Computational study of compressor operation mode effect on gas turbine engine combustion chamber processes

Aeronautical and Space-Rocket Engineering

Thermal engines, electric propulsion and power plants for flying vehicles


Orlov M. Y.*, Anisimov V. M.**

Samara National Research University named after Academician S.P. Korolev, 34, Moskovskoye shosse, Samara, 443086, Russia



Improvement of modern GTE and power plants directly related to improvement of the combustion chamber. However, combustion chamber is one of the most problematic parts in terms of the design and finishing-out. To solve these problems the authors developed the technique for performing common computations of the compressor and combustion chamber together. In the framework of this work this method was used studying the effect of flow unevenness, occurring behind the compressor blades, and on combustion chamber workflow.

The method has been further developed in the way of implementation of common mesh model for the compressor, the combustor, and working out the boundary conditions setting principles. Geometrical model consists of four different geometrical volumes: guide vanes of the penultimate stage of high-pressure compressor, the impeller and guide vanes of the last stage and the flow path of combustion chamber. The sector of compressor and combustor was used instead of full-sized model to reduce calculation time. The sector angle kept constant for compressor and combustor.

Three-dimensional modeling software package Ansys Fluent was used for simulation of common operation of compressor and combustion chamber, since the combustion processes simulation was tested and verified for this package. Mathematical model and boundary conditions were set after mesh generation. Mathematical model included different calculative models, which were necessary for the combustion simulation. Boundary conditions were specified by temperature and pressure of the flow at the inlet and of the fuel. The flow blows the guide vanes at a certain angle. Hence, the direction vectors were set in cylindrical coordinates. The simulation was carried out in non-stationary arrangement. Thus, the certain time step and number of time steps, which are necessary for convergence, were set. The simulations were carried out for three engine operation modes (nominal, 0.7 of nominal and 0.5 of nominal regimes) with and without compressor. The least effect of the compressor detected at the the engine nominal mode, and the the largest was detected at 0.5 of the nominal. The obtained results were compared with the results from simulation without compressor.

Simulations revealed that that blade wakes extend up to the flame tube head. These wakes change the flame tongue, pressure field, temperature and velocity in the recirculation-mixing zone. It can affect combustion efficiency, ecological performance and temperature field at the combustor outlet. Thus, the simulations, which accounted for combustion chamber and compressor, more fully represent the characteristics of the working process of the combustion chamber and increase the efficiency of new products design.


combustion chamber, compressor, guide vane, impeller, blade wakes, emission, computer simulation


  1. Matveev S.G., Orlov M.Yu., Matveev S.S., Zinkovskii V.S., Krivtsov A.V. Vestnik Samarskogo gosudarstvennogo aerokosmicheskogo universiteta, 2012, no. 3(34), part 3, pp. 293-298.

  2. Matveev S.G., Orlov M.Yu., Zubrilin I.A., Matveev S.S., Tsibizov Yu.I. Numerical investigation of the influence of flow parameters nonuniformity at the diffuser inlet on characteristics of the GTE annular combustion chamber. Proceedings of ASME Turbo Expo 2015: Turbine Technical Conference and Exposition, 2015, pp. 1-7.

  3. Orlov M.Yu., Matveev S.S. Numerical simulation of an influence of a compressor and a turbine on characteristics of a combustion chamber of a small-sizes gas turbine engine. Life Science Journal, 2014, no. 11, pp. 650-654.

  4. Krylov B.A., Manuilov A.A., Federov S.A., Yun A.A. Vestnik Moskovskogo aviatsionnogo instituta, 2010, vol. 17, no. 5, pp. 111-115.

  5. ANSYS 15.0 User's Guide.

  6. Biryukov V.I., Belaya A.Yu. Vestnik Moskovskogo aviatsionnogo instituta, 2011, vol. 18, no. 3, pp. 110-115.

  7. Agul'nik A.B., Onishchik I.I., Khtai T.M. Vestnik Moskovskogo aviatsionnogo instituta, 2011, vol. 18, no. 2, pp. 65-71. — informational site of MAI

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