Investigation of the Effect of the Non-uniform Flow Distribution After Compressor of Gas Turbine Engine on Inlet Parameters of the Turbine

2017 International Conference on Aerospace Technology, Communications and Energy Systems

航空航天工程;无线电电子学;能源学

Orlov, M.Yu.^1 ; Lukachev, S.V.^1 ; Anisimov, V.M.^1

Samara National Research University, Scientific Educational Center of Fluid Dynamics Research, Moskovskoye Shosse 34, Samara

443086, Russia^1

关键词: Combined actions;    Compressor blades;    Flow distribution;    High pressure turbine;    Impact of non-uniformities;    Integrated simulations;    Neighboring nodes;    Non-uniform flows;   

Others  :  https://iopscience.iop.org/article/10.1088/1757-899X/302/1/012021/pdf
DOI  :  10.1088/1757-899X/302/1/012021

学科分类：航空航天科学

来源: IOP

【 摘 要 】

The position of combustion chamber between compressor and turbine and combined action of these elements imply that the working processes of all these elements are interconnected. One of the main requirements of the combustion chamber is the formation of the desirable temperature field at the turbine inlet, which can realize necessary durability of nozzle assembly and blade wheel of the first stage of high-pressure turbine. The method of integrated simulation of combustion chamber and neighboring nodes (compressor and turbine) was developed. On the first stage of the study, this method was used to investigate the influence of non-uniformity of flow distribution, occurred after compressor blades on combustion chamber workflow. The goal of the study is to assess the impact of non-uniformity of flow distribution after the compressor on the parameters before the turbine. The calculation was carried out in a transient case for some operation mode of the engine. The simulation showed that the inclusion of compressor has an effect on combustion chamber workflow and allows us to determine temperature field at the turbine inlet and assesses its durability more accurately. In addition, the simulation with turbine showed the changes in flow velocity distribution and pressure in combustion chamber.