Calculation analysis of zonal and local resulting heat transfer in combustion chamber of tube furnaces

Проведено численное исследование нестационарного турбулентного сверхзвукового течения в камере сгорания прямоточного воздушно-реактивного двигателя. Описана методика экспериментального измерения температуры на стенке осесимметричного канала в камере сгорания двигателя. Математическое моделирование обтекания исследуемой модели двигателя проводилось для скоростей набегающего потока M = 5 ... 7. Начальные и граничные условия задачи соответствовали реальному аэродинамическому эксперименту. Проанализированы результаты численного расчета. Рассмотрено изменение распределения температуры вдоль стенки канала с течением времени. Проведена оценка согласованности полученных экспериментальных данных с результатами математического моделирования. Purpose. The aim of this study is a numerical simulation of unsteady supersonic gas flow in a working path of ramjet engine under conditions identical to aerodynamic tests. Free stream velocity corresponding to Mach numbers M=5 ... 7 are considered. Methodology. Presented study addresses the methods of physical and numerical simulation. The probing device for thermometric that allows to recording the temperature values along the wall of internal duct was proposed. To describe the motion of a viscous heat-conducting gas the unsteady Reynolds averaged Navier - Stokes equations are considered. The flow turbulence is accounted by the modified SST model. The problem was solved in ANSYS Fluent using finite-volume method. The initial and boundary conditions for unsteady calculation are set according to conditions of real aerodynamic tests. The coupled heat transfer for supersonic flow and elements of ramjet engine model are realized by setting of thermophysical properties of materials. The reliability testing of numerical simulation has been made to compare the results of calculations and the data of thermometric experimental tests. Findings. Numerical simulation of aerodynamic tests for ramjet engine was carried out. The agreement between the results of numerical calculations and experimental measurements for the velocity in the channel under consideration was obtained; the error was shown to be 2%. The temperature values were obtained in the area of contact of the supersonic flow with the surface of the measuring device for the external incident flow velocities for Mach numbers M = 5 ... 7. The process of heating the material in the channel that simulated the section of the engine combustion chamber was analyzed. The temperature distribution was studied depending on the position of the material layer under consideration relative to the contact zone with the flow. Value. In the course of the work, the fields of flow around the model of a ramjet engine were obtained, including the region of supersonic flow in the inner part of axisymmetric channel. The analysis of the temperature fields showed that to improve the quality of the results, it is necessary to take into account the depth of the calorimetric sensor. The obtained results will be used to estimate the time of interaction of the supersonic flow with the fuel surface required to reach the combustion temperature.

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Numerical Simulation of Convective Heat Transfer in a Spark Ignition Engine

ASME 2008 Internal Combustion Engine Division Spring Technical Conference ◽

10.1115/ices2008-1687 ◽

2008 ◽

Cited By ~ 1

Author(s):

Arash Mohammadi ◽

Seyed Ali Jazayeri ◽

Masoud Ziabasharhagh

Keyword(s):

Heat Transfer ◽

Heat Flux ◽

Heat Transfer Coefficient ◽

Transfer Coefficient ◽

Combustion Chamber ◽

Spark Ignition Engine ◽

Cylinder Wall ◽

Single Cylinder Engine ◽

Crank Angle ◽

Exhaust Valves

A computational fluid dynamics code is applied to simulate fluid flow and combustion in a four-stroke single cylinder engine with flat combustion chamber geometry. Heat flux and heat transfer coefficient on the cylinder head, cylinder wall, piston, intake and exhaust valves are determined. Result for a certain condition is compared for total heat transfer coefficient of the cylinder engine with available correlation proposed by experimental measurement in the literature and close agreement is observed. It is observed that the value of heat flux and heat transfer coefficient varies considerably in different positions of the combustion chamber, but the trend with crank angle is almost the same.

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Heat transfer in a rocket engine combustion chamber while geometry changing of the channel-slot solid fuel charge

Trudy MAI ◽

10.34759/trd-2020-111-5 ◽

2020 ◽

pp. 5-5

Author(s):

Boris Benderskyi ◽

Alena Chernova

Keyword(s):

Heat Transfer ◽

Combustion Chamber ◽

Solid Fuel ◽

Rocket Engine ◽

Fuel Charge ◽

Engine Combustion

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Local Heat Transfer in the Combustion Chamber of a Hydrogen Diesel

Russian Engineering Research ◽

10.3103/s1068798x19100137 ◽

2019 ◽

Vol 39 (10) ◽

pp. 831-836

Author(s):

R. Z. Kavtaradze ◽

T. M. Natriashvili ◽

M. G. Glonti ◽

Yichun Wang ◽

G. Zh. Sakhvadze

Keyword(s):

Heat Transfer ◽

Combustion Chamber ◽

Local Heat Transfer ◽

Local Heat

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3D modeling of the aerodynamics and heat transfer in the combustion chamber of the BKZ-75 boiler of the Shakhtinsk cogeneration plant

Thermophysics and Aeromechanics ◽

10.1134/s0869864319020124 ◽

2019 ◽

Vol 26 (2) ◽

pp. 295-311 ◽

Cited By ~ 2

Author(s):

A. S. Askarova ◽

S. A. Bolegenova ◽

V. Yu. Maximov ◽

M. T. Beketaeva

Keyword(s):

Heat Transfer ◽

Combustion Chamber ◽

3D Modeling ◽

Cogeneration Plant

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Heat Transfer Analysis in a Modern DLN Combustor

Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration ◽

10.1115/2000-gt-0254 ◽

2000 ◽

Cited By ~ 3

Author(s):

Giovanni Ferrara ◽

Luca Innocenti ◽

Giacomo Migliorini ◽

Bruno Facchini ◽

Anthony J. Dean

Keyword(s):

Heat Transfer ◽

Combustion Chamber ◽

Film Cooling ◽

Thermal Flux ◽

Calculation Model ◽

Heat Transfer Analysis ◽

Turbine Blade Cooling ◽

Air Flows ◽

Critical Components ◽

Cooling Air

The increasingly stringent emissions standards in recent years have mandated low gas turbine emissions and thus changed the approach to combustion chamber design. In particular, lean burners based on highly premixed fuel-air flows have become more important. These combustors, termed Dry Low NOx (DLN), can now achieve emissions of 25 ppm and below in commercial operation. This development together with the inlet turbine temperature increase has resulted in less cooling air for combustion chambers and turbine blade cooling systems. The designer now needs to optimise cooling air flows that control the wall temperature of the components that confine the hot gases. Moreover, much of the air coming from the compressor is used to premix the fuel and only a smaller fraction is now available for cooling processes. In annular combustor configurations the air available for cooling the combustion chamber walls sometimes also has to cool the first stage nozzle. So the pressure loss along the combustor cooling passages has to be limited in order to assure a suitable supply pressure for these downstream cooling passages. We analysed the cooling air flow around the liner of an annular combustion chamber and we investigated the thermal flux and friction losses. In this paper we show the development of a calculation model that allows the critical components heat transfer analysis of a typical annular combustion chamber. The code developed is based on the generalised 1–D flow treatment. We have used experimental correlations for convection, film cooling and impingement borrowed from works found in literature. The code is provided with a graphical interface that helps the user during the calculation. This code was used in practical application to optimize the PGT5B combustion chamber cooling.

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