弯叶片对超声速流动的影响

姚宏; 周逊; 王仲奇

doi:10.7652/xjtuxb201609011

您当前的位置：

首页 >

文章列表页 >

弯叶片对超声速流动的影响

更新时间：2025-07-09

- 弯叶片对超声速流动的影响
- Effects of Bowed Blade Design on Supersonic Flow
- 西安交通大学学报 2016年50卷第9期页码：66-73
- 作者机构：
  
  哈尔滨工业大学能源科学与工程学院,哈尔滨,150001
- 作者简介：
- 基金信息：
  
  : 2016-01-01。作者简介: 姚宏(1977—),男,博士生;周逊(通信作者),男,教授。基金项目: 国家自然科学基金优秀创新研究群体资助项目(51421063)
- DOI：10.7652/xjtuxb201609011
  中图分类号： TK26
- 网络首发：2016-09-10，
  
  纸质出版：2016
- 稿件说明：
移动端阅览
姚宏, 周逊, 王仲奇. 弯叶片对超声速流动的影响[J]. 西安交通大学学报, 2016,50(9):66-73.

Effects of Bowed Blade Design on Supersonic Flow[J]. 2016, 50(9): 66-73.
姚宏, 周逊, 王仲奇. 弯叶片对超声速流动的影响[J]. 西安交通大学学报, 2016,50(9):66-73. DOI： 10.7652/xjtuxb201609011.

Effects of Bowed Blade Design on Supersonic Flow[J]. 2016, 50(9): 66-73. DOI： 10.7652/xjtuxb201609011.

摘要

针对弯叶片可以减少激波损失且作用机理不明的问题

对工业汽轮机中跨声速、超声速流动条件下弯叶栅进行了数值研究

分析了弯叶片对流场结构的影响

并为此设计了叶片弯角分别为0°、±5°、±10°、±15°、±20°、±25°的11种正、反弯角静叶方案

弯叶片弯高为50%展向

叶根与叶顶弯角相同。研究结果表明:弯叶片改变了激波结构

这一作用在不同的超声速条件下是相同的; 在压比较大、流量较小的条件下

工业汽轮机采用超声速设计是可行的。弯叶片在超声速条件下可以降低叶栅损失

且存在最优值; 相对于亚声速流动

超声速动叶吸力面上的损失减小; 11种方案下静叶片正弯设计对动叶压力面影响较小

静叶片反弯设计对动叶压力面与吸力面均有较大影响。该结果可为工业汽轮机超声速设计、研究提供参考。

Abstract

A bowed blade under the conditions of transonic flow and supersonic flow in an industrial steam turbine is numerically investigated to reveal the mechanism of lowering shock loss for a bowed blade. Analyzing the influence of a bowed blade on a flow field structure

11 stator schemes of a straight blade and bowed blades are designed with bowed angles of 0°

±5°

±10°

±15°

±20° and ±25°. The relative bowed height of a blade is 50% span

while blade root and blade tip have the same bowed angle. The results show that a bowed blade changes the shock structure

which is the same under different supersonic flows. It is feasible to conduct supersonic flow design for an industrial steam turbine under the condition that the stage pressure is rather high while the flow is rather small. Under the condition of supersonic flow

a bowed blade enables to decrease energy loss and there exists an optimum value. The energy loss on the supersonic rotor decreases compared with that on subsonic rotor. In the 11 schemes

positively bowed stators exert slight effects on the pressure side of the rotor

while the negatively bowed stators exert obvious effects on both the pressure and suction sides of the rotor.

关键词

Keywords

references

MOUSTAPHA S H, PARON G J, WADE J H T. Secondary flow in cascades of highly loaded turbine blades [J]. ASME Journal of Engineering for Gas Turbine and Power, 1985, 105(10): 1031-1038.

周凡贞, 王世勇, 丁晓娟, 等. 涡轮高载荷动叶片设计及级三维流场数值分析 [J]. 推进技术, 2004, 25(1): 62-65.

ZHOU Fanzhen, WANG Shiyong, DING Xiaojuan, et al. Design and 3-D numerical analysis of highly loaded turbine rotor blade [J]. Journal of Propulsion Technology, 2004, 25(1): 62-65.

邓庆锋, 郑群, 张海, 等. 可控涡设计高负荷涡轮二次流旋涡结构及损失分析 [J]. 中国电机工程学报, 2012, 32(20): 108-114, 147.

DENG Qingfeng, ZHENG Qun, ZHANG Hai, et al. Analysis of secondary flow vortex structure and losses in a high load turbine designed by the controlled vortex method [J]. Proceedings of the CSEE, 2012, 32(20): 108-114, 147.

WOLF T, KOST F, JANKE E, et al. Experimental and numerical studies on highly loaded supersonic axial turbine cascades: GT2010-23808 [R]. New York, USA: ASME, 2010.

HURA H S, SAEIDI R, GIEL P, et al. Design and test results of a ultra high loaded single stage high pressure turbine, GT2013-94055 [R]. New York, USA: ASME, 2013.

TSUJITA H, MIZUKI S, YAMAMOTO A. Numerical investigation of blade profile effects on aerodynamic performance of ultra-highly loaded turbine cascades, GT2004-53429 [R]. New York, USA: ASME, 2004.

TSUJITA H, MIZUKI S, YAMAMOTO A. Numerical investigation of effects of incidence angle on aerodynamic performance of ultra-highly loaded turbine cascade, GT2006-90939 [R]. New York, USA: ASME, 2006.

TSUJITA H, YAMAMOTO A. Complex secondary flow and associated loss generation in ultra-highly loaded turbine cascade, GT2010-22594 [R]. New York, USA: ASME, 2010.

TSUJITA H. Influence of blade profile on secondary flow in ultra-highly loaded turbine cascades at off-design incidence, GT2013-95150 [R]. New York, USA: ASME, 2013.

孙奇, 李军, 孔祥林, 等. 后加载和高负荷前加载叶型气动性能的试验研究 [J]. 西安交通大学学报, 2007, 41(1): 23-27.

SUN Qi, LI Jun, KONG Xianglin, et al. Experimental investigations on the aerodynamic performance of the aft-loaded and fore-loaded turbine cascades [J]. Journal of Xi'an Jiaotong University, 2007, 41(1): 23-27.

CORRIVEAU D, SJOLANDER S A. Influence of loading distribution on the performance of transonic HP turbine blades, GT2003-38079 [R]. New York, USA: ASME, 2003.

MEINGAST M, KIELB R E, THOMAS J P. Preliminary flutter design method for supersonic low pressure turbines, GT2009-59177 [R]. New York, USA: ASME, 2009.

SONG P, SUN J, WANG K. Blade shape optimization of transonic axial flow fan in terms of sectional profiles and stacking line, GT2014-25816 [R]. New York, USA: ASME, 2014.

刘洋, 钟易成, 惠广晗, 等. 超声速涡轮动叶设计方法研究 [J]. 航空发动机, 2012, 38(4): 47-52.

LIU Yang, ZHONG Yicheng, HUI Guanghan, et al. Supersonic turbine rotor blade design method [J]. Aeroengine, 2012, 38(4): 47-52.

高雷, 郑群, 王超, 等. 船用推进器低压透平末两级改型设计 [J]. 推进技术, 2013, 34(6): 768-774.

GAO Lei, ZHENG Qun, WANG Chao, et al. Retrofit for last two stages of a marine low pressure steam turbine [J]. Journal of Propulsion Technology, 2013, 34(6): 768-774.

方祥军, 刘思永, 王屏, 等. 大扩张通道超声高载荷对转涡轮动叶三维设计方法研究 [J]. 航空学报, 2007, 28(1): 25-31.

FANG Xiangjun, LIU Siyong, WANG Ping, et al. Research of 3D design method for rotor of supersonic high loaded contra rotating turbine with large expansive meridional channel [J]. Acta Aeronautica et Astronautica Sinica, 2007, 28(1): 25-31.

杨金广, 吴虎, 杨鹏, 等. 基于二维优化方法的涡轮过渡流道设计 [J]. 推进技术, 2013, 34(2): 161-167.

YANG Jinguang, 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.

谭杰, 金捷. 跨声速和超声速流中激波/边界层干扰数值模拟 [J]. 推进技术, 2010, 31(4): 394-400.

TAN Jie, JIN Jie. Numerical simulation of shock wave/turbulent boundary layer interactions in transonic and supersonic flows [J]. Journal of Propulsion Technology, 2010, 31(4): 394-400.

胡应交, 王松涛, 王仲奇. 吸附式低反动度超、跨音速轴流压气机气动设计原理及其验证 [J]. 推进技术, 2013, 34(9): 1179-1187.

HU Yingjiao, WANG Songtao, WANG Zhongqi. Analysis and verification of aerodynamic design principle of the low-reaction and aspirated supersonic or transonic compressors [J]. Journal of Propulsion Technology, 2013, 34(9): 1179-1187.

王松涛, 胡应交, 王仲奇. 吸附式低反动度轴流压气机气动设计原理 [J]. 航空动力学报, 2014, 29(2): 350-362.

WANG Songtao, HU Yingjiao, WANG Zhongqi. Aerodynamic design principle of aspirated and low-reaction axial-compressors [J]. Journal of Aerospace Power, 2014, 29(2): 350-362.

王松涛, 王仲奇, 冯国泰. 弯曲叶片降低能量损失的涡动力学机制 [J]. 哈尔滨工业大学学报, 2002, 34(5): 607-613, 670.

WANG Songtao, WANG Zhongqi, FENG Guotai. Reduction of energy loss by bowed blades [J]. Journal of Harbin Institute of Technology, 2002, 34(5): 607-613, 670.

杨彤, 王松涛, 姜斌. 弯曲叶片造型对涡轮叶栅作用力影响的非定常数值研究 [J]. 推进技术, 2013, 34(6): 760-767.

YANG Tong, WANG Songtao, JIANG Bin. Unsteady numerical study of effects on turbine blade forces for the bowed blade [J]. Journal of Propulsion Technology, 2013, 34(6): 760-767.

张华良, 王松涛, 王仲奇. 对不同转角扩压叶栅内弯叶片的数值模拟 [J]. 推进技术, 2007, 28(4): 362-366, 387.

ZHANG Hualiang, WANG Songtao, WANG Zhongqi. Numerical simulation for the influence of bowed blade in compressor cascades with different turning angles [J]. Journal of Propulsion Technology, 2007, 28(4): 362-366, 387.

谭春青, 张华良, 董学智, 等. 在高负荷涡轮叶栅中应用弯叶片控制流动分离的实验研究 [J]. 工程热物理学报, 2009, 30(9): 1467-1471.

TAN Chunqing, ZHANG Hualiang, DONG Xuezhi, et al. A numerical investigation of application of bowed blade to control flow separation on highly loaded turbine cascades [J]. Journal of Engineering Thermophysics, 2009, 30(9): 1467-1471.

刘凤君, 顾发华, 杨弘, 等. 弯扭叶片对涡轮三维压力场的影响 [J]. 工程热物理学报, 1996, 17(增刊): 48-51.

LIU Fengjun, GU Fahua, YANG Hong, et al. Three dimensional pressure field in the passage [J]. Journal of Engineering Thermophysics, 1996, 17(s): 48-51.

浏览量

下载量

CSCD

文章被引用时，请邮件提醒。

提交

工具集

关联资源

工业汽轮机补汽结构对压力损失的影响及优化

垫升轴流风扇的静叶优化设计及内部流动机理数值研究

超临界水异常区域热力学特性研究

张角凹坑气膜孔对双层壁气膜冷却特性的影响

采用试验设计方法的第三代CO2气体箔轴承箔片几何参数敏感性分析