Vol 12, No 3-2 (2013): Vestnik SSAU

Full Issue

Results of primary operation of NK-37 engine low emission combustion system
Bantikov D.Y., Yeliseev Y.S., Lavrov V.N., Pchelyakov A.A., Fedorchenko D.G., Tsybizov Y.I.
Abstract

The article deals with the results of primary operation of the NK-37 engine low emission combustion system. "KUZNETSOV" company has developed a low emission combustion system, including a double-circuit fuel burner, a traditional type annular combustion chamber and a multistage automatic fuel feeding system, according to the mode of engine operation and ambient conditions. The results of a long- period primary operation of the combustion system incorporated in the NK-37 engine are given in the article.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):9-14
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Defects of shrouded blade platforms of high-temperature gas turbines
Belousov A.I., Nazdrachyov S.V.
Abstract

The article describes the defects of airfoil shroud platforms of the high pressure turbine of an NK-36ST engine for ground application and shows corrective actions for defect elimination. The structure of a light airfoil shroud platform that can increase the blade lifetime is introduced. 

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):15-21
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Forecasting the individual performance capabilities of the rocket engine powerplant units at the maintanance stage
Biryuk V.V., Bronshtein V.M., Presnyakova A.S., Shatilova M.Y., Dostovalova S.S.
Abstract

This paper describes a methodology of calculation of the required performance capabilities of rocket engine power plant units.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):22-24
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Thermodynamic calculation of a thermomechanical compressor
Blagin E.V., Dovgyallo A.I., Uglanov D.A., Dostovalova S.S.
Abstract

This article presents an analysis of the work processes in a thermomechanical compressor. Design data on changes in gas pressure and mass in the compressor are given and its efficiency is calculated.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):25-30
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Method of calculating GTE gas-thermodynamic parameters with blade row description of an axial multistage compressor
Boyko L.G., Karpenko E.L., Akhtemenko U.F.
Abstract

A method of calculating the operating performance of a turboshaft gas turbine engine for steady- state conditions has been developed based on a mathematical model with a row- after- row presentation of a multistage axial compressor. This method as opposed to the existing ones makes it possible to determine gas turbine engine gas-thermodynamic parameters at different ratings taking into account such factors as air bleeding and blow off directly from the air-gas channel, the variation of geometrical parameters of compressor blade rows and meridian bypasses and changes in the programme of regulating variable stator vanes. The results of investigating the thermodynamic parameters of the main units, their elements and performance characteristics of a turboshaft gas turbine engine are presented for a wide range of rotor speeds (throttle performance).  Comparisons between the computational results and the experimental data are made, their agreement is shown to be satisfactory.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):31-39
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Dynamic method of investigating stress concentrators of the YMZ-238 engine crankshaft considering surface hardening plastic deformation
Bukaty A.S., Kostichev V.E., Deniskina E.A.
Abstract

The article presents an approach to analyzing the stress-strain state of the YMZ-238 crankshaft after surface roller hardening. The approach is based on dynamic modeling of the stress-strain state of the crankshaft stress concentrators. The real-time modeling of roller hardening makes it possible to get a diagram of residual stresses occurring in the strengthened surface layer of the fillets. The next step is the analysis of the part’s stress-strain state applying the boundary conditions corresponding to the operating conditions of the engine. The dynamic research of the stress-strain state of the crankshaft makes it possible to analyze the manufacturing technology and identify the origin of cracks in stress concentrators taking into account the improvement of fatigue resistance resulting from hardening treatment.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):40-45
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Analysis of stress distribution in the dangerous section area of specimens with fillets under bending using the finite-element modeling method
Vakuljuk V.S.
Abstract

The results of testing specimens with the diameter of 12 mm made of steel 20 with fillets of various radii (0,5 mm, 1 mm, 3 mm and 5 mm) both non-hardened and hardened by peening have been analyzed by the finite- element modeling method. It is experimentally established that the fillet radius increase results in the dangerous section moving to the specimen’ smallest section and reaching it at the extreme. This fact is confirmed by thecalculation method. The dependences of the stress concentration coefficient in the dangerous section area of cylindrical specimens with fillets of various radii under bending regularities have been obtained out by the finite- element modeling method.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):46-50
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Development of pneumatic- type starting nozzles for a full-scale low emission combustion chamber
Vasilyev A.J., Blumkin P.I., Chelebyan O.G.
Abstract

To provide stable operation and confident firing up in the main combustion chamber of a gas turbine engine under high-altitude flight conditions a new scheme of a pneumatic- type starting nozzle is developed. The firing tests carried out in a full-scale low-emission combustion chamber showed their principal fitness for work. The results of the experimental study of two versions of starting nozzles for the purpose of determining  comparative starting and stalling characteristics at different heights are presented in the paper.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):51-56
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Peculiarities of application of biofuel mixture in combustion chambers of modern gas turbine engines
Vasilyev A.J., Medvedev R.S., Chelebyan O.G.
Abstract

An experimental study of combustion processes occurring during the combustion of both standard aviation fuel and alternative fuels (biofuels) is carried out. The range of steady-state combustion in the compartment of a chamber working on fossil fuel as well as on biofuel and ethanol is investigated. As a result, the scheme has shown its combustion efficiency, and the results have provided the necessary conditions for the solution of practical engineering problems.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):57-62
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Numerical simulation of the working process in a vortex tube with an additional stream
Vasilyuk O.V., Piralishvili S.A., Shaykina A.A.
Abstract

The paper presents a  numerical solution of full Navier-Stokes equations for an intensively swirling flow in  an axisymmetric channel disc-loaded in the input cross-section and supplied with a throttle of the peripheral slot type at the opposite end of the channel with a central hole for feeding additional masses of gas. The flow patterns, thermodynamic parameter distribution fields are obtained. The results of numerical computation are compared to the experimental data for vortex tubes with an additional stream. Formation of large-scale vortex structures is noted. The results of numerical calculation and computer visualization can be used to further refine the physical model and methodology for calculating characteristics of vortex tubes.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):63-72
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Aerodynamic improvement of GTE compressors by space profiling of blade vanes
Gerasimenko V.P., Shelkovsky M.Y.
Abstract

The optimum spatial profiling of blade vanes of GTE compressor stages is considered on the basis of calculation of a three-dimensional viscid stream. The simultaneous varying of geometrical parameters of blades and blade cascades in their profiling substantially accelerates the procedure of parametric optimization. As an integral criterion of minimization of different types of hydraulic losses the efficiency of compressor stages is used. The coefficient of hydraulic resistance is shown to decrease as compared to the initial vane, in a wide range of incidence angles, as a result of experimental research of the optimized output straight vane cascade of a stationary GTE compressor.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):73-79
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Thermal state of combustor can elements
Grechishnikov O.V., Ostapets I.I., Roslyakov A.D., Tsybizov Y.I.
Abstract

Materials for providing the thermal state of the elements of a two-staged gas turbine combustion chamber for terrestrial applications are presented. The factors that affect the temperature of combustor can rings are analyzed. A significant influence of flow characteristics and range of burners in the main loop on the combustor can wall temperature is shown and it is also shown that the task of ensuring acceptable combustor can wall temperature in accordance with the TOR is reduced, first of all, to the task of providing an optimum structure of the flow of fluid in the inner cavity of the combustor can.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):80-87
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Optimal distribution of turboprop engine free energy between the screw and the jet with mass characteristics taken into account
Grigoriev V.A., Prokaev A.S.
Abstract

The paper presents an analysis of research in optimal distribution of the airscrew thrust and the jet thrust of the turboprop engine. A conclusion is made as to the necessity of evaluating the efficiency of the power plant being a part of the aircraft.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):88-92
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Quasi one-dimensional model and calculation of processes in gas turbineengine combustion chambers given the heterogeneity of the combustible mixture, changes in mass, composition, temperature and stirring efficiency of the working body
Didenko A.A., Sokolov A.B.
Abstract

The methodology of one- dimensional calculation of the combustion chamber existing  at SSAU has been significantly complemented: a) the uneven distribution of fuel in the combustion zone and its combustion in the range of excess air ratio 0.55 ... 1.65 has been taken into account; b) the amount of vaporized fuel at each site is determined by considering the size of evaporating droplets; c) for each fraction of the fuel burnt  the equilibrium composition and the adiabatic equilibrium flame temperature is determined; d) a scheme of mixing the combustion products with the secondary combustion air and mixing air is proposed in order to evaluate the non-uniformity of the temperature of exhaust gas at the output of the combustor; e) a mixing quality factor is introduced. The impact of the completeness of mixing, composition and temperature of the gas on the quantity of nitrogen oxides along the length of the flame tube, the NO emission index  and the non-uniformity of the temperature field in the output section is assessed. The updated method of calculation is illustrated by the low- emission aviation turbine engine combustor.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):93-106
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Increasing the overall performance of a two-stroke engine with spark ignition by fuel injection
Dovgyallo A.I., Krasheninnikov S.V., Shchepetov D.A.
Abstract

The paper deals with the problems of organizing the process of gas mixing in two-stroke internal combustion engines with spark ignition and crankcase scavenging. Fuel injection into the intake manifold is chosen as the most effective way of mixing from the point of view of the authors. The increase of overall performance of a two-stroke internal combustion engine is estimated. The principle of operation of the system and the experimental installation are described.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):107-112
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Peculiarities of heat transfer in thermoacoustic converters
Dovgyallo A.I., Nekrasova S.O.
Abstract

The problems of heat transfer in thermoacoustic converters are discussed in the framework of analysis of studies of heat exchangers of thermoacoustic converters with a view of summarizing the concepts of physical processes of heat transfer in parameters of the theory of heat transfer, fluid dynamics and wave theory.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):113-121
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Evaluation of internal combustion engine cycle work using an ionic current sensor
Ivashin P.V., Ramazanov M.P., Tverdokhlebov A.Y., Shaikin A.P., Yasnikov I.S.
Abstract

The interrelation between the electrical conductivity of flame and the internal combustion engine cycle work is found experimentally with the aid of an ionic current sensor installed in a spark ignition internal combustion engine combustion chamber. It is shown that only one ionization cycle is needed for the analysis of combustion process parameters in a spark ignition internal combustion engine.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):122-127
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Mixture modelling in a swirle flow in the ANSYS CFX program
Krasheninnikov S.V., Savchenko O.V.
Abstract

The paper presents design research of mixing real gas in swirl flows of swirl burners of gas turbine engine combustion chambers in the ANSYS CFX program. The peculiarities of heat exchange of a swirl flow with the environment and the zone of reverse currents are investigated. The results of the numerical research and the previous physical experiment are shown to be in good qualitative and quantitative agreement.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):128-132
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Adhesion strength of heat-insulating and wear-resistant ceramic coatings on aluminum alloys
Krishtal M.M., Ivashin P.V., Polunin A.V., Pavlov D.A., Nikerov K.N.
Abstract

The paper presents a review of research devoted to the determination of adhesion strength and tendency to cleavage of a wear-resistant heat-insulating layer on aluminum-silicon alloys strengthened by the microarc oxidation method. The possibility of using the microarc oxidation technology for the strengthening of parts made of aluminum-silicon alloys operating under high-temperature conditions and significant thermal deformations in power plant engineering. 

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):133-138
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Automated generation of structural members of a spacecraft thermal model
Kulikov D.S., Shatin A.A., Velmisov I.G.
Abstract

The paper presents software for the calculation of temperature conditions of spacecraft, its advantages and disadvantages are discussed. The main idea is using combined software for the generation of structural members of a spacecraft thermal model taking into account the labor input of constructing such a model.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):139-142
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3d calculation of a multiport low-emission combustor cooling system
Moreva I.S., Vasilyuk D.K., Kirichenko R.Y.
Abstract

The results of calculating coupled heat transfer for four versions of a multiport flame tube are presented. The walls of the tube of an experimental combustion chamber have a double segment structure with an impact-convective cooling system. The calculations were made taking into account the combustion and the influence of radiant fluxes. The thermal state of the flame tube walls determined by the results of a numerical experiment is compared with the data of full-level tests of the combustion chamber as a part of a gas generator of an engine. Recommendations are given concerning the modernization of the flame tube structure in order to improve the thermal state of its segments.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):143-151
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Evaluation of the possibility of using combustion promoters in hydrocarbon fuels for perspective jet engines
Petrukhin N.V., Sergeev S.M., Prokopenko O.A., Grek M.O.
Abstract

The article presents the analysis of published data and results of experimental studies performed by the authors regarding the effect of combustion promoters – peroxides and hydro-peroxides on the turbulent burning rate of fuel TS-1. It was determined that the specific pulse thrust of the model pulse-detonating engine may be increased by 2.5 - 3.0 times. The same goes for the degree and burning rate of the fuel-air mixture. The authors explain the mechanism of action of promoters for increasing the activity of the fuel-air mixture in the process of combustion.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):152-157
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Influence of energy separation and vortex tube geometry on the flow turbulence
Piralishvili S.A.
Abstract

The paper outlines the interconnection between the characteristics of energy separation and the turbulence of the vortex flow based on the geometrical characteristics of the vortex tube (such as length, diameter, etc.). The calculated data are compared with the experimental results.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):158-164
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Emission characteristics and temperature non-uniformity at the outlet of the gas turbine engine combustion chamber
Sabirzyanov A.N., Yavkin V.B., Alexandrov Y.B., Markushin A.N., Baklanov A.V.
Abstract

Emission characteristics and temperature non-uniformity at the outlet of a gas turbine engine combustion chamber were simulated in bench test conditions. Simulation results were compared with the experimental data. The adequacy of the applicability of the turbulence and combustion models was investigated. The influence of the deformation intensity of the flame source in the combustion model and the constant swirl in the RNG k-e turbulence model on the distribution of parameters inside the combustion chamber and the emission characteristics is shown. Good agreement of the simulation results and the experimental data is obtained.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):165-172
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Analysis and ballistic design of a medium-caliber system with an attached camera of accelerating
Safronov A.I., Azovsky V.M., Zorkin V.A., Chirkunova N.V.
Abstract

The paper presents the results of investigating the temperature dependences of the velocities of launching a ballistic system of the SАC scheme based on the model of mechanics of heterogeneous media.The scheme proposed is shown to provide stable system operation in the temperature range from 40 ° to -40 ° C. 

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):173-180
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Approaches to the evaluation of fuels for hypersonic engines
Sergeev S.M., Petrukhin N.V.
Abstract

The article presents gas flow parameters in four cross- sections of the engine at the flight speed of 8M at the altitude of 20 km for various hydrocarbon fuels. The data were obtained with the use of a multi-purpose program complex. The analysis of the obtained results allowed determining the level of requirements for the basic properties of fuels for hyper-sonic ramjet engines and arguments in favour of developing a new fuel for hypersonic ram-flow jet engines as well as new methods for its evaluation.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):181-184
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Research and optimization of parameters of a system controlling the process of tube inside surface coating
Skvortsov B.V., Zaretskaya M.I., Kurylyova P.A.
Abstract

The paper presents the results of research of a system controlling the process of tube inside surface coating using computer simulation. The parameters of the elements are optimized in order to provide the highest quality of the coating applied along the tube. The computer model is complemented by units that make the results of the simulation close to the experimental results.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):185-191
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Using heat pipes to improve the efficiency of gas-dynamic thermal stratification
Tsynaeva A.A., Tsynaeva E.A., Shkolin E.V.
Abstract

A numerical solution of differential equations describing the motion and heat exchange in the boundary layer is used to simulate heat transfer in a tube of thermal stratification. The numerical solution proves that the use of heat pipes will make it possible to increase the efficiency of a tube of thermal stratification.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2013;12(3-2):192-197
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