SSN2079-0228
The annotated variant of the collection
”Proceedings of NPO Energomash”,
volume #30
FEDERAL SPACE AGENCY
Lenin, October Revolution and Labour Red Banner’ orders
NPO Energomash named after academician V.Glushko
(GDL-OKB)
PROCEEDINGS
XXX
Editor-in-chief – doctor of technical sciences, professor V.K.Chvanov
Moscow 2013
UDC 621.45:622.612
Kiselev Alexander Sergeevich, cand. of phys-math. sciences.
Russia, Moscow region, Khimki, NPO Energomash named after academician V.P. Glushko. Tel. (495)
286-92-54.
ABOUT INFLUENCE OF NON-STATIONARY PROCESSES ON COMBUSTION EFFICIENCY IN
CHAMBER OF LPRE
Calculation study of acoustic and vortex processes at interaction of jets of kerosene and oxygen with
the combustion in chamber of LPRE on the basis of LES-model with a detailed calculation of dynamics
of turbulent vortexes in the anisotropic range is presented. The results of the study allow to identify
specific processes that lead to increased combustion efficiency in these engines.
Key words: liquid propellant rocket engines, mixing of propellant components, turbulence, diffusion,
non-stationary processes, modeling of combustion.
UDC 621.45:622.612
Chvanov Vladimir Konstantinovich, doctor of techn. sciences,
Sternin Leonid Evgenievich, doctor of phys-math. sciences,
Tamalintseva Tatiana Nikolaevna.
Russia, Moscow region, Khimki, NPO Energomash named after academician V.P. Glushko. Tel. (495)
286-92-54.
ABOUT LIMITING POSSIBILITIES OF ISOBARIC AND ISOCHORIC THERMODYNAMIC CYCLES AT
THEIRS REALISATION IN LPRE
Limiting energy possibilities of increasing the specific impulse of rocket engine, operated at
combustion of propellant under cycle V = const in comparison with combustion under cycle p = const,
are defined. Limiting advantage of vacuum specific impulse of LPRE for isochoric combustion (V =
const) in comparison with isobaric one (p = const) for equilibrium flow by about 7% under pressure in
the chamber pc = 250 kgf/cm2, and frozen flow - up to 10% is shown. Account of these and other
factors can increase specific impulse of detonation rocket engines up to 15% [1, 2].
Key words: liquid propellant rocket engines, combustion of propellant, Brayton cycle, Humphrey cycle,
enthalpy, specific impulse.
2
UDC 621.455:622.75:546.241
Chvanov Vladimir Konstantinovich, doctor of techn. sciences,
Sternin Leonid Evgenievich, doctor of phys-math. sciences,
Tamalintseva Tatiana Nikolaevna.
Russia, Moscow region, Khimki, NPO Energomash named after academician V.P. Glushko. Tel. (495)
286-92-54.
Milovanov Alexander Georgievich, doctor of techn. sciences.
Russia, Moscow, Roscosmos.
THE CHOICE OF FUELS FOR OXYGEN-CONTAINING PROPELLANTS
A number of fuels that at connection with acetylene can provide high specific impulses of LPRE are
considered.
Key words: liquid rocket fuel, acetylene, propane, hydrazine, acetam, ethanol.
UDC 621.45:532.525
Kiselev Alexander Sergeevich, cand. of phys-math. sciences,
Starkov Vladimir Kirillovich, cand. of techn. sciences,
Russia, Moscow region, Khimki, NPO Energomash named after academician V.P. Glushko. Tel. (495) 286-92-54.
Short message
SELECT OF CONTOUR OF SUPERSONIC PART OF A NOZZLE OF RD195 ENGINE CHAMBER
Key words: liquid propellant rocket engines, chamber, nozzle, contour profiling.
3
UDC 621.455:662.75+541.6
Gaponov Valery Dmitrievich, cand. of techn. sciences,
Russia, Moscow region, Khimki, NPO Energomash named after academician V.P. Glushko. Tel. (495)
286-92-54.
Konovalov Konstantin Borisovich, cand. of techn. sciences,
Russia, Tomsk, Tomsk Polytechnic University
COMPARISON OF EFFECTIVENESS OF REDUCE OF HYDRODYNAMIC FRICTION OF LIQUID
HYDROCARBONS WITH ADDITIVES OF POLYISOBUTYLENE AND HIGHER ALPHA-OLEFINS
COPOLYMER
Experimental dependences of resistance coefficient against Reynolds number at flow in the capillaries
of different diameters for solutions of different concentrations of ultrahigh molecular weight
copolymer of higher alpha-olefins and industrial polyisobutylene in nefrase (product of refining of
gasoline fraction) are presented. The possibility of the use of polyalpha-olefins as an alternative for
polyisobutylene as the additive to hydrocarbon components of rocket propellant for reduction of
hydrodynamic losses in lines of fuel of liquid propellant rocket engine is considered.
Keywords: hydrocarbon rocket fuel, polyisobutylene, polymers of higher alpha-olefins, decrease of
hydrodynamic friction.
UDC 622.613:547.211+546.21
Alexandrov Boris Petrovich, cand. of phys-math. sciences,
Russia. Moscow region, Khimki. NPO Energomash named after academician V.P. Glushko. Tel. (495)
286-92-54.
NUMERICAL MODELING OF SPATIALLY HOMOGENEOUS COMBUSTION OF METHANE IN OXYGEN
4
A model of ignition of spatially homogeneous mixture of methane and oxygen at a constant pressure is
created. Modeling of oxidative conversion of methane into synthesis gas, including with initiation by
electron beam is conducted. It is shown that decomposition of methane and oxygen under influence of
beam and subsequent reactions lead to volume heating of initial mixture, which can significantly
reduce the ignition temperature.
Key words: numerical modeling, kinetic model, oxidation of methane, synthesis gas, initiation by
electron beam.
UDC 6 29 .7: 62 1. 37 5. 8+ 5 41. 12
AL E XAN DR O V B OR I S P ET R O VIC H, CAN D. OF P HY S- M AT H. S CI EN CE S,
BEZ N OZDR EV V I KT OR N IK OL A EV ICH , CAN D . O F P H YS- MA TH . S C IEN C ES.
R US SIA . M OSC O W R E G IO N , K HIM KI . N P O EN ER G O MA SH N AM ED AF TER ACA DE MICI AN V. P .
GL US H KO . T EL . (4 95) 2 86- 9 2- 5 4.
S IM UL A TIO N OF R E D UC T IO N OF U RA N IU M HE X AFL UO R I D E W IT H USE OF A TO M I C
HY D ROG E N GE NE R AT OR
R ESUL T S OF R E SEA R C H OF H IGH - PER F OR MA N CE MET H OD S OF R E DUC TI ON OF D EPL ET E D
(IN U 2 3 5 IS O T OP E) U R AN IUM HE XAF L UOR I DE UF 6 - B Y- PR O DUC T IN PR O DUC TI O N O F
N UCL EAR F UEL - T O SIG N IF I CAN TL Y M OR E I N ER T IN C HEM IC AL R E SP ECT UR A N IU M
TE TR AF L UOR ID E UF 4 WI T H US E OF A TO MI C HY DR OGEN GEN E R AT OR OF SU PER SON I C
CON TIN UO US C HEM IC AL L ASER S OF N PO E N ER GO MA SH D EVE L O P MEN T AR E PR E SEN TE D .
TH E S TU D Y WA S CA R R IE D O UT IN F R A M EW OR K O F C ON VER SI ON PR O GR AM OF N P O
EN ER G OMA SH ON IM PL EM EN T AT IO N OF DEV EL O PM EN TS IN AL L IED BR AN CH ES O F
IN DU S T R Y. T W O- DIM E N SI ON AL GA S - D YN A MI C MOD EL OF R ED UC TI ON OF UF 6 T O UF 4 IS
CR EA TED . P ER F O R M E D CO M P UT AT IO N S HA VE S H O WN THE PR I N CIPA L P O SS IBIL IT Y O F
SUC H R E D UCT I ON OF DEPL E TE D UR AN I UM HEX AF L U OR I DE A T HIG HER PR O DUC TI VI T Y
TH AN CUR R EN TL Y U SE D TEC HN OL OG Y.
5
KE Y W OR D S: N UCL E A R P O WER , R E PR O CE SS IN G O F DE PL E TE D UR AN IUM H E XAF L U OR I D E
WI T H U SE OF A T OM IC H Y DR OGEN GEN E R AT OR , G A S- D YN AMIC MO DEL , N U MER I CAL
SIM UL A TI ON .
UDC 621.455:662.76
Adjyan Alexey Pogosovich, cand. of techn. sciences,
Koshelev Igor Mikhailovich,
Levochkin Petr Sergeevich, cand. of techn. sciences.
Russia, Moscow region, Khimki. NPO Energomash named after academician V.P. Glushko. Tel. (495) 286-92-54.
SUPPRESSION OF HIGH-FREQUENCY LONGITUDINAL INSTABILITY IN PREBURNERS OF LPRE BY
THROTTLING ORIFICES
Analysis of causes of acoustic longitudinal modes of pressure pulsations in preburners of LPRE with
afterburning is conducted. The most effective way to suppress these pulsations is considered.
Key words: liquid propellant rocket engines, preburner, pressure pulsations, suppression of high-frequency
instability, throttling orifices.
UDC 621.45:629.7
Gemranova Ekaterina Anatolievna,
Kolbasenkov Anatoly Ivanovich, cand. of techn. sciences,
Koshelev Igor Mikhailovich,
Levochkin Petr Sergeevich, cand. of techn. sciences,
Martirosov David Surenovich, doctor of techn. sciences.
Russia. Moscow region, Khimki. NPO Energomash named after academician V.P. Glushko. Tel. (495)
286-92-54.
6
WAYS OF SUPPRESSION OF LOW-FREQUENCY PULSATIONS IN LPRE AT MODES OF DEEP
THROTTLING
Main causes of appearance of low-frequency pulsations in powerful LPRE at modes of 27...30 %
nominal thrust are considered and methods of their suppression are proposed.
Keywords: deep throttling of LPRE, low-frequency pulsations, stability, three-way valve.
UDC 62-253:621.438.001.5
Loshkarev Alexander Nikolaevich,
Merzlyakov Denis Vladimirovich.
Russia, Moscow region, Khimki. NPO Energomash named after academician V.P. Glushko. Tel. (495)
286-92-54.
STUDY OF INFLUENCE OF GEOMETRICAL DEVIATIONS
CHARACTERISTICS OF TURBINE ROTOR OF LPRE
OF
BLADES
ON
DYNAMIC
The comparative calculation-experimental modal analysis of model of turbine rotor and its verification
with a nick type defect of different sizes and locations is conducted. A table of relative changes in the
first three natural frequencies for various geometrical sizes of defect is obtained. The sensitivity of
calculation model to a nick type defect of variable geometry is studied.
Key words: liquid propellant rocket engines, turbine, rotor, geometrical deviations, dynamic
characteristics, modal analysis.
UDC 621.45:621.375:662.612
Belov Evgeny Alekseevich,
Dubovik Dina Ivanovna,
7
Ivanov Nikolay Gennadievich,
Klyueva Olga Gennadievna, cand. of techn. sciences,
Levochkin Petr Sergeevich, cand. of techn. sciences,
Romasenko Evgeny Nikolaevich, cand. of techn. sciences.
Russia, Moscow region, Khimki, NPO Energomash named after academician V.P. Glushko. Tel. (495) 286-92-54.
Golikov Andrey Nikolaevich, doctor of techn. sciences,
Viktor Alexandrovich Golubev,
Rebrov Sergey Grigorievich, doctor of techn. sciences.
Russia, Moscow, RC named after M.V.Keldysh.
EXPERIMENTAL INVESTIGATION OF INFLUENCE OF LOCATION OF LASER FOCUSING AREA ON IGNITION
OF OXYGEN-KEROSENE PROPELLANT
Results of second phase of investigation at model rig of test facility of NPO Energomash and process of laser
ignition of non-self-ignitable "gaseous oxygen-kerosene" propellant are presented. Estimation of influence of
location of focusing area of laser ignition device on presence of ignition in conditions approached to normal ones
of start-up of steering and main chambers of RD107 and RD108 engines was main objective of experiments.
During the fire tests, we used two laser ignition devices with different characteristics. Injector heads with
different number and design of injector elements are used in model rigs. The calculation estimation of density of
laser radiation power in focusing areas is conducted.
Key words: liquid propellant rocket engines, ignition of propellant components, laser ignition, fire tests.
UDC 621.45:620.17
Polyansky Alexander Mikhailovich, cand. of techn. sciences,
Milov Alexander Evgenievich, cand. of techn. sciences.
Russia, Moscow region, Khimki, NPO Energomash named after academician V.P. Glushko. Tel. (495)
286-92-54.
Polyansky Vladislav Mikhailovich, doctor of techn. sciences.
Russia, Moscow, MSTU named after N.E.Bauman.
CAUSES AND MECHANISM OF FORMATION OF LOCAL BURN-THROUGH IN COOLED WALLS OF
COMBUSTION CHAMBERS
8
Study of burn-through and nickel coating bulging on cooled walls of combustion chambers of LPRE is
conducted. Causes and possible mechanisms of formation of defects are considered. Simulation of nonstationary thermal state of chamber at nominal heat removal and in event of its violation due to
ultrasonic cavitation on chamber wall is conducted by the finite element method in the threedimensional formulation.
Key words: liquid propellant rocket engines, combustion chamber, heat-resistant coatings, burnthrough, simulation of thermal state of a cooled wall.
UDC 669.14.018:621.822
Novikov Victor Ivanovich, сand. of techn. sciences.
Russia, Moscow region, Khimki, NPO Energomash named after academician V.P. Glushko. Tel. (495) 286-92-54.
DEVELOPMENT AND APPLICATION OF HIGH-STRENGTH CASTING STEEL VNL-6 IN WELDED STRUCTURES
OF LPRE
The results of researches in NPO Energomash for development and application of high-strength corrosionresistant steel VNL-6 in welded structures of LPRE are presented. The necessity of adjustment of composition,
technology of smelting and mode of heat treatment of steel VNL-6 to ensure the required complex of mechanical
and corrosive properties is substantiated.
Key words: liquid propellant rocket engines, casting steel, welded construction, strength, toughness, corrosion
resistance, technology of smelting, stabilization of austenite.
UDC 621.45.04
Kanalin Yuri Ivanovich,
Pudonina Nadezhda Borisovna,
Sidorenko Alexander Sergeevich,
9
Tolstikov Leonid Alexeevich, cand. of techn. sciences.
Russia, Moscow region, Khimki, NPO Energomash named after academician V.P. Glushko. Tel. (495)
286-92-54.
STUDY OF CAUSES OF DIVERGENCE OF PRESSURE CHARACTERISTICS OF OXIDIZER PUMP OF
LPRE OBTAINED AT AUTONOMOUS TESTS AND IN ENGINE COMPOSITION
Influence of various factors that could lead to discrepancies between left branches of pressure
characteristics of oxidizer pump is analyzed in paper. These characteristics are calculated by
parameters of RD-191 engine tests and by pump autonomous tests on water. Reason for discrepancy
of pressure characteristics is established: a large relative error of pressure sensors at deep throttling
modes of engine operation.
Key words: liquid propellant rocket engines, oxidizer pump, pressure characteristic, autonomous tests.
UDC 621.45:621.791.3
Dubrovsky Konstantin Evgenievich, cand. of techn. sciences.
Russia, Moscow region, Khimki, NPO Energomash named after academician V.P. Glushko. Tel. (495)
286-92-54.
ABOUT MECHANISM OF DEFORMATION OF RIBS OF WALLS IN WELD-BRAZED ELEMENTS OF
LPRE DESIGN
The paper covers problem of improving the quality of brazing of weld-brazed construction elements of
LPRE design. Problem of formation of dry joints is discussed. Calculated estimation in justification of
reasons of their formation is presented.
Key words: welded seam, brazed connection, dry joint, thermal elongation, voltage, plastic
deformation.
10
UDC 621.45:621.791:629.76
Polyansky Alexander Mikhailovich., cand. of techn. sciences.
Russia, Moscow region, Khimki, NPO Energomash named after academician V.P. Glushko. Tel. (495) 286-92-54.
Polyansky Vladislav Mikhailovich, doctor of techn. sciences.
Russia, Moscow, MSTU named after N.E.Bauman.
FRACTURE OF BRAZED JOINT AS INDICATOR OF QUALITY OF BRAZING CONNECTION
Evaluation technique of quality of brazing connections is substantiated experimentally. It includes determination
of tensile strength of joints and fractographic analysis of surface of fractures. Examples of application of such
technique for examination of brazing connections of assembly, received by capillary and contact-reactive brazing
are presented.
Key words: liquid propellant rocket engines, brazing connections, tensile strength of joints, fractographic
analysis.
UDC 621.45:629.76:620.49
Polyansky Alexander Mikhailovich., cand. of techn. sciences,
Milov Alexander Evgenievich, cand. of techn. sciences,
Romasenko Evgeny Nikolaevich, cand. of techn. sciences,
Golubkov Sergey Borisovich.
Russia, Moscow region, Khimki, NPO Energomash named after academician V.P. Glushko. Tel. (495) 286-92-54.
Polyansky Vladislav Mikhailovich, doctor of techn. sciences.
Russia, Moscow, MSTU named after N.E.Bauman.
PECULIARITIES OF GROWTH OF CRACKS IN PIPELINE OF UNLOADING OF FUEL BOOST PUMP UNIT OF
LPRE
Numerical calculation of stress-deformed state of pipeline under influence of internal pressure is conducted by
finite element method. Mechanism of growth of cracks is revealed and it is shown that high-level dynamic stress
11
is main cause of destruction. Such stress depends on internal pressure and value of ovality of pipe in pipeline
bends.
Key words: liquid propellant rocket engines, pipelines, mechanism of growth of cracks, finite element method.
UDC 621.45:629.76:620.19
Polyansky Alexander Mikhailovich., cand. of techn. sciences.
Russia, Moscow region, Khimki, NPO Energomash named after academician V.P. Glushko. Tel. (495) 286-92-54.
Polyansky Vladislav Mikhailovich, doctor of techn. sciences.
Russia, Moscow, MSTU named after N.E.Bauman.
ABOUT SUBCRITICAL GROWTH OF CRACKS IN CAST BRANCH PIPES FROM TITANIUM ALLOY VT-5L
Causes and mechanisms of formation of cracks in cast branch pipes from VT-5L alloy are studied. Fractographic
research of cracks surfaces reliefs is conducted, macro - and microstructure in areas of destruction is studied and
hydrogen content in castings is determined. Places of cracks origin and their further subcritical growth are
discovered. Microstructural aspects of origin and growth of cracks are discussed. Recommendations on ways to
prevent cracking of cast branch pipes are formulated.
Key words: liquid propellant rocket engines, cast branch pipes, titanium alloy, cracking, fractographic research.
UDC 621.45:621.175
Klyueva Olga Gennadievna, cand. of techn. sciences,
Kolymagin Alexander Nikolaevich, cand. of techn. sciences.
Russia, Moscow region, Khimki, NPO Energomash named after academician V.P. Glushko. Tel. (495) 286-92-54.
EVALUATION OF EFFECTIVENESS OF ADVANCED UNIT OF PRESSURIZATION IN LPRE COMPOSITION
12
Results of tests of two lamellar-ribbed improved units of pressurization in structure of oxygen-kerosene RD191
engines are presented. Estimation of effectiveness of their work in comparison with initial unit is conducted.
Verification of developed methods of thermal and hydraulic calculations by comparing the calculated and
experienced parameter values is performed. It is shown their suitability for practical use. Condition under which
advanced unit of pressurization meets to all requirements of technical specifications is formulated. Prospectivity
of its application in RD191engine instead of initial unit is substantiated.
Key words: liquid propellant rocket engine, unit of pressurization of propellant tanks, heat exchanger, heat
transfer.
UDC 547.211.621.455
Voronkov Alexander Fedorovich,
Grebenyuk Dmitriy Alekseevich,
Ivanov Vitaliy Aleksandrovich,
Klepikov Igor Alekseevich, doctor of techn. sciences,
Likhvantsev Anatoly Alekseevich.
Russia, Moscow region, Khimki, NPO Energomash named after academician V.P. Glushko. Tel. (495) 286-92-54.
OXYGEN-METHANE RD196 ENGINE FOR SYSTEM DEMONSTRATOR OF REUSABLE FIRST STAGE
OF MRKS-1
Main characteristics of RD196 engine with thrust about 50 tf are presented in paper. This engine is intended for
preliminary verification of basic problems of advanced reusable reentry rocket block at flight tests. Such development
of reusable space launch-vehicle is conducted by GKNPC named after M.V.Khrunichev in «MRKS-1» framework. The
basic results of preliminary engine design: schematics and features of its operation, main engine systems, as well as
brief description of engine design, terms and volumes of development tests are presented.
Keywords: reusable liquid propellant rocket engine, methane, fuel-rich preburner gas, advanced launch-vehicle, reentry
rocket block.
UDC 621.45:621.822+629.784
Romasenko Evgeny Nikolaevich, cand. of techn. sciences,
Sidorenko Alexander Sergeevich.
Russia, Moscow region, Khimki, NPO Energomash named after academician V.P. Glushko. Tel. (495)
286-92-54.
STAND TURBOPUMP UNIT FOR ACETAM SUPPLY
Design of stand turbopump unit for acetam supply in combustion chamber of stand demo-engine and
main issues, solved during its design are described in paper.
13
Key words: liquid propellant rocket engines, turbopump unit, design.
UDC 621.822
Sidorenko Alexander Sergeevich.
Russia, Moscow region, Khimki, NPO Energomash named after academician V.P. Glushko. Tel. (495)
286-92-54.
DEVELOPMENT OF HIGH-SPEED GEAR ASSEMBLY WITH PUMP FOR PORTABLE FIRE
INSTALLATION
The sequence of designing and development of high-speed gear assembly with pump for portable fire
installation is shown in paper. Features of its design are reviewed and results of experimental
researches are presented.
Keywords: fire installation, pump, gear assembly, design, experiments.
UDC 621.121:629.7.018:621.455
Kolymagin Alexander Nikolaevich, cand. of techn. sciences,
Medvedev Viktor Konstantinovich.
Russia, Moscow region, Khimki, NPO Energomash named after academician V.P. Glushko. Tel. (495)
286-92-54.
FEATURES OF MEASUREMENT OF PROPELLANT FLOWRATES
AT STAND FIRE TESTS OF LPRE
14
Problems of increase of accuracy of definition of mass flowrates of propellant by readings of turbine
gas meters with correction factors at fire tests of RD171M, RD180 and RD191 engines at test facility of
NPO Energomash are considered.
Key words: liquid propellant rocket engines, stand fire tests, measurement of propellant flowrates.
UDC 621.45:93
Sternin Leonid Evgenievich, doctor of phys-math. sciences.
Russia, Moscow region, Khimki, NPO Energomash named after academician V.P. Glushko. Tel. (495) 286-92-54.
V.P. GLUSHKO - FOUNDER OF GDL-OKB, PIONEER AND CREATOR OF DOMESTIC ROCKET
ENGINEERING
UDC 621.45:93
Starkov Vladimir Kirillovich, cand. of techn. sciences.
Russia, Moscow region, Khimki, NPO Energomash named after academician V.P. Glushko. Tel. (495)
286-92-54.
HOW VALENTIN PETROVICH HAS ESTABLISHED TERMINOLOGY OF LPRE
UDC 621.45:93
Rakhmanin Vyacheslav Fedorovich, cand. of techn. sciences,
Sudakov Vladimir Sergeevich.
15
Russia, Moscow region, Khimki, NPO Energomash named after academician V.P. Glushko. Tel. (495)
286-92-54.
ACADEMICIAN V.P.GLUSHKO AND IDEAS OF MODULARITY AT CREATION OF PROPULSION UNITS
OR LAUNCH-VEHICLES
Aspects of use of concept of modularity at creation of propulsion units or launch-vehicles in creation of
academician V.P.Glushko are considered.
Key words: liquid propellant rocket engine, propulsion unit, modularity, launch-vehicle.
UDC 621.45:93
Rakhmanin Vyacheslav Fedorovich, cand. of techn. sciences,
Sudakov Vladimir Sergeevich.
Russia, Moscow region, Khimki, NPO Energomash named after academician V.P. Glushko. Tel. (495)
286-92-54.
AT THE FOREFRONT OF ROCKET PROPULSION ENGINEERING
To 85-anniversary of JSC «NPO Energomash named after academician V.P. Glushko»
CONTENTS
FOREWORD
3
THERMO-HYDRO-GAS-DYNAMICS AND HEAT TRANSFER
ABOUT INFLUENCE OF NON-STATIONARY PROCESSES ON COMBUSTION EFFICIENCY IN
CHAMBER OF LPRE. A.S.Kiselev
ABOUT LIMITING POSSIBILITIES OF ISOBARIC AND ISOCHORIC THERMODYNAMIC
16
4
CYCLES AT THEIRS REALISATION IN LPRE. V.K.Chvanov, L.E.Sternin, T.N.Tomalintseva
18
THE CHOICE OF FUELS FOR OXYGEN-CONTAINING PROPELLANTS. V.K.Chvanov,
A.G.Milovanov, L.E.Sternin, T.N.Tomalintseva
25
SELECT OF CONTOUR OF SUPERSONIC PART OF A NOZZLE OF RD195 ENGINE CHAMBER.
A.S.Kiselev, V.K.Starkov
30
COMPARISON OF EFFECTIVENESS OF REDUCE OF HYDRODYNAMIC FRICTION OF
LIQUID HYDROCARBONS WITH ADDITIVES OF POLYISOBUTYLENE AND HIGHER
ALPHA-OLEFINS COPOLYMER. V.D.Gaponov, K.B.Konovalov
33
NUMERICAL MODELING OF SPATIALLY HOMOGENEOUS COMBUSTION OF METHANE IN
OXYGEN. B.P.Alexandrov
48
SIM UL A TI ON OF R E DU CT I ON OF UR AN I UM H E XAF L UO R ID E W I TH U S E OF
AT OMI C H YDR OG EN GE N E R AT OR . B. P. A L EX AN DROV, V. N. B EZ NOZ DR E V
64
TRANSIENT PROCESSES AND RELIABILITY
SUPPRESSION OF HIGH-FREQUENCY LONGITUDINAL INSTABILITY IN PREBURNERS OF LPRE BY
THROTTLING ORIFICES. A.P.Adjyan, I.M.Koshelev, P.S.Levochkin
83
WAYS OF SUPPRESSION OF LOW-FREQUENCY PULSATIONS IN LPRE AT MODES OF
DEEP THROTTLING. E.A.Gemranova, A.I.Kolbasenkov, I.M.Koshelev, P.S.Levochkin,
D.S.Martirosov
104
STUDY OF INFLUENCE OF GEOMETRICAL DEVIATIONS OF BLADES ON DYNAMIC
CHARACTERISTICS OF TURBINE ROTOR OF LPRE. A.N.Loshkarev, D.V.Merzlyakov.
111
DESIGN OF LPRE AND ITS UNITS
EXPERIMENTAL INVESTIGATION OF INFLUENCE OF LOCATION OF LASER FOCUSING AREA ON
IGNITION OF OXYGEN-KEROSENE PROPELLANT. E.A.Belov, A.N.Golikov, V.A.Golubev, D.I.Dubovik,
N.G.Ivanov, O.G.Klyueva, P.S.Levochkin, S.G.Rebrov, E.N.Romasenko
120
CAUSES AND MECHANISM OF FORMATION OF LOCAL BURN-THROUGH IN COOLED
WALLS OF COMBUSTION CHAMBERS. A.M.Polyansky, V.M.Polyansky, A.E.Milov
135
DEVELOPMENT AND APPLICATION OF HIGH-STRENGTH CASTING STEEL VNL-6 IN WELDED
STRUCTURES OF LPRE. V.I.Novikov
155
STUDY OF CAUSES OF DIVERGENCE OF PRESSURE CHARACTERISTICS OF OXIDIZER
PUMP OF LPRE OBTAINED AT AUTONOMOUS TESTS AND IN ENGINE COMPOSITION.
Y.I.Kanalin, N.B.Pudonina, A.S.Sidorenko, L.A.Tolstikov
163
ABOUT MECHANISM OF DEFORMATION OF RIBS OF WALLS IN WELD-BRAZED
ELEMENTS OF LPRE DESIGN. K.E.Dubrovsky
178
FRACTURE OF BRAZED JOINT AS INDICATOR OF QUALITY OF BRAZING CONNECTION.
A.M.Polyansky, V.M.Polyansky….………..
186
PECULIARITIES OF GROWTH OF CRACKS IN PIPELINE OF UNLOADING OF FUEL BOOST PUMP
UNIT OF LPRE. A.M.Polyansky. A.E.Milov, V.M.Polyansky, E.N.Romasenko, S.B.Golubkov
199
17
ABOUT SUBCRITICAL GROWTH OF CRACKS IN CAST BRANCH PIPES FROM TITANIUM ALLOY VT5L. A.M.Polyansky, V.M.Polyansky
214
EVALUATION OF EFFECTIVENESS OF ADVANCED UNIT OF PRESSURIZATION IN LPRE
COMPOSITION. O.G.Klyueva, A.N.Kolymagin
227
OXYGEN-METHANE RD196 ENGINE FOR SYSTEM DEMONSTRATOR OF REUSABLE FIRST
STAGE OF MRKS-1. A.F.Voronkov, D.A.Grebenyuk, V.A.Ivanov, I.A.Klepikov, A.A.Likhvantsev
STAND
TURBOPUMP
E.N.Romasenko, A.S.Sidorenko….
UNIT
FOR
ACETAM
243
SUPPLY.
DEVELOPMENT OF HIGH-SPEED GEAR ASSEMBLY WITH PUMP FOR PORTABLE FIRE
INSTALLATION. A.S.Sidorenko
260
276
TEST AND MEASURING
FEATURES OF MEASUREMENT OF PROPELLANT FLOWRATES AT STAND FIRE TESTS OF
298
LPRE. A.N.Kolymagin, V.K.Medvedev
HISTORY QUESTIONS
V.P. GLUSHKO - FOUNDER OF GDL-OKB, PIONEER AND CREATOR OF DOMESTIC ROCKET
ENGINEERING. L.E.Sternin.
316
HOW VALENTIN PETROVICH HAS ESTABLISHED TERMINOLOGY OF LPRE. V.K.Starkov
359
ACADEMICIAN V.P.GLUSHKO AND IDEAS OF MODULARITY AT CREATION OF
PROPULSION UNITS OR LAUNCH-VEHICLES. V.F.Rakhmanin, V.S.Sudakov
368
AT THE FOREFRONT OF ROCKET PROPULSION ENGINEERING. To 85-anniversary of JSC
375
«NPO Energomash named after academician V.P.Glushko». V.F.Rakhmanin, V.S.Sudakov
Contents
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