压气机静子叶型低速模拟方法研究
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摘要
针对静子基元叶型低速模拟问题,分析了高低速转换过程的设计准则,提出对于静子叶型低速模拟需要保持出口气流角不变。根据设计准则,利用一维等熵假设,推导出基于低速叶型喉道宽度的约束模型,分析了关键设计参数的计算方法。利用分析结果,进行了一组高速静子CDA叶型的低速模拟,数值计算结果显示,低速模拟叶型的损失特性,落后角特性与高速原型趋势较为一致。分析发现喉道约束模型计算的喉道宽度与低速叶型实际值相对误差较小。在低速模拟过程中,喉道约束模型可以指导低速叶型最大厚度等参数的调整,从而减少设计迭代次数。
Some analyses of low-speed similarity design principles have been done for stator airfoils. It was proposed that the outlet flow angle should be kept unchanged for high-to-low speed transformation. Based on the design principles and a one-dimensional isentropic hypothesis, a constrained model of throat width for stator airfoils was derived, and the method of calculating geometry design parameters of low-speed airfoil was presented. According to the analysis results,a set of low-speed similarity transformation of high-speed stator CDA airfoil was carried out.The numerical results showed that the incidence-loss characteristics and incidence-deviation-angle characteristics had a good agreement for high and low speed airfoils. What's more, the relative error of throat width is small between the actual value and the value calculated by the throat constraint model. Therefore, the ad.justment of parameters such as maximum thickness of low-speed blade could be guided by the throat constraint model, which could reduce the iterations of design low-speed airfoils.
Some analyses of low-speed similarity design principles have been done for stator airfoils. It was proposed that the outlet flow angle should be kept unchanged for high-to-low speed transformation. Based on the design principles and a one-dimensional isentropic hypothesis, a constrained model of throat width for stator airfoils was derived, and the method of calculating geometry design parameters of low-speed airfoil was presented. According to the analysis results,a set of low-speed similarity transformation of high-speed stator CDA airfoil was carried out.The numerical results showed that the incidence-loss characteristics and incidence-deviation-angle characteristics had a good agreement for high and low speed airfoils. What's more, the relative error of throat width is small between the actual value and the value calculated by the throat constraint model. Therefore, the ad.justment of parameters such as maximum thickness of low-speed blade could be guided by the throat constraint model, which could reduce the iterations of design low-speed airfoils.
引文
[1]陈懋章.中国航空发动机高压压气机发展的几个问题[J].航空发动机,2006, 32(2):5-11CHEN Maozhang. Some Issues in the Research and Development of Aeroengine HP Compressor in China[J]. Aeroengine, 2006, 32(2):5-11
[2] Woolard H W. A Note on the Subsonic Compressible Flow About Airfoils in a Cascade[J]. Journal of the Aeronautical Sciences, 1950, 17(6):379-381
[3] Wisler D C. Core Compressor Exit Stage Study Volume I—Blading Design[R].NASA-CR-135391, General Electic Company, 1977
[4] Wisler D C. Loss Reduction in Axial-flow Compressors Through Low-speed Model Testing[J]. Transactions of the ASME. Journal of Engineering for Gas Turbines and,1985, 107(2):354-363
[5] Dring R P, Joslyn H D, Hardin L W. An Investigation of Axial Compressor Rotor Aerodynamics[J]. Journal of Engineering for Power, 1982, 104(1):84-96
[6] Joslyn H D. Dring R P. Axial Compressor Stator Aerodynamics[J]. Transactions of the ASME. Journal of Engineering for Gas Turbines and Power, 1985, 107(2):485-493
[7] Wasserbauer C A, Weaver H F, Senyitko R G. NASA LowSpeed Axial Compressor for Fundamental Research[R],NASA-TM-4635, 1995
[8] Dong Y, Baltimore S J, Hodson H P. Three-Dimensional Flows and Loss Reduction in Axial Compressors[J]. Journal of Turbomachinery, 1987, 109(3):354-361
[9] Robinson C J, Northall J D, McFarlane C W R. Measurement and Calculation of the Three-Dimensional Flow in Axial Compressor Stators, With and Without End-Bends[R].ASME Paper GT1989-79139, 1989
[10] Lyes P A. Low speed Axial Compressor Design and Evaluation:High Speed Representation and Endwall Flow Control Studies[D]. School of Mehcanical Engineering, Department of Turbomachinery and Engineering Mechanics.Cranfield University, 1999
[11]朱年国,徐力平,陈矛章.高压压气机叶栅的高速模型和低速模型的相似变换准则[J].航空动力学报,1990, 5(3):193-198ZHU Nianguo, XU Liping, CHEN Maozhang. Similarity Rules for Transformation Between High and Low-Speed Models of High Pressure Axial Compressor Bladings[J].Journal of Aerospace Power, 1990, 5(3):193-198
[12]朱年国,徐力平,陈矛章.用于高压压气机叶栅设计的影响矩阵法[J].力学学报,1992, 24(3):303-311ZHU Nianguo, XU Liping, CHEN Maozhang. An Influence-Matrix Method For High Pressure Compressor Blade Designs[J]. Acta Mechanica Sinica, 1992, 24(3):303-311
[13]朱年国,徐力平,陈矛章.叶栅相似变换准则的实验研究[J].航空动力学报,1991, 6(3):193-198, 281ZHU Nianguo, XU Liping, CHEN Maozhang. Experimental Study on Cascade Similarity Transformation Rules[J].Journal of Aerospace Power, 1991, 6(3):193-198, 281
[14]于贤君,刘宝杰,蒋浩康,等.轴流压气机转子尖部三维复杂流动I一实验和理论研究[J].航空学报,2010, 31(1):48-57YU Xianjun, LIU Baojie, JIANG Haokang. Threedimensional Flows near Rotor Tip in an Axial Compressor I—Experimental and Theoretical Studies[J]. Acta Aeronautica Et Astronautica Sinica, 2010, 31(1):48-57
[15]于贤君,刘宝杰,蒋浩康.轴流压气机转子尖部三维复杂流动II一数值模拟研究[J].航空学报,2010, 31(1):58-69YU Xianjun, LIU Baojie, JIANG Haokang. Threedimensional Flows near Rotor Tip in an Axial Compressor II—Numerical Simulation Study[J]. Acta Aeronautica Et Astronautica Sinica, 2010, 31(1):58-69
[16]王志强.高压压气机低速模拟方法研究[D].南京航空航天大学,2010WANG Zhiqiang. Research on the Method of Low-speed Model Testing for High Pressure Compressor[D]. Nanjing University of Aeronautics and Astronautics, 2010
[17]黄天豪.压气机低速模化设计及机匣处理研究[D].上海交通大学,2014HUANG Tianhao. Low-Speed Model Design and Casing Treatment Study for Compressor[D]. Shanghai Jiao Tong University, 2014
[18]马宁.高速压气机低速模化相似准则及轴向缝机匣处理流动机理研究[D].中国科学院研究生院(工程热物理研究所),2016MA Ning. Research on the Low-Speed Modeling Similarity Criteria for High-Speed Compressors and the Flow Mechanisms of Axial-Slot Casing Treatments[D]. University of the Chinese Academy of Sciences, 2016
[19]于贤君,袁现立,刘宝杰,等.压气机二维叶型的低速模拟分析[J].工程热物理学报,2016, 37(4):721-728YU Xianjun, YUAN Xianli, LIU Baojie, et al. Analysis of the Low-Speed Similarity Design Principle for a Compressor Airfoil[J]. Journal of Engineering Thermophysics,2016, 37(4):721-728
[2] Woolard H W. A Note on the Subsonic Compressible Flow About Airfoils in a Cascade[J]. Journal of the Aeronautical Sciences, 1950, 17(6):379-381
[3] Wisler D C. Core Compressor Exit Stage Study Volume I—Blading Design[R].NASA-CR-135391, General Electic Company, 1977
[4] Wisler D C. Loss Reduction in Axial-flow Compressors Through Low-speed Model Testing[J]. Transactions of the ASME. Journal of Engineering for Gas Turbines and,1985, 107(2):354-363
[5] Dring R P, Joslyn H D, Hardin L W. An Investigation of Axial Compressor Rotor Aerodynamics[J]. Journal of Engineering for Power, 1982, 104(1):84-96
[6] Joslyn H D. Dring R P. Axial Compressor Stator Aerodynamics[J]. Transactions of the ASME. Journal of Engineering for Gas Turbines and Power, 1985, 107(2):485-493
[7] Wasserbauer C A, Weaver H F, Senyitko R G. NASA LowSpeed Axial Compressor for Fundamental Research[R],NASA-TM-4635, 1995
[8] Dong Y, Baltimore S J, Hodson H P. Three-Dimensional Flows and Loss Reduction in Axial Compressors[J]. Journal of Turbomachinery, 1987, 109(3):354-361
[9] Robinson C J, Northall J D, McFarlane C W R. Measurement and Calculation of the Three-Dimensional Flow in Axial Compressor Stators, With and Without End-Bends[R].ASME Paper GT1989-79139, 1989
[10] Lyes P A. Low speed Axial Compressor Design and Evaluation:High Speed Representation and Endwall Flow Control Studies[D]. School of Mehcanical Engineering, Department of Turbomachinery and Engineering Mechanics.Cranfield University, 1999
[11]朱年国,徐力平,陈矛章.高压压气机叶栅的高速模型和低速模型的相似变换准则[J].航空动力学报,1990, 5(3):193-198ZHU Nianguo, XU Liping, CHEN Maozhang. Similarity Rules for Transformation Between High and Low-Speed Models of High Pressure Axial Compressor Bladings[J].Journal of Aerospace Power, 1990, 5(3):193-198
[12]朱年国,徐力平,陈矛章.用于高压压气机叶栅设计的影响矩阵法[J].力学学报,1992, 24(3):303-311ZHU Nianguo, XU Liping, CHEN Maozhang. An Influence-Matrix Method For High Pressure Compressor Blade Designs[J]. Acta Mechanica Sinica, 1992, 24(3):303-311
[13]朱年国,徐力平,陈矛章.叶栅相似变换准则的实验研究[J].航空动力学报,1991, 6(3):193-198, 281ZHU Nianguo, XU Liping, CHEN Maozhang. Experimental Study on Cascade Similarity Transformation Rules[J].Journal of Aerospace Power, 1991, 6(3):193-198, 281
[14]于贤君,刘宝杰,蒋浩康,等.轴流压气机转子尖部三维复杂流动I一实验和理论研究[J].航空学报,2010, 31(1):48-57YU Xianjun, LIU Baojie, JIANG Haokang. Threedimensional Flows near Rotor Tip in an Axial Compressor I—Experimental and Theoretical Studies[J]. Acta Aeronautica Et Astronautica Sinica, 2010, 31(1):48-57
[15]于贤君,刘宝杰,蒋浩康.轴流压气机转子尖部三维复杂流动II一数值模拟研究[J].航空学报,2010, 31(1):58-69YU Xianjun, LIU Baojie, JIANG Haokang. Threedimensional Flows near Rotor Tip in an Axial Compressor II—Numerical Simulation Study[J]. Acta Aeronautica Et Astronautica Sinica, 2010, 31(1):58-69
[16]王志强.高压压气机低速模拟方法研究[D].南京航空航天大学,2010WANG Zhiqiang. Research on the Method of Low-speed Model Testing for High Pressure Compressor[D]. Nanjing University of Aeronautics and Astronautics, 2010
[17]黄天豪.压气机低速模化设计及机匣处理研究[D].上海交通大学,2014HUANG Tianhao. Low-Speed Model Design and Casing Treatment Study for Compressor[D]. Shanghai Jiao Tong University, 2014
[18]马宁.高速压气机低速模化相似准则及轴向缝机匣处理流动机理研究[D].中国科学院研究生院(工程热物理研究所),2016MA Ning. Research on the Low-Speed Modeling Similarity Criteria for High-Speed Compressors and the Flow Mechanisms of Axial-Slot Casing Treatments[D]. University of the Chinese Academy of Sciences, 2016
[19]于贤君,袁现立,刘宝杰,等.压气机二维叶型的低速模拟分析[J].工程热物理学报,2016, 37(4):721-728YU Xianjun, YUAN Xianli, LIU Baojie, et al. Analysis of the Low-Speed Similarity Design Principle for a Compressor Airfoil[J]. Journal of Engineering Thermophysics,2016, 37(4):721-728