Vol 1, No 2 (2002): Special Issue

Full Issue

Investigation of fuel spraying and mixing in the head of nk-type engine combustor
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Abstract

Characteristics of air flow and fuel spray as they leave the frontal device (module) of NK-type engine combustor are determined experimentally. On the basis of these characteristics a conclusion is made about the optimal setting of fuel collectors to obtain the best fuel spraying in the low gas mode.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2002;1(2):10-14
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Experimental determination of characteristics of pneumatic atomizers and their correlation with calculation results
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Abstract

Results of experimental investigations and calculations of jet emulsion and pneumatic atomizers for spraying aviation fuels are surveyed. On the basis of the data obtained atomizers using various sources of spraying high- and lowpressure air were designed and tested. A new optical express-method to investigate fuel-air mixture spray is proposed. The results are compared with those of calculations.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2002;1(2):15-20
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Peculiarities of converting speed-boosted combustion chamber operating on natural gas
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Abstract

The paper presents the results of experimental research into the peculiarities of the combustion process in a highly speed-boosted combustor when it starts to work on natural gas. Ways of updating the basic combustor design ensuring the required level of characteristics and NOx concentration without previously stirring the air-fuel mixture have been determined.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2002;1(2):21-26
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Influence of initial turbulence of aluminum-air mixture flow on ignition and flame stabilization processes
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Abstract

The influence of initial turbulence of aluminum-air mixture flow on ignition and flame stabilization processes in a ramjet combustion chamber with an abrupt expansion has been investigated. Experimental data have been received and the influence of initial turbulence of aluminum-air mixture flow on the stabilizer on the ignition, temperature and flame failure boundaries has been defined depending on the size of aluminum particles.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2002;1(2):27-32
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Method of controlling burning processes in a pseudo-liquid fuel flow
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Abstract

Method of controlling burning and flame stabilization processes in a pseudo-liquid fuel flow has been developed. The method is based on imposing pseudoturbulent pulsations on discrete air jets injected into the mixing layer of the main fuel-air flow. By varying speed and frequency of pulsating jets it is possible to change the hydrodynamics and scale of flow structure in the chamber and, consequently, to influence the pseudo-liquid fuel burning characteristics.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2002;1(2):33-39
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“Rich burn - quick quench - lean burn” technology (RQQL) for aviation gas turbine engine working on liquid natural gas
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Abstract

The paper reports some results of Research and Development Department of the Joint-Stock Company «Aviadvigatel» (the city of Perm) as to the mastering of RQQL low-emission burning (Rich Burn-Quick Quench-Lean Burn) as applied to the gas turbine engine PS-90A combustion chamber. Data on NOx and CO emission for combustion chambers operating on aviation kerosene and liquid natural gas are presented. It is noted, in particular, that using RQQL burning technology makes it possible to obtain 4- or 5-fold NOx emission decrease as compared to the existing PS-90A combustion chamber. The paper also notes some problems concerning reliable start and steady burning in the RQQLtype combustion chamber when using natural gas as fuel.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2002;1(2):40-45
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RQQL low emission combustion process as a way of achieving high reliability of stationary gas turbine engine
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Abstract

The article covers the process of low emission combustion “Rich Burn - Quick Quench - Lean Burn” that is applied to settle functional problems typical for engines equipped with combustors with lean premixed fuel/air mixtures. The article shows that RQQL process with NOx = 150…100 mg/nm3 is more preferable compared to the process of lean premixed fuel/air mixtures burning.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2002;1(2):46-51
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Developing a dynamic model of premixed fuel combustor
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Abstract

The choice of optimal parameters of a burner mixer of a combustor with pre-prepared fuel-air mixture is considered. Requirements for providing the standard level of Nox emission and for pressure pulsation amplitude in the combustor on the basis of the elaborated dynamic model of the operating process in a combustor of this type are taken into consideration. The use of this approach to design a low-emission combustor of the gas-pumping unit GTK-10I (Flame 3) is discussed.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2002;1(2):52-59
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Using computational gas dynamics methods for the simulation of multicomponent gas flow, combustion and heat exchange in a gas turbine combustion chamber
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Abstract

The problem of mathematical simulation of physical and chemical processes in a gas turbine combustion chamber is considered. The results of numerical simulation of a gas mixture turbulent flow and combustion in a methane-fuelled combustor are presented. The simulation of multicomponent turbulent gas flow processes was performed using averaged Navier-Stokes equations, k − ε turbulence model. Thin flame front model and Zeldovitch mechanism are used to describe the combustion process. Using these models made it possible to assess the NO emission level at the combustor outlet.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2002;1(2):60-64
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Experience of design and lines of further improvement of gas turbine engine low-emission combustion chambers
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Abstract

On the basis of the experience gained by N. D. Kuznetsov Scientific and Technical Complex in Samara in the area of design and development of low toxic combustion chambers the paper presents the results of analyzing the main reasons that restrain further pollution reduction of combustion chambers for gas turbine engines and power plants. We suggest taking into consideration actual possibilities of reducing toxic exhaust when choosing thermodynamic parameters of a newly designed engine.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2002;1(2):65-70
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Influence of interphase exchange on fuel-air mixing in a module combustor
1 1., 1 1., 1 1.
Abstract

A mathematical model of a two-phase flow in a gas turbine combustion chamber has been developed. The model includes momentum and heat exchange between the gas and fuel drops. Model flow in a straight channel of rectangular cross section with fuel aerosol injection from the wall has been calculated. Heat exchange between the gas and the drops is shown to have a strong influence on temperature fields when air flows of different densities are mixed.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2002;1(2):71-75
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Low-emission characteristics and reliability of gas turbine engine combustion chamber and peculiarities of their provision
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Abstract
The paper discusses the peculiarities of the methodology of improving ecological and reliability characteristics of gas turbine combustion chambers. Methods of developing combustion chamber elements using pneumatic- and hydromodels as well as full-scale combustion chambers are described.
VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2002;1(2):76-80
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Experimental and computational research of thermal and stressed state on a liner perforated wall with various injection angle and hole spacing
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Abstract

Experimental research of heat exchange on a perforated wall with standard and inclined holes, around which a turbulent flow of heated gas is flowing, has been carried out, using thermovision equipment. The results of the experiments made it possible to deduce the formulas for calculating heat exchange between the wall and the gas flow, as well as that between the wall and the cooling air, including the holes in the wall.
Three – dimensional calculations of thermal and stressed states of perforated walls with inclined holes in a twowall liner have been made for take-off regime.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2002;1(2):81-87
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Afterburning of toxic components of eic burnt gases
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Abstract

Various devices and methods of ignition and afterburning of toxic components contained in EIC burnt gases are considered as an alternative to catalytic neutralizers. Experimental investigations have been carried out on the laboratory stand with the VAZ-1111 “Oka” engine. Efficiency of introducing additional air and (or) oxygen into the burnt gases is shown.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2002;1(2):88-91
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Defining combustor gas flow turbulence parameters on the basis of integration and transformations of Reynolds AND Navier-Stokes equations
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Abstract

By transforming the Reynolds and Navier-Stokes equations into the integral form a criterion function was obtained. The function was confirmed by experimental data. It relates the continuous flow turbulence parameters to hydrodynamic criteria and the parameters characterizing the channel variable geometry as the flow travels in the channel.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2002;1(2):92-96
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Summarizing the experience of turbulent combustion in aircraft engine and industrial gas turbine combustion chambers
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Abstract

The paper presents the results of investigating the influence of turbulent mixing process intensification upon the efficiency, combustion stability and harmful emissions in combustion chambers (CC) of NK-family aircraft engines and industrial gas turbines. In the course of CC development relationship between “soft” and “hard” excitation of highfrequency (HF) vibrations in thrust chambers of closed-circuit liquid-propellant rocket engines (NK-39, NK-33) and
non-uniformity of gaslous component flow across the CC cross-section, as well as the range of injector jet action were obtained. On the basis of investigating the sources of turbulence in CC two models of flow turbulization hare been developed: “R” model for areas of injector head reverse flows; and “C” model for injector jets caused by dynamic interaction of fuel components, due to initial flow turbulization in the CC gas passage, as the flow enters the injector gas
channels etc. application of “R” and “C” models for Hersch criterion improvement made it possible to create models of acoustic energy generation in CC and to prove experimentally the developed principles of optimizing the above-mentioned combustion characteristics for NK-25, NK-321 engine afterburners and for two-zone CC of NK-36ST, NK-37, NK-38ST engines.

VESTNIK of Samara University. Aerospace and Mechanical Engineering. 2002;1(2):97-111
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