高负荷压气机径向间隙工程优化设计与验证
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摘要
为减小径向间隙对高负荷压气机气动性能的负面影响,从工程实用角度出发,研究了压气机运转周期内转子叶尖间隙变化规律,对不同间隙对压气机性能的影响进行了对比分析,综合考虑气动性能和结构工程设计,对转子叶尖间隙进行了优化设计。基于可调静叶实际具体结构,研究了可调静叶圆台不同位置处间隙在不同转速下的变化规律,采用全三维数值模拟对不同静叶间隙气动性能进行了对比分析,并开展方案优化设计。将径向间隙优化设计方法应用于高负荷压气机设计中,试验验证表明:该压气机相对于第四代发动机的压气机平均级压比提高了16%,效率提高了1%,三维特性预估准确,验证了压气机转、静子叶片间隙优化设计的合理性和有效性。
In order to reduce the negative impact of radial clearance on high load compressor aerodynamic performance,from an engineering application perspective,rotor tip clearance variation during compressor working period was studied and comparison analysis of different clearance impact on compressor performance was carried out. Rotor tip clearance was optimum designed considering aerodynamic performance and structural design.Based on practical structure,variable vane penny clearance change law at various speeds was studied. Clearance aerodynamic performance comparison analysis for different vanes was carried out using full 3 D CFD and concept optimum design has also been performed. The radial clearance optimization design method then was applied to a high load compressor design. Test validation shows that comparing with 4 th generation compressor,average stage pressure ratio has increased by 16% while efficiency has increased by 1%. 3 D characteristic prediction is correct.The optimum design of blade clearance is proved to be proper and effective.
In order to reduce the negative impact of radial clearance on high load compressor aerodynamic performance,from an engineering application perspective,rotor tip clearance variation during compressor working period was studied and comparison analysis of different clearance impact on compressor performance was carried out. Rotor tip clearance was optimum designed considering aerodynamic performance and structural design.Based on practical structure,variable vane penny clearance change law at various speeds was studied. Clearance aerodynamic performance comparison analysis for different vanes was carried out using full 3 D CFD and concept optimum design has also been performed. The radial clearance optimization design method then was applied to a high load compressor design. Test validation shows that comparing with 4 th generation compressor,average stage pressure ratio has increased by 16% while efficiency has increased by 1%. 3 D characteristic prediction is correct.The optimum design of blade clearance is proved to be proper and effective.
引文
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[2] Boyer K M. An Improved Streamline Curvature Approach for Off-Design Analysis of Transonic Axial Compression Systems[R]. ASME 2002-GT-30444.
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[8]蒋志军,兰发祥.可调静子叶片机匣间隙对轴流压气机性能的影响[J].燃气涡轮试验与研究,2012,25(2):21-23.
[9] Adamczyk J J,Celestina M L,Greitzer E M. The Role of Tip Clearance in High-Speed Fan Stall[J]. ASME Journal of Turbomachinery,1993,155(1):28-39.
[10] Suder K L,Celestina M L. Experimental and Computational Investigation of the Tip Clearance Flow in a Transonic Axial Compressor Rotor[R]. ASME 94-GT-365.
[11]王子登,王永明,黄国平.压气机转子叶尖间隙对其性能的影响[J],燃气涡轮试验与研究,2012,25(S0):31-35.
[12] Puterbaugh S L,Brendel M. Tip Clearance Flow-Shock Interaction in a Transonic Compressor rotor[R]. AIAA95-2549.
[13] Saha N,Ma R,William J,et al. Characterizing Unsteady Periodic Disturbances in the Tip Leakage Vortex of an Idealized Axial Compressor Rotor Blade[R]. AIAA2001-0386.
[14] Taylor S C,Steinetz B M,Oswald J J. Further Characterization of an Active Clearance Control Concept[R].AIAA 2007-5739.
[15]张龙,韩鹏卓,刘忠奎,等.航空发动机转子叶尖间隙及同心度变化规律研究[J].燃气涡轮试验与研究,2017,30(1):44-47.
[16]熊宇飞.转子叶尖间隙测量在风扇和压气机性能试验中的应用[J].航空发动机,2002,28(1):20-23.
[17]宁方飞.考虑真实几何复杂性的跨音压气机内部流动的数值模拟[D].北京:北京航空航天大学,2002.
[18] Ning F F,Xu L P. Numerical Investigation of Transonic Compressor Rotor Flow Using an Implicit 3D Flow Solver with One-Equation Spalart-Allmaras Turbulence Model[R]. ASME 2001-GT-0359.
[19]李清华,安利平,徐林,等.高负荷轴流压气机设计与试验验证[J].航空学报,2017,38(9).
[20]安利平,李清华,徐林,等.一种新型压气机叶片造型方法的平面叶栅试验验证[J].燃气涡轮试验与研究,2013,26(5):12-15.
[21]米攀,李清华,安利平.多级轴流压气机静子三维造型优化设计[J].燃气涡轮试验与研究,2017,30(5):13-17.
[2] Boyer K M. An Improved Streamline Curvature Approach for Off-Design Analysis of Transonic Axial Compression Systems[R]. ASME 2002-GT-30444.
[3] Jansen W. The Off-Design Analysis of Axial-Flow Compressors[J]. Journal of Engineering for Power,1967,102(66):453-462.
[4] Robbins W H,Dugan J F. Prediction of Off-Design Performance of Multi-Stage Compressors[R]. NASA-SP-36,1965.
[5] Smith L H. Axial Compressor Aerodesign Evolution at General Electric[J]. Journal of Turbomachinery,2002,124(3):321-330.
[6]胡江峰,竺晓程,杜朝辉.一种跨声速轴流压气机性能预测的数值方法[J].航空动力学报,2011,26(1):122-126.
[7]杜文海,吴虎,黄健.跨声速多级轴流压气机非设计性能预测[J],航空动力学报,2007,22(9):1481-1486.
[8]蒋志军,兰发祥.可调静子叶片机匣间隙对轴流压气机性能的影响[J].燃气涡轮试验与研究,2012,25(2):21-23.
[9] Adamczyk J J,Celestina M L,Greitzer E M. The Role of Tip Clearance in High-Speed Fan Stall[J]. ASME Journal of Turbomachinery,1993,155(1):28-39.
[10] Suder K L,Celestina M L. Experimental and Computational Investigation of the Tip Clearance Flow in a Transonic Axial Compressor Rotor[R]. ASME 94-GT-365.
[11]王子登,王永明,黄国平.压气机转子叶尖间隙对其性能的影响[J],燃气涡轮试验与研究,2012,25(S0):31-35.
[12] Puterbaugh S L,Brendel M. Tip Clearance Flow-Shock Interaction in a Transonic Compressor rotor[R]. AIAA95-2549.
[13] Saha N,Ma R,William J,et al. Characterizing Unsteady Periodic Disturbances in the Tip Leakage Vortex of an Idealized Axial Compressor Rotor Blade[R]. AIAA2001-0386.
[14] Taylor S C,Steinetz B M,Oswald J J. Further Characterization of an Active Clearance Control Concept[R].AIAA 2007-5739.
[15]张龙,韩鹏卓,刘忠奎,等.航空发动机转子叶尖间隙及同心度变化规律研究[J].燃气涡轮试验与研究,2017,30(1):44-47.
[16]熊宇飞.转子叶尖间隙测量在风扇和压气机性能试验中的应用[J].航空发动机,2002,28(1):20-23.
[17]宁方飞.考虑真实几何复杂性的跨音压气机内部流动的数值模拟[D].北京:北京航空航天大学,2002.
[18] Ning F F,Xu L P. Numerical Investigation of Transonic Compressor Rotor Flow Using an Implicit 3D Flow Solver with One-Equation Spalart-Allmaras Turbulence Model[R]. ASME 2001-GT-0359.
[19]李清华,安利平,徐林,等.高负荷轴流压气机设计与试验验证[J].航空学报,2017,38(9).
[20]安利平,李清华,徐林,等.一种新型压气机叶片造型方法的平面叶栅试验验证[J].燃气涡轮试验与研究,2013,26(5):12-15.
[21]米攀,李清华,安利平.多级轴流压气机静子三维造型优化设计[J].燃气涡轮试验与研究,2017,30(5):13-17.