Research on the Mechanism of Flow Loss in the Transition Stage of Aircraft Engine Stage
In order to explore the flow mechanism and loss mechanism of the internal flow field in the transition stage of aircraft engine and promote the overall performance improvement of aircraft engines,this article conducts numerical simulation and flow field analysis on the transition stage of a certain air-craft engine,and compares it with experimental results.The results show that the flow field at the outlet of transition stage is evenly distributed in the radial position of the 20％-90％flow channel,and the total pressure loss of air flow at the outlet is mainly concentrated near the trailing edge of the support plate and the upper and lower walls;the loss in the flow channel is caused by the combined curvature of the lower wall and the boundary layer seperation on the support plate surface;the secondary flow disturbance in the corner region starts along the flow direction at the point where the curvature of the lower wall is maxi-mum;and the total pressure loss will increase with the increase of flow rate.The larger the flow rate,the greater the increment of total pressure loss.The increment of total pressure loss at flow rate of 140 to 170 m/s is 7 times that at flow rate of 80 to 110 m/s.
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