超高负荷低压涡轮非定常特性实验

孙爽; 雷志军; 卢新根; 李伟; 朱俊强

doi:10.13224/j.cnki.jasp.2015.05.022

超高负荷低压涡轮非定常特性实验

doi: 10.13224/j.cnki.jasp.2015.05.022

1. 中国民航大学航空工程学院, 天津 300300;
2. 中国科学院工程热物理研究所燃气轮机实验室, 北京 100190

基金项目:

中国民航大学科研启动资金(2014QD22X,2014QD21X)

国家国际科技合作专项对R项目(2013DFR61080)

国家自然科学基金(51206163,51306176)

详细信息

作者简介:
孙爽(1983-),男,天津人,讲师,博士,主要从事航空发动机气动热力学研究.

中图分类号: V231
计量
- 文章访问数: 934
- HTML浏览量: 2
- PDF量: 717
- 被引次数: 0
出版历程
- 收稿日期: 2014-12-19
- 刊出日期: 2015-05-28

Experiment of an ultra-high-lift low pressure turbine performance at unsteady state

1. Department of Aviation Engineering, Civil Aviation University of China, Tianjin 300300, China;
2. Gas Turbine Laboratory, Institute of Engineering Thermophyiscs, Chinese Academy of Sciences, Beijing 100190, China

摘要

摘要: 针对某后加载超高负荷低压涡轮叶型的定常与非定常气动特性进行了实验研究.结果表明:由于上游尾迹的作用,在低来流雷诺数与来流湍流度下,尾迹诱导转捩叠加自然转捩可以抑制分离、降低叶型损失.在一个尾迹通过周期,由于尾迹诱导转捩的作用,附面层分离周期性地放大、缩小.同时在吸力面速度峰值点下游观测到了尾迹被割裂为两部分的现象,形成了一个主尾迹与一个副尾迹.副尾迹同样可以诱导转捩,但强度较低,对分离抑制效果有限.
- 低压涡轮 /
- 尾迹 /
- 附面层 /
- 分离 /
- 转捩
Abstract: The performance of an ultra-high-lift after loaded low pressure turbine (LPT) at steady and unsteady state has been investigated experimentally in the present paper. The experiment result show that both of the separation bubble and profile loss have been decreased by the wakes induced transition combined with the separation transition at low inlet Reynolds number and low inlet free stream turbulence intensity under the effect of upstream wakes. In one wake passing periodicity, the boundary layer separation is expanded and shrunken periodically due to the upstream wakes. It has also been seen that the wake is cut into 2 parts-a primary wake and a secondary wake, downstream the blade maximum camber. Even though the secondary wake can induce the transition, the suppression effect of separation is low due to the low wake intensity.
- low pressure turbine /
- wakes /
- boundary layer /
- separation /
- transition

HTML

参考文献(17)

[1]	Howell R J.Wake separation bubble interactions in low reynolds number turbomachinery[D].Cambridge:Cambridge University, 1999.
[2]	Vázquez R, Cadrecha D, Torre D.High stage loading low pressure turbines:a new proposal for an efficiency chart[R].ASME Paper 2003-GT-38374, 2003.
[3]	Hodson H P, Howell R J.The role of transition in high-lift low-pressure turbines for aero engines[J].Progress in Aerospace Sciences, 2005, 41(2005):419-514.
[4]	Hourmouziadis J.Aerodynamic design of low pressure turbines[R].AGARD Lecture Series 167, 1989.
[5]	Brunner S, Fottner L, Schiffer H P.Comparison of two highly loaded low pressure turbine cascades under the influence of wake-induced transition[R].ASME Paper GT-2000-268, 2000.
[6]	Schiffer H F.The application of ultra high lift blade in the BR715 LP turbine[J].Journal of Turbomach, 2002, 124(1):45-51.
[7]	Cumpsty N, Dong Y.Compressor blade boundary layers in the presence of wakes[R].ASME Paper 95-GT-443, 1995.
[8]	Halstead D E, Wisler D C.Boundary layer development in axial compressor and turbines:Part 1 of 4-composite picture[J].Journal of Turbomach, 1997, 119(2):114-127.
[9]	Halstead D E, Wisler D C.Boundary layer development in axial compressor and turbines:Part 3 of 4-LP turbines[J].Journal of Turbomach, 1997, 119(2):225-237.
[10]	ZHANG Xuefeng, Vera M.Separation and transition control on an aft-loaded ultra-high-lift LP turbine blade at low reynolds numbers:low-speed investigation[J].Journal of Turbomach, 2005, 128(3):517-527.
[11]	Stieger R D.The effects of wakes on separating boundary layers in low pressure turbines[D].Cambridge:Cambridge University, 2002.
[12]	Stieger R, Hodson H P.The transition mechanism of highly loaded LP turbine blades[R].ASME Paper GT-2003-38304, 2003.
[13]	綦蕾, 潘尚能, 李维, 等.1+1/2对转涡轮非定常流动数值模拟[J].航空动力学报, 2010, 25(8):1826-1835. QI Lei, PAN Shangneng, LI Wei, et al.Numerical simulation of unsteady flow in a vaneless counter-rotating turbine[J].Journal of Aerospace Power, 2010, 25(8):1826-1835.(in Chinese)
[14]	ZHANG Xuefeng.Separation and transition control on ultral-high-lift low pressure turbine blades in unsteady flow[D].Cambridge:Cambridge University, 2005.
[15]	Houtermans R, Coton T.Aerodynamic performance of a very high lift LP turbine blade with emphasis on separation prediction[J].Journal of Turbomach, 2004, 126(3):406-413.
[16]	Gostelow J P.Response of a laminar separation bubble to an impinging wake[R].ASME Paper GT2003-38972, 2003.
[17]	Volino R J.Separated flow transition under simulated low pressure turbine airfoil conditions:Part 1 mean flow and turbulence statistics[J].Journal of Turbomach, 2002, 124(4):645-55.