关键词: 气动匹配；反问题设计方法；多级轴流压气机；载荷分布

Abstract: In order to improve the performance of multistage axial compressor，a new aerodynamic matching design method for multistage axial compressor is developed based on the three-dimensional viscous inverse method. The swirl of the compressor stage exit is chosen as the design objective and the design variable is the blade pressure loading distribution on the blade surface. The relationship between blade exit swirl and blade surface pressure loading distribution is established based on the angular momentum conservation. The blade pressure loading is automatically adjusted during the computation process to modify the blade exit swirl. In order to ensure that each stage of compressor is working under the specified inlet operation condition，the stator of upstream stage is redesigned using the inverse design method. The exit swirl of upstream stage is adjusted to satisfy the design value. In order to validate the effectiveness of present method，an aerodynamic matching design using inverse method is carried out on a 4 stage high-pressure axial compressor original design configuration，which is used as the test case. The exit swirl on three axial positions between stages is modified to improve the inlet operation condition of downstream stage. The flow in the compressor blade passage satisfies the design intent and matches better between stages. Compared with original design，the total pressure ratio and adiabatic efficiency of compressor is improved by 2.8% and 1.3%，which demonstrated the effectiveness and accuracy of present method.

Key words: Aerodynamic matching；Inverse method；Multistage axial compressor；Pressure loading distribution