Numerical Investigation Of Applying Bowed Blades In Transonic Compressor

Gas turbine is a product of great strategic significance to national defense industry and national economy. As one of the three core components of gas turbine, the improvement of the performance of the compressor plays a key role in improving the overall performance of the engine. With the development of high load, high speed and high performance of the compressor, the blade design technology of high performance transonic compressor has become one of the hot research fields. The axial and circumferential lean or bending of the three dimensional stacking lines have great influence on the aerodynamic performance of the compressor. The application of the curved blade of transonic compressor has become the focus of the research work at home and abroad.In this paper, the Rotor37 and Stage37 of transonic compressor are studied as research objects. With commercial software NUMECA, the numerical study of the rotor and static blade bending is carried out. In order to provide further theoretical basis for the application of curved blade technology in transonic compressor, the influence of blade bending shape on the flow characteristics and loss mechanism of transonic compressor is studied, Mainly carried out the following aspects of the work:Firstly, the grid independence of the research objects are verified, and then the numerical results are compared with experiments, The results show that the numerical simulation can reflect the actual flow field information, and ensure the reliability of the calculation. In the following research, the numerical prototype has a high reference value.Then, the bending design of Rotor37 was carried out according to the parameters of the positive/negative bending, bending height and bending angles, Through the detailed numerical calculation of each scheme, the results are found that:The static pressure distribution on the wall surface and the structure of shock wave and vortex structure are changed as blade bending deformation. Under the premise of stable working range and total pressure ratio, the design of negative bending can improve efficiency and its promotion effect varies with bending height and angle, up to 1.3%. The design of positive bending make the rotor overall performance reduced, and it become worse with higher bending height and angle.Finally, according to the bending height and bending angle parameters, the bending design of the Stage37 stator blade is carried out, under the stage environment, each case of detail calculation results show that:When just stator bending, proper matching of bend high and angle design can make a better promotion of stable working flow range on the basis of guarantee the premise of the total pressure ratio and the adiabatic efficiency unchanged, basically in about 20%. When rotor was adopted bending design in the stage environment, the stage efficiency was promoted about 0.6%, the improvement of efficiency mainly came from the promotion of the performance of rotor. The reasonable curved blade design and appropriate inter stage matching can improve the overall performance of the compressor stage.