Experimental Investigations On The Performance Of Aspirate Compressor Cascades

High Trust-Weight-Ratio has always been one of main goals for modern aeroengine design. Aspirated compressor in one of outstanding achievements in the IHPTET Project, which has been investigated by many researchers in MIT GTL and GE Company for several decades. With the help of highly loaded aspirated compressor, it should be possible to design a single stage fan instead of 2 or 3 stages fan used widely during the aeroengine design at present. In order to meet the requirements for highly loaded fan design, the primary investigations on the aspirated compressor cascade have been finished by the Institute of Engineering Thermophysics, Chinese Academy of Sciences. Some design criteria for the aspirated compressor and fundamental theory on boundary layer development under the condition of aspiration have been established based on the calculational and experimental results. Meanwhile influences of aspiration location and aspirated flow rate on pressure distribution on blade surfaces and profile loss have been discussed in details according to the numerical and experimental results based on aspirated compressor cascade test. And then some design criteria on aspirated compressor profile have been summed up to provide the technical supports for the advanced aeroengine design.With the subsonic cascade wind tunnel, the author designed the suction slot on the suction surface of compressor blade and the device which could control the suction flow. The effects of suction on the performance of aspirate compressor cascade under different Mach numbers, incidence angle, suction flow rate and suction slot situation were studied. The parameters to be measured included the pressure distributions on the surfaces of the cascade, total pressure, deviation angle. It's obviously proven that boundary layer suction alleviated the accumulation of low energy fluid at suction surface corners, reduced the total pressure loss and decreased the deviation angle. With the appropriate suction slot location and suction flow rate, the compressor performance should be further improved.