Research On Influence Of Tubercle Leading Edge Blade To The Performance And Stability Of Compressor

Improving aerodynamic performance and stability of compressor is an important way to achieve high thrust weight ratio, low specific fuel consumption rate and high stability. However, along with the skewed swept and low aspect ratio, tandem rotor aerodynamic design technology have been improved continuously, to discover the potential of compressor become increasingly difficult in the aspect of traditional design, it is possible for the designer to promote the aerodynamic performance and stability with trying new approaches or methods. This thesis takes example of the research on the front of humpback whale's flippers in external flow and introduces the special leading edge pattern to compressor blade with the name of ‘tubercle leading edge blade' to try to improve the performance and stability of compressor.(1) Firstly, numerical simulation research on tubercle leading edge cascade has been carried out, which analysis the impact of parameters of the tubercle as well as the impact rule and mechanism of the tubercle to the stream structure of the cascade. The results show that the tubercles increase total pressure loss of the cascade in the stable region, but significantly reduce it in the stall region. The parameters of the tubercle have influences on the cascade. In the stable region, the number of the tubercles has more impact than the amplitude, not obviously; in the stall region, the amplitude has more impact. The tubercles change the stream structure of the cascade significantly, which improve the performance of the cascade in the stall region.(2) Then, the experimental research on the tubercle leading edge cascade is carried out to verify the reliability of the numerical method. This experiment also proves that tubercle leading edge has the ability of improving the performance in the stall region.(3) Finally, tubercle leading edge stator is studied on a transonic single stage compressor. The results show that the efficiency and total pressure ratio are increased in most working zone under the design speed. The tubercles modify the structure of the stator fields, which developed into mutli but small separation zone, the end wall flow zone has also been bettered. The pair swirl generated on the crest of the tubercle leads the partial separation delay effect that broadens the stable region of the compressor.