叶身/端壁融合技术工况的适用性

田勇; 季路成; 李伟伟; 伊卫林; 肖云汉

叶身/端壁融合技术工况的适用性

1.
中国科学院工程热物理研究所先进能源动力重点实验室, 北京 100190
2.
中国科学院大学, 北京 100049
3.
北京理工大学宇航学院, 北京 100081

基金项目: 国家自然科学基金(51006100,51176012)

计量
- 文章访问数: 1634
- HTML浏览量: 12
- PDF量: 1164
- 被引次数: 0
出版历程
- 收稿日期: 2012-07-26
- 刊出日期: 2013-08-28

Applicability of blended blade and endwall under different operating conditions

1.
Key Laboratory of Advanced Energy and Power, Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China
2.
University of Chinese Academy of Sciences, Beijing 100049, China
3.
School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China

摘要

摘要: 在前期提出并初步验证了叶身/端壁融合(BBEW)技术效果的基础上,以NASA Rotor 67为例实施BBEW改型,研究了100%,90%和80%三种转速,海平面与万米高空两种不同雷诺数工况条件下BBEW技术的实施效果.数值结果表明:相对于原型,BBEW改型在几乎所有工况范围内均显现出总压比、效率等性能提升.在低转速和低雷诺数下的收益更为明显,效率收益可达0.6%~0.8%.这表明BBEW技术具有宽广的工况适用性,将是弯、掠以外叶轮机全三维叶片造型的又一重要方面.
- 叶身/端壁融合(BBEW) /
- 二面角原理 /
- 倒圆 /
- 角区分离 /
- 叶轮机
Abstract: To continue the previous work,NASA rotor 67 redesigned with blended blade and endwall (BBEW) was further studied and focused on assessing the influences of three different rotating speeds,i.e.100%,90% and 80% of full speed,at two different Reynolds numbers,under ground condition and 10000-meter high altitude condition.Numerical tests show that under almost all the operating conditions in relation to original model,BBEW model can improve performance such as total pressure ratio and isentropic efficiency,particularly under conditions of low rotating speeds and low Reynolds numbers,with the efficiency up by 0.6% to 0.8%.This indicates that BBEW has broad applications under operating conditions,serving as another important aspect of full 3-D blade in addition to sweep and bow techniques.
- blended blade and endwall(BBEW) /
- rules of dihedral /
- fillet /
- corner separation /
- turbomachinery

HTML

参考文献(15)

[1]	JI Lucheng,SHAO Weiwei,YI Weilin,et al.A model for describing the influences of SUC-EW dihedral angle on corner separation [C]//Proceedings of the ASME Turbo Expo 2007.Montreal Germany:ASME,2007:219-228.
[2]	季路成,伊卫林,田勇,等.一种叶轮机械叶片与端壁融合设计方法:中国,CN102094847A [P].2010-06-15. JI Lucheng,YI Weilin,TIAN Yong,et al.A method of designing blended blade and endwall for turbomachinery:China,CN102094847A [P].2010-06-15.(in Chinese)
[3]	季路成,田勇,李伟伟,等.叶身-端壁融合技术研究[J].航空发动机,2012,39(6):10-17. JI Lucheng,TIAN Yong,LI Weiwei,et al.Study on blended blade and endwall technique[J].Aeroengine,2012,39(6):10-17.(in Chinese)
[4]	Curlett B P.The aerodynamic effect of fillet radius in a low speed compressor cascade [R].Washington,DC:NASA Technical Memorandum,105347,1991.
[5]	Hoeger M,Schmidt-Eisenlohr U.Numerical simulation of the influence of a bulb and a fillet on the secondary flow in a compressor cascade[J].Task Quarterly,2002,6(1):25-38.
[6]	Hoeger M,Baier R D,Müller R,et al.Impact of a fillet on diffusing vane endwall flow structure [R].Honolulu,US:The 11th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery,ISROMAC 2006-057,2006.
[7]	康顺,孙丽萍.叶根倒角对离心叶轮气动性能的影响[J].工程热物理学报.2009,30(1):41-43. KANG Sun,SUN Liping.Influence of root fillet on the aerodynamic performance of centrifugal impeller[J].Journal of Engineering Thermophysics,2009,30(1):41-43.(in Chinese)
[8]	Goodhand M N,Miller R J.The impact of real geometries on three-dimensional separations in compressors[J].Journal of Turbomachinery,2012,134(2):021007.1-021007.8.
[9]	Duden A,Raab I,Fottner L.Controlling the secondary flow in a turbine cascade by three-dimensional airfoil design and endwall contouring[J].Journal of Turbomachinery,1999,121(2):191-199.
[10]	Mahmood G I,Acharya S.Measured endwall flow and passage heat transfer in a linear blade passage with endwall and leading edge modifications [C]//Proceedings of ASME Turbo Expo 2007.Montreal,Canada:ASME,2007:917-930.
[11]	Nagel M G,Baier R D.Experimentally verified numerical optimization of a three-dimensional parametrized turbine vane with nonaxisymmetric end walls[J].Journal of Turbomachinery,2005,127(2):380-387.
[12]	Gregory-Smith D,Bagshaw D,Ingram G,et al.Using profiled endwalls,blade lean and leading edge extensions to minimise secondary flow [C]//Proceedings of ASME Turbo Expo 2008.Berlin,Germany:ASME,2008:1301-1311.
[13]	Bagshaw D A,Ingram G L,Gregory-Smith D G,et al.An experimental study of three-dimensional turbine blades combined with profiled endwalls[J].Journal of Power and Energy,2008,222(1):103-110.
[14]	Bagshaw D A,Ingram G L,Gregory-Smith D G,et al.The design of three-dimensional turbine blades combined with profiled endwalls[J].Journal of Power and Energy,2008,222(1):93-102.
[15]	Chima R V.Viscous three-dimensional calculations of transonic fan performance [R].Washington,DC:NASA Technical Memorandum,103800,1991.