The invention provides a turbine nozzle, an expansion machine and an air cycle machine. The turbine nozzle comprises a turbine disc (1), wherein a convex ring (2) is arranged at one end of the turbine disc (1); nozzle blades (3) are arranged on the end surface of the convex ring (2) in the circumferential direction; and in a wing-shaped structure of each nozzle blade (3), the curvature of a mean camber line of the front 50% meridian chord length close to the front edge is smaller than the curvature of a mean camber line of the rear 50% meridian chord length, far away from the front edge, of the nozzle blade (3), the curvature change rate of the mean camber line of the front 50% meridian chord length close to the front edge is smaller than the curvature change rate of the mean camber line of the rear 50% meridian chord length, away from the front edge, of the nozzle blade (3), and the curvature of the mean camber line of the rear 50% meridian chord length, away from the front edge, of the nozzle blade (3) is gradually increased. According to the turbine nozzle, the interference loss of a shock wave boundary layer can be reduced, the efficiency of the turbine nozzle is improved, the enthalpy difference of a refrigerating system is increased, and the entropy increase of the system is effectively reduced.
本申请提供一种涡轮喷嘴、膨胀机和空气循环机。该涡轮喷嘴包括轮盘(1),轮盘(1)的一端设置有凸环(2),凸环(2)的端面上沿周向设置有喷嘴叶片(3),喷嘴叶片(3)的翼型结构中,靠近前缘的前50%子午弦长的中弧线曲率小于喷嘴叶片(3)的远离前缘的后50%子午弦长的中弧线曲率,靠近前缘的前50%子午弦长的中弧线曲率变化率小于喷嘴叶片(3)的远离前缘的后50%子午弦长的中弧线曲率变化率,喷嘴叶片(3)的远离前缘的后50%子午弦长的中弧线曲率逐渐增大。根据本申请的涡轮喷嘴,能够减小激波附面层干涉损失,提高涡轮喷嘴效率,增大制冷系统焓差,并有效减小系统熵增。
Turbine nozzle, expansion machine, and air cycle machine
涡轮喷嘴、膨胀机和空气循环机
2021-08-06
Patent
Elektronische Ressource
Chinesisch
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