轮廓度与扭转角偏差对压气机气动性能的影响
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摘要
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。
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.
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.
引文
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9李晓丽,楚武利.安装角变化对多级轴流压缩机性能影响的分析[J].风机技术,2008,(5):27-29Li Xiaoli,Chu Wuli.Analysis on the influence of variable installation angle on performance of multi-stage axial-flow compressor[J].Compressor,Blower and Fan Technology,2008,(5):27-29
10于贤君,庞健,刘宝杰.低速模拟在叶型加工偏差影响研究的应用[J].工程热物理学报,2018,39(7):1436-1446Yu Xianjun,Pang Jian,Liu Baojie.The application of low-speed simulation in researching the impact of blades manufacturing deviation on aerodynamic performance[J].Journal of Engineering Thermophysics,2018,39(7):1436-1446
11张伟昊,邹正平,李维,等.叶型偏差对涡轮性能影响的非定常数值模拟研究[J].航空学报,2010,31(11):2130-2138Zhang Weihao,Zou Zhengping,Li Wei,et al.Unsteady numerical simulation investigation of effect of blade profile deviation on turbine performance[J].Acta Aeronautica et Astronautica Sinica,2010,31(11):2130-2138
12李俊,刘波,杨小东,等.高空低雷诺数吸附式压气机叶型耦合优化设计[J].航空动力学报,2016,31(2):503-512Li Jun,Liu Bo,Yang Xiaodong,et al.Coupling optimization design for aspirated compressor airfoil with low Reynolds number in high altitude[J].Journal of Aerospace Power,2016,31(2):503-512
13何成,王如根,胡加国,等.不同转速下叶尖间隙流对跨声速压气机失速的影响[J].推进技术,2016,37(9):1657-1663He Cheng,Wang Rugen,Hu Jiaguo,et al.Effects of tip leakage flow on transonic compressor instability at different rotation speed[J].Journal of Propulsion Technology,2016,37(9):1657-1663
2 Lange A,Voigt M,Vogeler K,et al.Impact of manufacturing variability on multistage high-pressure compressor performance[J].Journal of Engineering for Gas Turbines and Power,2012,134(11):417-426
3 Schnell R,Lengyel-Kampmann T,Nicke E.On the impact of geometric variability on fan aerodynamic performance,unsteady blade row interaction,and its mechanical characteristics[J].Journal of Turbomachinery,2014,136(9):1-14
4 Elmstrom M E,Millsaps K T,Hobson G V,et al.Impact of nonuniform leading edge coatings on the aerodynamic performance of compressor airfoils[J].Journal of Turbomachinery,2011,133(4):041004
5高丽敏,蔡宇桐,曾瑞慧,等.叶片加工误差对压气机叶栅气动性能的影响[J].推进技术,2017,38(3):525-531Gao Limin,Cai Yutong,Zeng Ruihui,et al.Effects of blade machining error on compressor cascade aerodynamic performance[J].Journal of Propulsion Technology,2017,38(3):525-531
6郑似玉,滕金芳,羌晓青.叶片加工超差对高压压气机性能影响和敏感性分析[J].机械工程学报,2018,54(2):216-224Zheng Siyu,Teng Jinfang,Qiang Xiaoqing.Sensitivity analysis of manufacturing variability on high-pressure compressor performance[J].Journal of Mechanical Engineering,2018,54(2):216-224
7郑似玉,滕金芳,羌晓青.轮廓度加工超差对压气机气动性能影响的数值研究[J].科学技术与工程,2016,16(29):317-320Zheng Siyu,Teng Jinfang,Qiang Xiaoqing.Numerical investigation of profile variability on axial compressor flow field performance[J].Science Technology and Engineering,2016,16(29):317-320
8郑似玉,滕金芳,羌晓青.位置度超差对轴流压气机流场性能影响的数值研究[J].流体机械,2016,44(11):20-24Zheng Siyu,Teng Jinfang,Qiang Xiaoqing.Numerical investigation of positional variability on axial compressor flow field performance[J].Fluid Machinery,2016,44(11):20-24
9李晓丽,楚武利.安装角变化对多级轴流压缩机性能影响的分析[J].风机技术,2008,(5):27-29Li Xiaoli,Chu Wuli.Analysis on the influence of variable installation angle on performance of multi-stage axial-flow compressor[J].Compressor,Blower and Fan Technology,2008,(5):27-29
10于贤君,庞健,刘宝杰.低速模拟在叶型加工偏差影响研究的应用[J].工程热物理学报,2018,39(7):1436-1446Yu Xianjun,Pang Jian,Liu Baojie.The application of low-speed simulation in researching the impact of blades manufacturing deviation on aerodynamic performance[J].Journal of Engineering Thermophysics,2018,39(7):1436-1446
11张伟昊,邹正平,李维,等.叶型偏差对涡轮性能影响的非定常数值模拟研究[J].航空学报,2010,31(11):2130-2138Zhang Weihao,Zou Zhengping,Li Wei,et al.Unsteady numerical simulation investigation of effect of blade profile deviation on turbine performance[J].Acta Aeronautica et Astronautica Sinica,2010,31(11):2130-2138
12李俊,刘波,杨小东,等.高空低雷诺数吸附式压气机叶型耦合优化设计[J].航空动力学报,2016,31(2):503-512Li Jun,Liu Bo,Yang Xiaodong,et al.Coupling optimization design for aspirated compressor airfoil with low Reynolds number in high altitude[J].Journal of Aerospace Power,2016,31(2):503-512
13何成,王如根,胡加国,等.不同转速下叶尖间隙流对跨声速压气机失速的影响[J].推进技术,2016,37(9):1657-1663He Cheng,Wang Rugen,Hu Jiaguo,et al.Effects of tip leakage flow on transonic compressor instability at different rotation speed[J].Journal of Propulsion Technology,2016,37(9):1657-1663
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