轮廓度与扭转角偏差对压气机气动性能的影响

压气机叶片实际加工过程中,会出现叶片轮廓度、扭转角等加工超差,对压气机气动性能产生影响。采用S1流面计算和三维数值计算的方法分别研究了轮廓度及扭转角偏差对亚音速压气机气动性能的影响,计算结果表明:轮廓度增大,叶型最小损失值增大;堵点流量逐渐降低,轮廓度为0. 08 mm时,堵点流量减小了1%;峰值效率逐渐降低,但降低幅度较小。扭转角偏差对性能的影响来自于前缘偏转对进口喉道面积与尾缘偏转对叶片出口气流角的改变;扭转角偏差对叶型最小损失值影响不大,±0. 35°扭转角偏差范围对叶片的低损失攻角范围影响较小;扭转角向前缘打开方向增大,流量-压比特性线向右上方平移;扭转角向前缘关闭方向增大,流量-压比特性线向左下方平移;扭转角偏差0. 35°,最大流量减小了0. 67%;扭转角偏差对峰值效率点的影响微弱。

Influence of blade profile and twist angle difference on compressor aerodynamic performance

In the processing of manufacturing the compressor blade, there are always the tolerances of blade profile and twist angle, which affects compressor aerodynamic performance. Numerical investigations of S1 surface and three dimensional calculations were conducted to study the influence of the blade profile and twist angle tolerance on compressor aerodynamic performance. The results show that increase of the blade profile results in the growth of airfoil loss and reduction of choke mass flow. At the condition of 0.08 millimeter blade profile, the reduction of choke mass flow is 1%. Peak efficiency gradually decreases a little. The influence of twist angle difference on compressor performance results from the change of throat area caused by blade leading edge twist and exit flow angle caused by blade trailing edge twist. Twist angle has little influence on airfoil loss. Besides, twist angle between positive and minus 0.35 degree has little impact on loss budget. When increase twist angle at the direction of opening leading edge, the performance curve of mass flow and pressure ratio goes to upward and right direction. The choke mass flow and maximum pressure ratio grow. When increase twist angle at the direction of closing leading edge, the performance curve of mass flow and pressure ratio goes to downward and left direction. The choke mass flow and maximum pressure ratio decrease. The reduction of choke mass flow is 0.67% at the condition of twist angle difference 0.35 degree. The influence of twist angle on peak efficiency is trivial.