一体化过渡段大叶片对涡轮部件气动影响研究

推进技术 ›› 2017, Vol. 38 ›› Issue (4): 779-786.

一体化过渡段大叶片对涡轮部件气动影响研究

杨杰,刘冬华,潘尚能

中国航空动力机械研究所，湖南株洲 412002,中国航空动力机械研究所，湖南株洲 412002,中国航空动力机械研究所，湖南株洲 412002

发布日期:2021-08-15
作者简介:杨杰，男，博士，工程师，研究领域为涡轮气动设计与研究。

Effects of Large Vanes in Integrated Inter-Turbine Duct on Turbine Aerodynamic Performanace

AVIC Aviation Powerplant Research Institute，Zhuzhou 412002，China,AVIC Aviation Powerplant Research Institute，Zhuzhou 412002，China and AVIC Aviation Powerplant Research Institute，Zhuzhou 412002，China

Published:2021-08-15

摘要/Abstract

摘要： 为了理清一体化过渡段中大叶片的引入对涡轮部件气动性能和流动情况造成的影响，以带一体化动力涡轮过渡段的发动机的整个涡轮部件为研究对象，通过采用数值模拟的方法对其流动进行了研究。研究结果表明在地面起飞和最大巡航两种发动机工作状态下，一体化过渡段中大叶片的引入对低压涡轮和动力涡轮的性能均有显著影响，膨胀比和功率的影响量级达到1%；低涡动叶和动涡一导轴向力的影响量级分别为2%和5%；动涡一导和动涡一动进口气流角的影响量级分别为0.5°和2.5°。由于地面和空中两种状态下动力涡轮和排气支板的工作状态不同，故一体化过渡段大叶片的引入对其气动损失的影响机理不同，从而造成其损失和效率的变化趋势和量级不同。

关键词: 涡轮；一体化过渡段；大叶片；气动影响；地面起飞；最大巡航

Abstract: In order to clarify the aerodynamic effects on the turbine caused by the imported large vanes，the whole turbine of a certain engine with a power turbine integrated inter-turbine duct (IITD) was taken as the research object，and the flow field was numerically simulated and researched by means of CFD. The research results show that both on the ground takeoff and max cruise conditions，the imported large vanes in IITD bring obvious effects on the LP turbine and power turbine performance，e.g. 1% magnitude for pressure ratio and power; 2% and 5% magnitude for the axial force of the LP turbine stator and power turbine 1st rotor; 0.5 and 2.5 degrees magnitude for the power turbine 1st stator and 1st rotor. As the operation conditions of the power turbine and exhaust struts are distinct on ground and aerial status，the effect mechanism of the imported large vanes in ITTDs on their aerodynamic loss is different，and thus the aerodynamic loss and efficiency show inconsistent varying trend and magnitude.

Key words: Turbine；Integrated inter-turbine duct；Large vanes；Aerodynamic effects；Ground takeoff；Max cruise

杨杰,刘冬华,潘尚能. 一体化过渡段大叶片对涡轮部件气动影响研究[J]. 推进技术, 2017, 38(4): 779-786.

YANG Jie,LIU Dong-hua,PAN Shang-neng. Effects of Large Vanes in Integrated Inter-Turbine Duct on Turbine Aerodynamic Performanace[J]. Journal of Propulsion Technology, 2017, 38(4): 779-786.

参考文献

[1] Martin J, Valery C, Linda S, et al. Experimental and Numerical Investigation of an Aerodynamically Loaded Guide Vane in a Turbine Duct[R]. ASME GT2011-46221.
[2] Sovran G, Klomp E D. Experimentally Determined Optimum Geometries for Rectilinear Diffusers with Rectangular, Conical or Annular Cross-Section[M]. Fluid Mechanics of Internal Flow, 1st edition, Elsevier: 270-319, 1967.
[3] Norris G, Dominy R G. Diffusion Rate Influences on Inter-Turbine Diffusers[J]. Journal of Power and Energy, 1997, 211 (3): 235-42.
[4] Grasel J, Pierre M, Demolis J. Parametric Inter-Turbine Duct Design and Optimization[C]. Hamburg: Proceedings of 25th International Congress of the Aero-Nautical Sciences, ICAS, 2006.
[5] Paul T, Craig W, Malak F, et al. Computational Study of Geometric Parameter Influence on Aggressive Inter-Turbine Duct Performance[R]. ASME GT2010-23604.
[6] Zhang Y F, Hu S Z, Zhang X F, et al. Flow Control in an Aggressive Inter-Turbine Duct Using Low Profile Vortex Generators[R]. ASME GT 2012-69951.
[7] Pedro D, Miguel A, Jorge P, et al. Design and Development of the Inter-Turbine Structure and Power Turbine for the Mtr390-E Turboshaft Engine[R]. ASME GT 2013-94021.
[8] Gardner W B. Energy Efficient Engine (E3) Technology Status[R]. AIAA 82-1052.
[9] Howard H, Peter B V. Aggressive Intermediate Turbine Duct Aerodynamics for Competitive and Environmentally Friendly Jet Engines[C]. Vienna: ECCOMAS, 2008.
[10] EU Transport Research. Aero Thermal Investigations on Turbine End-Walls and Blades II[EB/OL]. http://www.transport-research. info/ project/aerothermal-investigations-turbine-end-walls-and-blades-ii.
[11] 孙志刚, 黄洪艳, 谭青春, 等. 某型燃机涡轮过渡段流场优化设计[J]. 工程热物理学报, 2008, 29(6):940-943.
[12] 唐洪飞, 黄洪雁, 韩万金. 大子午扩张涡轮过渡段的子午型线[J]. 推进技术, 2009, 30(4): 439-445. (TANG Hong-fei, HUANG Hong-yan, HAN Wan-jin. Meridional Passage Contour of a Large Meridional Expansion Turbine[J]. Journal of Propulsion Technology, 2009, 30(4): 439-445.)
[13] 陈江, 朴龙贤, 杜刚, 等. 涡轮过渡段气动性能数值优化[J]. 工程热物理学报, 2011, 32(2): 210-214.
[14] 杨金广, 吴虎, 杨鹏, 等. 基于二维优化方法的涡轮过渡段流道设计[J]. 推进技术, 2013, 34(2):161-167. (YANG Jin-guang, WU Hu, YANG Peng, et al. Design of Intermediate Turbine Flowpath Based on Two- Dimensional Optimization Method[J]. Journal of Propulsion Technology, 2013, 34(2): 161-167.)
[15] Emil G. Research on the Aerodynamics of Intermediate Turbine Diffusers[J]. Progress in Aerospace Sciences, 2011, 47(4): 249-279.
[16] Hu S, Zhang X F, Benner M, et al. Geometric Optimization of Aggressive Inter-Turbine Ducts[R]. ASME IMECE 2010-37323.
[17] Wallin F, Eriksson L E. Response Surface-Based Transition Duct Shape Optimization[R]. ASME GT 2006-90978.　　　　　　　　　　　　　*　收稿日期:2015-12-07；修订日期:2016-01-06。作者简介:杨杰,男,博士,工程师,研究领域为涡轮气动设计与研究。E-mail: yjguy@126.com(编辑:史亚红)