高负荷轴流压气机设计与试验验证

doi:10.7527/S1000-6893.2017.620990

Abstract

Abstract:

In order to improve the aerodynamic performance of the high load axial-flow compressor and to explore the design method for the high load compressor. The axial load and parameter distribution of the high load compressor is studied and selectively optimized. The span load distribution of the compressor is then optimized using 2D direct and inverse solution design and analysis method. 3D flow filed analysis is applied to conduct refinement analysis. Stage parameters of the high load compressor are matched well. The method is used to design one high load compressor. Test results and calculation results are compared and studied. Results show that this technique can effectively improved compressor performance under all operation conditions and can allow the compressor to work with reasonable parameters at each stage. With this design technique, the average stage pressure ratio of the compressor can be increased by 16% and efficiency can be increased by 1% over the 4th generation aero-engine compressor.

Key words: high load, axial-flow compressor, stage matching, optimization, test verification

CLC Number:

V231.3

LI Qinghua, AN Liping, XU Lin, MI Pan, PANG Chao. Design and test verification of high load axial-flow compressor[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(9): 520990-520990.

References

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Design and test verification of high load axial-flow compressor

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