|Table of Contents|

Optimization design of a low aspect ration gas turbine for curved guide vane(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2019年06期
Page:
23-28
Research Field:
研究与技术
Publishing date:

Info

Title:
Optimization design of a low aspect ration gas turbine for curved guide vane
Author(s):
MAO Kai;  LI Changhuan;  ZHANG Dan;  JIANG Jianyuan
(Xi’an Aerospace Propulsion Institute,Xi’an 710100, China)
Keywords:
low aspect ration;  curved guide vane;  numerical simulate;  optimization
PACS:
V434.21
DOI:
-
Abstract:
In order to further improve the internal flow field and improve the turbine efficiency, a sub-sonic low aspect gas turbine for a certain rocket engine was taken as research object, the optimization was developed in this paper through the adjustment of meridional endwall’s curvature and the design of curved guide vanes.Its function is to reduce the secondary flow loss and optimize the guide outlet pressure distribution at guide vanes outlet, thereby reducing the leak loss at blade top.Base on the hexahedron grid, CFX flow field analysis software was used to calculate the turbine performance.The result shows that the optimized turbine efficiency of single channel gap-less structure increases by 1.4%; the absolute and relative airflow angles at hub and tip of the blade are significantly increased after the curved blade was used, the airflow angle in the middle of the blade is reduced, and the overall distribution is more uniform, the flow separation of the prototype structure is eliminated; the relative leakage of blade tip with maze structure gap decreases by 7% to 4.75%,turbine overall efficiency increases by 5.9%.

References:

[1] 王仲奇, 韩万今, 徐文远, 等.在低展弦比透平静叶栅中叶片的弯曲作用[J].工程热物理学报, 1990, 11(3):255-262.
[2] TAN C Q, ZHANG H L, XIA H D, et al.Blade bowing effect on aerodynamic performance of a highly loaded turbine cascade[J].Journal of Propulsion and Power, 2010, 26(3): 604-608.
[3] HAN W J, WANG Z Q, TAN C Q, et al. Effects of leaning and curving of blades with high turning angles on the aerodynamic characteristics of turbine rectangular Cascades[J].Journal of Turbomachinery, 1994, 116(3): 417-424.
[4] 张晓辉, 陈绍文, 李燕飞.基于弯曲叶片的燃气涡轮导叶数值研究[J].推进技术, 2016, 37(3):443-448.
[5] 谢婕, 夏晨, 张远森, 等.低展弦比微型轴流涡轮弯叶片设计[J].南京航空航天大学学报, 2015, 47(1):160-166.
[6] 李斌, 王晓锋, 陈本森, 等.大叶顶间隙高效率火箭发动机涡轮设计[J].宇航学报, 2009, 30(2):695-698.
[7] 郑晓宇, 林奇燕, 王磊.小型部分进气亚声速涡轮流动损失研究及优化[J].火箭推进, 2017, 43(1):32-37.ZHENG X Y, LIN Q Y, WANG L.Research and optimization for flow loss of a small partial admission subsonic turbine[J].Journal of Rocket Propulsion, 2017, 43(1):32-37.
[8] 严俊峰, 逯婉若.冲击式涡轮内部流动数值研究[J].火箭推进, 2009, 35(1):31-35.YAN J F, LU W R.Numerical analysis of inner flow field for an impulse turbine[J].Journal of Rocket Propulsion, 2009, 35(1):31-35.
[9] 高杰, 郑群, 李义进.动叶顶部蜂窝面迷宫密封对涡轮级气动性能的影响[J].航空动力学报, 2012, 27(1):160-168.
[10] 贾惟, 刘火星.涡轮叶栅叶冠泄漏流动数值研究[J].推进技术, 2013, 34(3):316-325.
[11] 付云峰, 宋彦萍, 陈聪, 等. 叶顶布置蜂窝的涡轮平面叶栅间隙泄漏流动研究[J].工程热物理学报, 2017, 38(1): 68-73.
[12] 王晓锋, 李昌奂, 韩飞, 等. 动叶顶部间隙结构对涡轮性能影响的数值分析[J].火箭推进, 2013, 39(2): 24-28.WANG X F, LI C H, HAN F, et al. Numerical analysis on influence of rotor tip clearance structure on turbine performance[J].Journal of Rocket Propulsion, 2013, 39(2): 24-28.
[13] 胡骏, 吴铁鹰, 曹人靖.航空叶片机原理[M].北京:国防工业出版社, 2006.
[14] 石靖,周勇,李维.低展弦比高温涡轮导叶外端壁收缩与倾斜叶片组合设计[J].南华动力,1999(2):1-6

Memo

Memo:
-
Last Update: 2019-12-20