高负荷涡轮进口导向叶片叶型设计及验证

张绍文; 石建成; 李维

doi:10.13224/j.cnki.jasp.2021.01.021

高负荷涡轮进口导向叶片叶型设计及验证

doi: 10.13224/j.cnki.jasp.2021.01.021

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出版历程
- 收稿日期: 2020-08-12
- 刊出日期: 2021-01-28

Design and validation of high-lift turbine nozzle guide vane profile

Hunan Key Laboratoryof Turbomachinery on Medium and Small Aero-Engine,Hunan Aviation Powerplant Research Institute,Aero Engine Corporation of China,Zhuzhou Hunan 412002,China

摘要

摘要: 针对涡轮进口导向叶片进口马赫数低、前部负荷小的特点,采用前缘截断思路构建了高负荷涡轮叶型,并采用Pritchard 11参数法进行重构设计。采用数值计算和平面叶栅试验开展了研究和分析。结果表明：高负荷叶型吸力面前缘马赫数显著提升,增加了叶片前部负荷。喉部峰值马赫数基本不变,但位置前移,负荷分布均匀性提高。叶型的马赫数特性和攻角特性表明,高负荷叶型在不同攻角和马赫数下,均能获得较低的总压损失,其中在设计马赫数,叶型负荷提升1倍的情况下,总压损失系数降低259%。
- 燃气涡轮 /
- 进口导向叶片(NGV) /
- 高负荷叶型 /
- 叶型设计 /
- 气动损失
Abstract: A method for high-lift turbine blade design based on Pritchard 11 parameters method was introduced for turbine nozzle guide vane working under low entrance Mach number and typically low lift at front part of the blade. A series of high lift nozzle guide vane profile were designed and investigated using numerical calculation, and validated by linear cascade test. Results showed that the blade loading of high-lift profile was more uniform due to increase of Mach number at front part of the suction side, and the throat suction moved forward. The Mach number characteristic and attack angle characteristic showed that the highly-loaded blades generated lower total pressure loss. The pressure loss coefficient of high-lift profile was 259% lower under design condition than that of the datum profile.
- gas generator turbine /
- nozzle guide vane(NGV) /
- high-lift profile /
- ,profile design /
- aerodynamic loss

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参考文献(18)

[1]	ZWEIFEL O.Optimum blade pitch for turbomachines with special reference to blades of great curvature［J］.The Engineers Digest,1946,7:358-360.
[2]	HOWELL R J,HODSON H P,SCHULTE V,et al.Boundary layer development in the BR710 and BR715 LP turbines:the implementation of high-lift and ultra-high-lift concepts［J］.Journal of Turbomachinery,2002,124(3):385-392.
[3]	PRAISNER T J,GROVER E A,KNEZEVICI D C,et al.Toward the expansion of low-pressure-turbine airfoil design space［R］.ASME Paper GT2008-50898,2008.
[4]	HOHEISEL H,KIOCK R,LICHTFU H J,et al.Influence of free stream turbulence and blade pressure gradient on boundary layer and loss behavior of turbine cascades［R］.New York:ASME International Gas Turbine Conference and Exhibit,1986.
[5]	ZHANG X F,VERA M,HODSON H P,et al.Separation and transition control on an aft-loaded ultra-high-lift lp turbine blade at low Reynolds numbers:low-speed investigation［J］.Journal of Turbomachinery,2006,128(6):517-527.
[6]	ZORIC T,POPOVIC I,SJOLANDER S A,et al.Comparative investigation of three highly loaded LP turbine airfoils:Part Ⅰ measured profile and secondary losses at design incidence［R］.ASME Paper GT2007-27537,2007.
[7]	ZORIC T,POPOVIC I,SJOLANDER S A,et al.Comparative investigation of three highly loaded lp turbine airfoils:Part Ⅱ measured profile and secondary losses at off-design incidence［R］.ASME Paper GT2007-27538,2007.
[8]	张华良,谭春青,董学智,等.超高负荷涡轮弯曲叶栅的实验研究［J］.航空动力学报,2009,24(10):2314-2318. ZHANG Hualiang,TAN Chunqing,DONG Xuezhi,et al.Experimental investigation on the influence of bowed blade in ultra-highly loaded turbine cascade［J］.Journal of Aerospace Power,2009,24(10):2314-2318.(in Chinese)
[9]	杨林,乔渭阳,罗华玲,等.低雷诺数高负荷低压涡轮叶型的气动设计［J］.航空动力学报,2013,28(5):1019-1028. YANG Lin,QIAO Weiyang,LUO Hualing,et al.Aerodynamic design of highly-loaded blade in low-pressure turbine with low Reynolds number［J］.Journal of Aerospace Power,2013,28(5):1019-1028.(in Chinese)
[10]	孙爽,雷志军,卢新根,等.基于表面粗糙度的超高负荷低压涡轮叶片附面层控制［J］.航空动力学报,2016,31(4):836-846. SUN Shuang,LEI Zhijun,LU Xingen,et al.Boundary layer control of ultra-high-lift low pressure turbine blade with surface roughness［J］.Journal of Aerospace Power,2016,31(4):836-846.(in Chinese)
[11]	董明,葛宁,陈云.跨声速涡轮叶栅激波损失控制方法［J］.航空动力学报,2018,33(5):1226-1235. DONG Ming,GE Ning,CHEN Yun,Shock loss control methods for transonic turbine cascades［J］.Journalof Aerospace Power,2018,33(5):1226-1235.(in Chinese)
[12]	GIER J,ARDEY S.On the impact of blade count reduction on aerodynamic performance and loss generation in a three-stage LP turbine［R］.ASME Paper 2001-GT-0197,2001.
[13]	HASELBACH F,SCHIFFER H P,HORSMAN M,et al.The application of ultra high lift blading in the BR715 LP turbine［J］.Journal of Turbomachinery,2002,124(1):45-51.
[14]	陈云,王雷,王刚.大涵道比发动机多级低压涡轮气动设计［J］.航空发动机,2013,39(4):51-55. CHEN Yun,WANG Lei,WANG Gang.Aerodynamic design of multistage low pressure turbine for high bypass ratio aeroengine［J］.Aeroengine,2013,39(4):51-55.(in Chinese)
[15]	BUNKER R S.A review of shaped hole turbine film-cooling technology［J］.Journal of Heat Transfer,2005,127(4):441-453.
[16]	KOFF B L,KOFF B L.Gas turbine technology evolution:a designer’s perspective［J］.Journal of Propulsion and Power,2004,20(4):577-595.
[17]	TOM S,VIGER Y.Aerodynamics heat transfer materials and mechanics［M］∥BOGARD D G,THOLE K A.Film Cooling.Restion,US:AIAA,2014.
[18]	STEPHAN B,KRCKELS J,GRITSCH M.Investigation of aerodynamic losses and film cooling effectiveness for a NGV profile［R］.ASME Paper GT2010-22810,2010.