Effect Of Blade Machining Error And Data Transfer On Compressor Aerodynamic Performance

With the improvement of the design performance of the compressor, compressor blades bend, twist, swept increasing extent and tend to be thinner. Compressor blades become one of the largest number and the hardest machining part of aeroengine. During the manufacture process of compressor blades, the inevitable machining error and data transfer has very important influence on aerodynamic performance and economy of the compressor as well as the entire engine. Therefore, the research of effect machining error and data transfer on compressor aerodynamic performance has significantly importance. Combined with our existing blade machining process system, the thesis focused on the blade machining error and error produced by data transfer of blade design section and manufacturing section and carried out the following aspects:1. Deep analysis of the processing and checking process of modern aero engine compressor blades. Blade error analysis method based on the coordinate detection method has been developed. The blade parameter analysis program and profile error calculation procedure are written. Then the distribution of blade error has been analyzed.2. The cascade aerodynamic performance sensitivity to different types of error using single factor method has been researched. A large number of numerical results show that blade positive profiles error is detrimental to the performance; the blade leading edge processing error is the sensitive part; at high Mach number cascade aerodynamic performance has stronger sensitivity.3. Compressor blades data transfer from design section to manufacture section has been analyzed and blade data conversion program is written. The factors like interpolation method that affect accuracy of data transfer and magnitude and distribution of data transfer error have been discussed based on contra-rotating compressor. Numerical study shows data transfer error has little effect on aerodynamic performance, but re-fitting leading and trailing edge has more impact on aerodynamic performance than the direct result of interpolation.