吸附式压气机叶栅的实验研究和分析
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摘要
高推重比是航空涡轮发动机设计过程中最为注重的技术指标之一，吸附式压气机是高推重比发动机研制中关于新型压气机的探索成果之一，有可能用单级吸附式风扇替代目前的两级或三级风扇。吸附式压气机的工作机理是借助叶片吸力面上的开槽吸除叶片表面的低能流体，防止或推迟附面层分离，使槽道气流实现较大的折转，风扇或压气机级负荷大大提高。
本文以平面叶栅风洞为实验平台，设计、加工了在叶栅吸力面上不同位置布置吸气槽，以及进行吸气和调节吸气量的设备，同时构建了实验台测量和数据采集系统。在不同来流马赫数、攻角、吸气量和吸气位置等状态下，测试吸附式压气机叶栅吸力面、压力面表面压力分布和叶栅尾缘等参数。借助数值分析和平面叶栅实验结果，讨论了吸气量、吸气位置对叶片表面压力分布、叶型损失的影响，初步总结了一些吸附式压气机叶型的设计准则。
结果表明，附面层吸除能有效减弱吸力面角区低能流体积聚，导致附面层减薄，减少分离损失，有助于降低叶栅总压损失，提高气流折转能力，改善叶栅气动性能。选择合适的吸气槽位置和吸气量，有助于进一步提高压气机的性能。
High Trust-Weight-Ratio has always been one of main goals for modern aeroengine design. Aspirated compressor in one of outstanding achievements in the IHPTET Project, which has been investigated by many researchers in MIT GTL and GE Company for several decades. With the help of highly loaded aspirated compressor, it should be possible to design a single stage fan instead of 2 or 3 stages fan used widely during the aeroengine design at present. In order to meet the requirements for highly loaded fan design, the primary investigations on the aspirated compressor cascade have been finished by the Institute of Engineering Thermophysics, Chinese Academy of Sciences. Some design criteria for the aspirated compressor and fundamental theory on boundary layer development under the condition of aspiration have been established based on the calculational and experimental results. Meanwhile influences of aspiration location and aspirated flow rate on pressure distribution on blade surfaces and profile loss have been discussed in details according to the numerical and experimental results based on aspirated compressor cascade test. And then some design criteria on aspirated compressor profile have been summed up to provide the technical supports for the advanced aeroengine design.
With the subsonic cascade wind tunnel, the author designed the suction slot on the suction surface of compressor blade and the device which could control the suction flow. The effects of suction on the performance of aspirate compressor cascade under different Mach numbers, incidence angle, suction flow rate and suction slot situation were studied. The parameters to be measured included the pressure distributions on the surfaces of the cascade, total pressure, deviation angle. It's obviously proven that boundary layer suction alleviated the accumulation of low energy fluid at suction surface corners, reduced the total pressure loss and decreased the deviation angle. With the appropriate suction slot location and suction flow rate, the compressor performance should be further improved.
本文以平面叶栅风洞为实验平台，设计、加工了在叶栅吸力面上不同位置布置吸气槽，以及进行吸气和调节吸气量的设备，同时构建了实验台测量和数据采集系统。在不同来流马赫数、攻角、吸气量和吸气位置等状态下，测试吸附式压气机叶栅吸力面、压力面表面压力分布和叶栅尾缘等参数。借助数值分析和平面叶栅实验结果，讨论了吸气量、吸气位置对叶片表面压力分布、叶型损失的影响，初步总结了一些吸附式压气机叶型的设计准则。
结果表明，附面层吸除能有效减弱吸力面角区低能流体积聚，导致附面层减薄，减少分离损失，有助于降低叶栅总压损失，提高气流折转能力，改善叶栅气动性能。选择合适的吸气槽位置和吸气量，有助于进一步提高压气机的性能。
High Trust-Weight-Ratio has always been one of main goals for modern aeroengine design. Aspirated compressor in one of outstanding achievements in the IHPTET Project, which has been investigated by many researchers in MIT GTL and GE Company for several decades. With the help of highly loaded aspirated compressor, it should be possible to design a single stage fan instead of 2 or 3 stages fan used widely during the aeroengine design at present. In order to meet the requirements for highly loaded fan design, the primary investigations on the aspirated compressor cascade have been finished by the Institute of Engineering Thermophysics, Chinese Academy of Sciences. Some design criteria for the aspirated compressor and fundamental theory on boundary layer development under the condition of aspiration have been established based on the calculational and experimental results. Meanwhile influences of aspiration location and aspirated flow rate on pressure distribution on blade surfaces and profile loss have been discussed in details according to the numerical and experimental results based on aspirated compressor cascade test. And then some design criteria on aspirated compressor profile have been summed up to provide the technical supports for the advanced aeroengine design.
With the subsonic cascade wind tunnel, the author designed the suction slot on the suction surface of compressor blade and the device which could control the suction flow. The effects of suction on the performance of aspirate compressor cascade under different Mach numbers, incidence angle, suction flow rate and suction slot situation were studied. The parameters to be measured included the pressure distributions on the surfaces of the cascade, total pressure, deviation angle. It's obviously proven that boundary layer suction alleviated the accumulation of low energy fluid at suction surface corners, reduced the total pressure loss and decreased the deviation angle. With the appropriate suction slot location and suction flow rate, the compressor performance should be further improved.
引文
[1]方昌德．流动控制技术在航空涡轮推进系统上的应用．燃气涡轮试验与研究．2003．16(2)：1-6．
[2]发动机常见故障介绍，航空科技，1978,1．
[3]Nobuyuki Tahara, Masahiro Kurosaki, Yutaka Ohta, et al, "Early Stall Warning Technique For Axial Flow" ASME Paper GT2004-53292,2004.
[4]Lin, F., Li, Z., "Recent Focus And Future Research In Smart Engine Technology" Proceeding of Symposuim on Energy Engineering in the 21st Century(SEE2000), Jan.2000, pp. 1388-1396.
[5]刘大响，2007，“振兴航空，动力先行，抓住机遇，加快发展”学术报告，中国科学院航空航天高技术研讨会，北京，2007年2月13日。
[6]Ali A. Merchant, Design And Analysis Of Axial Aspirated Compressor Stages, PhD thesis, MIT, Cambridge, MA, 1999.
[7]J. L. Kerrebrock, Mark Derla, Ali A. Merchant et al. A Family of Designs for Aspirated Compressors [R]. ASME Paper 98-GT-196, 1998.
[8]Shreeve, R. P., "Wake Measurements and Loss Evaluation in a Controlled Diffusion Compressor Cascade", ASME 90-GT-129.
[9]Poensgen, C. and Gallus, H. E., "Three-Dimensional Wake Decay Inside of a Compressor Cascade and Its Influence on the Downstream Unsteady Flow Field Part Ⅰ: Wake Decay Characteristics in the Passage", ASME 90-GT-21.
[10]Poensgen, C. and Gallus, H. E., "Three-Dimensional Wake Decay Inside of a Compressor Cascade and Its Influence on the Downstream Unsteady Flow Field Part Ⅱ: Unsteady Flow Field Downstream of the Stator", ASME 90-GT-22.
[11]Storer, J. A. and Cumpsty, N. A., "Tip Leakage Flow in Axial Compressors", ASME 90-GT-127.
[12]J. L. Kerrebrock, D. P. Reijnen, W. S. Zimimsky, et al. Aspirate Compressor. ASME 97-GT-525, 1997.
[13]B. J. Schuler, J. L. Kerrebrock, A. A. Merchant, M. Drela, J. Adamczyk, Design, Analysis, Fabrication and Test of an Aspirated Fan Stage [R].ASME Paper 2000-GT-618, 2000.
[14]Freeman J. H., Design of A Multi-spool, High-speed, Counter-Rotating, Aspirated Compressor[R]. AD-A385286, 2000.
[15]A. A. Merchant, M. Drela, J. L. Kerrebrock, J. J. Adamczyk, M. Celestina, Aerodynamic Design and Analysis of a High Pressure Radio Aspirated Compressor Stage[R]. ASME Paper 2000-GT-619, 2000.
[16]C. J. Carter, S.A. Guillot, W.F. Ng, W.W. Copenhaver. Aerodynamic Performance of a High-Turning Compressor Stator with Flow Control. AIAA 2001-GT-3973, 2001.
[17]D.P.Reijnen. Experimental Study of Boundary Layer Suction in a Transonic Compressor. PhD thesis, MIT, Cambridge, MA, January 1997.
[18]L. M. Smilg. Design of a high pressure ratio fan stage to take advantage of boundary layer suction. Master's thesis, MIT, Cambridge, MA, 1994.
[19]W. S. Ziminsky. Design of a high pressure ratio transonic compressor stage with active boundary layer control. Master's thesis, MIT, Cambridge, MA, 1996.
[20]Bolln G. W. Jr, Field K. J., Burnes R., F414 Engine Today and Growth Potential for 21st Century Fighter Mission Challenges[R]. ISABE 99-7113.
[21]宋彦萍，陈浮，赵桂杰等，吸气槽道形状对扩压叶栅性能的影响，工程热物理学报，2005，26(5)：761—763．
[22]周海等，跨音风扇转子叶片抽吸气数值实验探索，航空动力学报，第19卷第3期，2004．6．
[23]Yangping Song, Fuchen, Jun Yang and Zhongqi Wang, A Numerical Investigation Of Boundary Layers Suction In Compound Lean Compressor Cascades, ASME Turbo Expo 2005, GT2005-68441.
[24]陈浮等，附面层吸除对压气机叶栅稠度特性影响，工程热物理学报，第26卷第2期，2005．3．
[25] 庄平、俞镔、谭春青、张伟，“IET跨音速平面叶栅风洞使用说明(透平风洞鉴定材料之二)”，中国科学院工程热物理研究所，1995．
[26] 彭泽琰，刘刚，《航空燃气轮机原理》，国防工业出版社，2000．
[27] 西北工业大学编，《航空发动机气动参数测量》，国防工业出版社，1980.12．
[28] 童志庭等，虚拟仪器概念在压气机实验研究中的实现，工程热物理学报，第05期，2003．
[29] H.史里西廷，《边界层理论》，科学出版社，1991．
[30] 刘天宝，《流体力学及叶栅理论》，机械工业出版社，1983．
[2]发动机常见故障介绍，航空科技，1978,1．
[3]Nobuyuki Tahara, Masahiro Kurosaki, Yutaka Ohta, et al, "Early Stall Warning Technique For Axial Flow" ASME Paper GT2004-53292,2004.
[4]Lin, F., Li, Z., "Recent Focus And Future Research In Smart Engine Technology" Proceeding of Symposuim on Energy Engineering in the 21st Century(SEE2000), Jan.2000, pp. 1388-1396.
[5]刘大响，2007，“振兴航空，动力先行，抓住机遇，加快发展”学术报告，中国科学院航空航天高技术研讨会，北京，2007年2月13日。
[6]Ali A. Merchant, Design And Analysis Of Axial Aspirated Compressor Stages, PhD thesis, MIT, Cambridge, MA, 1999.
[7]J. L. Kerrebrock, Mark Derla, Ali A. Merchant et al. A Family of Designs for Aspirated Compressors [R]. ASME Paper 98-GT-196, 1998.
[8]Shreeve, R. P., "Wake Measurements and Loss Evaluation in a Controlled Diffusion Compressor Cascade", ASME 90-GT-129.
[9]Poensgen, C. and Gallus, H. E., "Three-Dimensional Wake Decay Inside of a Compressor Cascade and Its Influence on the Downstream Unsteady Flow Field Part Ⅰ: Wake Decay Characteristics in the Passage", ASME 90-GT-21.
[10]Poensgen, C. and Gallus, H. E., "Three-Dimensional Wake Decay Inside of a Compressor Cascade and Its Influence on the Downstream Unsteady Flow Field Part Ⅱ: Unsteady Flow Field Downstream of the Stator", ASME 90-GT-22.
[11]Storer, J. A. and Cumpsty, N. A., "Tip Leakage Flow in Axial Compressors", ASME 90-GT-127.
[12]J. L. Kerrebrock, D. P. Reijnen, W. S. Zimimsky, et al. Aspirate Compressor. ASME 97-GT-525, 1997.
[13]B. J. Schuler, J. L. Kerrebrock, A. A. Merchant, M. Drela, J. Adamczyk, Design, Analysis, Fabrication and Test of an Aspirated Fan Stage [R].ASME Paper 2000-GT-618, 2000.
[14]Freeman J. H., Design of A Multi-spool, High-speed, Counter-Rotating, Aspirated Compressor[R]. AD-A385286, 2000.
[15]A. A. Merchant, M. Drela, J. L. Kerrebrock, J. J. Adamczyk, M. Celestina, Aerodynamic Design and Analysis of a High Pressure Radio Aspirated Compressor Stage[R]. ASME Paper 2000-GT-619, 2000.
[16]C. J. Carter, S.A. Guillot, W.F. Ng, W.W. Copenhaver. Aerodynamic Performance of a High-Turning Compressor Stator with Flow Control. AIAA 2001-GT-3973, 2001.
[17]D.P.Reijnen. Experimental Study of Boundary Layer Suction in a Transonic Compressor. PhD thesis, MIT, Cambridge, MA, January 1997.
[18]L. M. Smilg. Design of a high pressure ratio fan stage to take advantage of boundary layer suction. Master's thesis, MIT, Cambridge, MA, 1994.
[19]W. S. Ziminsky. Design of a high pressure ratio transonic compressor stage with active boundary layer control. Master's thesis, MIT, Cambridge, MA, 1996.
[20]Bolln G. W. Jr, Field K. J., Burnes R., F414 Engine Today and Growth Potential for 21st Century Fighter Mission Challenges[R]. ISABE 99-7113.
[21]宋彦萍，陈浮，赵桂杰等，吸气槽道形状对扩压叶栅性能的影响，工程热物理学报，2005，26(5)：761—763．
[22]周海等，跨音风扇转子叶片抽吸气数值实验探索，航空动力学报，第19卷第3期，2004．6．
[23]Yangping Song, Fuchen, Jun Yang and Zhongqi Wang, A Numerical Investigation Of Boundary Layers Suction In Compound Lean Compressor Cascades, ASME Turbo Expo 2005, GT2005-68441.
[24]陈浮等，附面层吸除对压气机叶栅稠度特性影响，工程热物理学报，第26卷第2期，2005．3．
[25] 庄平、俞镔、谭春青、张伟，“IET跨音速平面叶栅风洞使用说明(透平风洞鉴定材料之二)”，中国科学院工程热物理研究所，1995．
[26] 彭泽琰，刘刚，《航空燃气轮机原理》，国防工业出版社，2000．
[27] 西北工业大学编，《航空发动机气动参数测量》，国防工业出版社，1980.12．
[28] 童志庭等，虚拟仪器概念在压气机实验研究中的实现，工程热物理学报，第05期，2003．
[29] H.史里西廷，《边界层理论》，科学出版社，1991．
[30] 刘天宝，《流体力学及叶栅理论》，机械工业出版社，1983．