT STATOR HIGH PRESSURE COMPRESSOR REAR STATOR HIGH PRESSURE COMPRESSOR ROTOR 4TH STAGE BLEED AIR 9TH STAGE BLEED AIR HP COMPRESSOR SECTION CTC-133-020-01 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC 5TH STAGE BLEED AIR CFMI PROPRIETARY INFORMATION 72-30-00 BASIC ENGINE Page 3 Jan 00 CFM56-5C EFG TRAINING MANUAL THE HIGH PRESSURE COMPRESSOR (HPC) Borescope ports The lower stator case has a series of plugged ports to allow for borescope inspection of the rotor and stator vanes. There are 9 borescope inspection ports located at approximately the 5 o’clock position and they are numbered S1 thru S9, where S1 is the most forward. S7, S8 and S9 plugs are double plugs connected by a shaft. A spring-loaded system enables the outer plug to drive the inner plug. Both inner and outer plugs have specific torque values. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-30-00 BASIC ENGINE Page 4 Jan 00 CFM56-5C EFG S6 S5 FWD TRAINING MANUAL S4 S3 S2 S1 TOP VERTICAL S9 S1 TO S9 S8 AFT LOOKING FORWARD S7 S6 BORESCOPE PLUG ( S1 TO S6 ) S9 BORESCOPE PLUG ASSEMBLY ( S7 TO S9 ) S7 S9 S8 S6 S5 S4 S3 S2 S1 HPC BORESCOPE PORTS CTC-133-021-00 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-30-00 BASIC ENGINE Page 5 Jan 00 CFM56-5C EFG TRAINING MANUAL THIS PAGE INTENTIONALLY LEFT BLANK EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-30-00 BASIC ENGINE Page 6 Jan 00 CFM56-5C EFG TRAINING MANUAL COMBUSTION SECTION EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-40-00 BASIC ENGINE Page 1 Jan 02 CFM56-5C EFG TRAINING MANUAL THE COMBUSTION SECTION The combustion section is located between the High Pressure Compressor (HPC) and the Low Pressure Turbine (LPT). Air from the HPC is mixed with fuel, supplied by 20 fuel nozzles. The mixture is ignited by 2 igniter plugs that are located at the 4 and 8 o’ clock positions. The front face of the combustor is attached to the rear of the compressor module. The rear section of the combustion case houses the HPT module. The combustion section also supplies HPC 9th stage bleed air for both aircraft and engine use. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-40-00 BASIC ENGINE Page 2 Jan 02 CFM56-5C EFG TRAINING MANUAL FUEL NOZZLE x20 IGNITER PLUGS x2 LPT STATOR 9TH STAGE BLEED AIR ENERGY HIGH PRESSURE COMPRESSOR HIGH PRESSURE TURBINE COMBUSTOR DESIGN CTC-133-022-01 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC ANNULAR COMBUSTION CHAMBER CFMI PROPRIETARY INFORMATION 72-40-00 BASIC ENGINE Page 3 Jan 02 CFM56-5C EFG TRAINING MANUAL THE COMBUSTION SECTION Borescope ports There are 4 plugged ports (S12, S13, S14, S15) around the combustion case, which enable borescope inspection of the combustion chamber. Two other ports are available, using the spark igniter ports S10 and S11, which can also be used to inspect the High Pressure Turbine (HPT) blades. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-40-00 BASIC ENGINE Page 4 Jan 02 CFM56-5C EFG TRAINING MANUAL BORESCOPE PORT LOCATIONS (ALF) S12 S15 S13 COMBUSTION CASE S10 IGNITER S11 IGNITER S14 FWD BORESCOPE PLUG S12, S13, S14, S15 CTC-133-023-01 IGNITER (S10, S11) COMBUSTION CASE BORESCOPE PORTS EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-40-00 BASIC ENGINE Page 5 Jan 02 CFM56-5C EFG TRAINING MANUAL THIS PAGE INTENTIONALLY LEFT BLANK EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-40-00 BASIC ENGINE Page 6 Jan 02 CFM56-5C EFG TRAINING MANUAL TURBINE SECTION EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-50-00 BASIC ENGINE Page 1 Jan 02 CFM56-5C EFG TRAINING MANUAL TURBINE SECTION The turbine section provides the necessary power to drive the compressor rotors. It consists of the : - High Pressure Turbine (HPT) - Low Pressure Turbine (LPT) High Pressure Turbine (HPT) Engine cooling Air from the 4th stage of the HPC is ducted through 4 pipes, to cool down the LPT stage 1 nozzle and the front cavity. Air from the 4th and 9th stage of the HPC goes through the HPTCC valve and is ducted through 2 pipes, to cool down the cavity that surrounds the HPT shroud. The HPT module is housed in the combustion case and consists of a single stage nozzle that directs the gas flow from the combustion chamber to the HPT rotor blades that drive the HPC rotor. The LPT stage 1 nozzle is also housed in the combustion case. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-50-00 BASIC ENGINE Page 2 Jan 02 CFM56-5C EFG HPC 4th / 9th STAGE COOLING AIR TRAINING MANUAL HPC 4th STAGE COOLING AIR LPT STATOR COMBUSTOR CASE STAGE 1 LPT NOZZLE HPT ROTOR HPT NOZZLE HPT SHROUD HPTCC VALVE CTC-133-024-01 HPT & STAGE 1 LPT NOZZLE ASSEMBLY EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-50-00 BASIC ENGINE Page 3 Jan 02 CFM56-5C EFG TRAINING MANUAL TURBINE SECTION HPT borescope ports Borescope ports S16 and S17 are used to inspect the HPT section. Igniter ports S10 and S11 (and combustion chamber ports S12 thru S15) can also be used to inspect the HPT front sections. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-50-00 BASIC ENGINE Page 4 Jan 02 CFM56-5C EFG TRAINING MANUAL BORESCOPE PORT LOCATIONS (ALF) S12 S15 S13 S17 S11 IGNITER S10 IGNITER S14, S16 FWD FWD S16, S17 HPT BORESCOPE PORTS CTC-133-025-01 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC BORESCOPE PLUG S16 OR S17 CFMI PROPRIETARY INFORMATION 72-50-00 BASIC ENGINE Page 5 Jan 02 CFM56-5C EFG TRAINING MANUAL TURBINE SECTION Low Pressure Turbine (LPT) The LPT module converts the energy of gasses from combustion into the necessary torque to drive the fan and booster rotor. The LPT is a 5 stage axial flow turbine that consists of a rotor and stator assembly. The LPT module front flange is mounted onto the rear flange of the combustor module. Its rear flange is attached onto the LPT frame and its inner flange is secured onto the LPT shaft. Fan discharge air is ducted through manifolds that are provided with orifices, to direct cooling air onto the LPT outer case. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-50-00 BASIC ENGINE Page 6 Jan 02 CFM56-5C EFG TRAINING MANUAL TURBINE FRAME LPT ROTOR / STATOR ASSEMBLY UPPER COOLING MANIFOLD TUBE SUPPORT AIR MANIFOLD LPT SHAFT LOWER COOLING MANIFOLD CTC-133-026-00 LOW PRESSURE TURBINE MODULE EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-50-00 BASIC ENGINE Page 7 Jan 02 CFM56-5C EFG TRAINING MANUAL TURBINE SECTION LPT Borescope Ports There are 6 borescope ports for inspection of the LPT blades. Ports S16 and S17, which are located at the 5 and 8 o’clock positions respectively, are used to examine the LPT stage 1 blade leading edge. Ports S18, S19, S20 and S21, at the 5 o’clock position, are located between all stages. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-50-00 BASIC ENGINE Page 8 Jan 02 CFM56-5C EFG TRAINING MANUAL S16, S17 BORESCOPE PLUGS S18, S19, S20, S21 BORESCOPE PLUGS S16, S17 S18 S19 S17 S16, S18, S19, S20, S21 BORESCOPE PORT LOCATIONS (ALF) CTC-133-027-00 S21 LOW PRESSURE TURBINE BORESCOPE PORTS EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC S20 CFMI PROPRIETARY INFORMATION 72-50-00 BASIC ENGINE Page 9 Jan 02 CFM56-5C EFG TRAINING MANUAL TURBINE SECTION Turbine Frame Module The turbine frame module is one of the engine major structural assemblies, and is located at the rear of the engine. It is made up of a hub and an outer casing. Bolted on the rear flange of the LPT case, the turbine frame rear flange provides attachment for the exhaust mixer and exhaust plug. The outer casing is equipped with mounts for rear engine installation on the airframe. The aft side of the turbine frame hub provides support and attachment for : - the flange assembly and, at its center, the flame arrestor - the exhaust plug EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-50-00 BASIC ENGINE Page 10 Jan 02 CFM56-5C EFG TRAINING MANUAL EXHAUST MIXER SUPPORT FLANGE VENTING AND OIL DRAIN TUBE STRUT FAIRING FLANGE ASSEMBLY FLAME ARRESTOR OIL SUPPLY TUBE SCAVENGE TUBE TURBINE FRAME MODULE CTC-133-029-00 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-50-00 BASIC ENGINE Page 11 Jan 02 CFM56-5C EFG TRAINING MANUAL THIS PAGE INTENTIONALLY LEFT BLANK EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-50-00 BASIC ENGINE Page 12 Jan 02 CFM56-5C EFG TRAINING MANUAL ACCESSORY DRIVE SECTION EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-60-00 BASIC ENGINE Page 1 Jan 02 CFM56-5C EFG TRAINING MANUAL ACCESSORY DRIVE SECTION The accessory drive system is located at the 6 o’clock position. In order to drive the engine and aircraft accessories, part of the core engine power is extracted through the Inlet Gearbox (IGB) and transmitted through the following gearboxes and shafts : - Radial Drive Shaft (RDS) - Transfer Gearbox (TGB) - Horizontal Drive Shaft (HDS) - Accessory Gearbox (AGB) At engine start, the accessory drive system transmits external power from the engine air starter to drive the core engine. For maintenance tasks, there is a hand-cranking pad on the AGB that is used to manually turn the core engine. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-60-00 BASIC ENGINE Page 2 Jan 02 CFM56-5C EFG TRAINING MANUAL INLET GEARBOX (IGB) FAN FRAME THICK STRUT (6 O'CLOCK) UPPER RADIAL DRIVE SHAFT (RDS) LOWER RADIAL DRIVE SHAFT HORIZONTAL DRIVE SHAFT (HDS) ACCESSORY GEARBOX (AGB) TRANSFER GEARBOX (TGB) CTC-133-030-00 ACCESSORY DRIVE SECTION DESIGN EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-60-00 BASIC ENGINE Page 3 Jan 02 CFM56-5C EFG TRAINING MANUAL THE ACCESSORY GEARBOX (AGB) The AGB consists of a gear train that reduces and increases the rotational speed to drive various engine and aircraft accessories. The AGB’s rear face connects with the Horizontal Drive Shaft (HDS) coupling tube and provides mounting pads for : - The fuel pump - The N2 speed sensor - The starter The AGB’s front face has mounting pads for the following equipment : The fuel pump and IDG are installed on the AGB through Quick Attach/Detach (QAD) rings. The AGB assembly is mounted under the fan inlet case at the 6 o’clock position and is secured by 2 clevis mounts. - Lube unit - Hydraulic pump - Hand-cranking drive - Control alternator - Integrated Drive Generator (IDG) EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-60-00 BASIC ENGINE Page 4 Jan 02 CFM56-5C EFG TRAINING MANUAL CLEVIS MOUNT FUEL PUMP/HMU PAD N2 SPEED SENSOR MOUNTING PAD LUBRICATION UNIT PAD HORIZONTAL DRIVE COUPLING TUBE STARTER PAD HYDRAULIC PUMP PAD FWD HANDCRANKING PAD CLEVIS MOUNT CONTROL ALTERNATOR PAD IDG PAD ACCESSORY GEARBOX HOUSING CTC-133-031-00 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-60-00 BASIC ENGINE Page 5 Jan 02 CFM56-5C EFG TRAINING MANUAL THE ACCESSORY GEARBOX (CONTINUED) Sealing Sealing of the AGB is provided by 2 configurations of carbon-contact seals : - Magnetic type - Spring-loaded type Magnetic seals The magnetic-type seal consists of : - a non-magnetic housing, which contains a magnetized mating ring with a polished face and a retaining ring. - a rotating seal with carbon material held in a rotating ring. This type of seal can be used on the following pads : - Integrated Drive Generator (IDG) - Hydraulic pump - Fuel pump EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-60-00 BASIC ENGINE Page 6 Jan 02 CFM56-5C EFG (ASSEMBLED) TRAINING MANUAL (DISASSEMBLED) NON MAGNETIC SEAL HOUSING MAGNETIZED RING RETAINING RING O-RING SEALS STATIC PART ROTATING PART CARBON CONTACT FACE O-RING SEAL MAGNETIC SEAL CTC-133-032-00 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC LAPPED OR POLISHED CONTACT FACE CFMI PROPRIETARY INFORMATION 72-60-00 BASIC ENGINE Page 7 Jan 02 CFM56-5C EFG TRAINING MANUAL THE ACCESSORY GEARBOX (CONTINUED) Starter drive pad seal On the starter drive pad only, a different configuration of magnetic seal is used. It has a thrust ring, which also acts as a heat sink, installed in between the mating ring and retaining ring. EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-60-00 BASIC ENGINE Page 8 Jan 02 CFM56-5C EFG TRAINING MANUAL (ASSEMBLED) STATIC PART O-RING SEAL THRUST RING OIL DRAINING HOLES ROTATING PART O-RING SEAL (DISASSEMBLED) STATIC PART NON MAGNETIC SEAL HOUSING RETAINING RING THRUST RING CARBON CONTACT FACE MAGNETIZED RING LAPPED OR POLISHED CONTACT FACE CTC-133-033-00 MAGNETIC SEAL (STARTER DRIVE ONLY) EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-60-00 BASIC ENGINE Page 9 Jan 02 CFM56-5C EFG TRAINING MANUAL THE ACCESSORY GEARBOX (CONTINUED) Spring-loaded seals Spring-loaded seals have a rotating mating ring with 4 lugs that engage in corresponding slots machined in the gear shaft bearing. A housing, which contains the spring-loaded seal, ensures constant contact between the polished face and the carbon seal element. This type of seal can be used on the following drive pads: - Integrated Drive Generator (IDG) - Hydraulic pump - Starter - Fuel pump EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-60-00 BASIC ENGINE Page 10 Jan 02 CFM56-5C EFG TRAINING MANUAL CARBON CONTACT FACE (DISASSEMBLED) (ASSEMBLED) O-RING SEAL O-RING SEALS STATIC PART MATING RING ROTATING PART LUGS LAPPED OR POLISHED CONTACT FACE SPRING LOADED SEAL CTC-133-034-00 EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 TOC CFMI PROPRIETARY INFORMATION 72-60-00 BASIC ENGINE Page 11 Jan 02 CFM56-5C EFG TRAINING MANUAL THIS PAGE INTENTIONALLY LEFT BLANK EFFECTIVITY ALL CFM56-5C ENGINES FOR A340 CFMI PROPRIETARY INFORMATION TOC 72-60-00 BASIC ENGINE Page 12 Jan 02
