高通流宽工况适应范围超多级压气机设计研究与验证

To comprehensively improve the design capability of super multistage (more than 7 stages) compressor for high-speed turbine engine, the design and verification of the super multistage compressor with high-pass flow and wide operating range were introduced in this paper. It is characterized by high inlet Mach number and wide working range. The design technology of high-pass flow compressor with small hub-tip ratio, the design technology of compressor with wide operating range considering ground take-off and high Mach number working condition were studied. The design simulation and test verification of super multistage compressor with high-pass flow and wide operating range was accomplished, and the matching of each stage under the two states of ground take-off and high Mach number was comprehensively studied. The test results show that the compressor flow rate, pressure ratio and efficiency meet the design index under the ground take-off and high Mach number states. The maximum efficiency of the ground take-off state is 0.891 at 100% relative rotating speed, and that of the high Mach number state is 0.865 at 74.1% relative rotating speed. The surge margin of each rotating speed is greater than 24%, which is well matched at all stages. The problems of difficult matching of high-load super multistage compressor and low efficiency of high-pass flow compressor are solved, which lays a foundation for the compressor design of the next generation engine.