旋转半径和叶片安装角对动叶旋流冷却流动和传热特性的影响

杜长河; 范小军; 李亮; 丰镇平

doi:10.7652/xjtuxb201705006

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旋转半径和叶片安装角对动叶旋流冷却流动和传热特性的影响

更新时间：2025-07-09

- 旋转半径和叶片安装角对动叶旋流冷却流动和传热特性的影响
- Influences of Rotating Radius and Blade Setting Angle on Rotor Vortex Cooling Flow and Heat Transfer Characteristics
- 西安交通大学学报 2017年51卷第5期页码：37-42+148
- 作者机构：
  
  西安交通大学叶轮机械研究所,西安,710049
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb201705006
  中图分类号： TK474.7
- 网络首发：2017-05-10，
  
  纸质出版：2017
- 稿件说明：
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杜长河, 范小军, 李亮, 等. 旋转半径和叶片安装角对动叶旋流冷却流动和传热特性的影响[J]. 西安交通大学学报, 2017,51(5):37-42+148.

Influences of Rotating Radius and Blade Setting Angle on Rotor Vortex Cooling Flow and Heat Transfer Characteristics[J]. 2017, 51(5): 37-42+148.
杜长河, 范小军, 李亮, 等. 旋转半径和叶片安装角对动叶旋流冷却流动和传热特性的影响[J]. 西安交通大学学报, 2017,51(5):37-42+148. DOI： 10.7652/xjtuxb201705006.

Influences of Rotating Radius and Blade Setting Angle on Rotor Vortex Cooling Flow and Heat Transfer Characteristics[J]. 2017, 51(5): 37-42+148. DOI： 10.7652/xjtuxb201705006.

摘要

针对航空发动机涡轮动叶片中应用旋流冷却的问题

建立了旋转条件下的旋流腔冷却模型

比较了静止和旋转条件下冲击与旋流冷却的流动传热特性差异

研究了旋转半径和叶片安装角对旋流冷却特性的影响规律。研究结果表明:叶片旋流腔旋转显著改变旋流冷却气动传热特性

旋转条件下旋流腔产生离心力和科氏力; 离心力驱使冷气向叶顶方向运动

加强冷气横向冲击作用

使得高传热区域向叶顶方向偏移; 科氏力方向为轴向上游或下游

引起冷气轴向回流

增强冷气掺混

减小射流冷气周向速度

显著降低了传热强度; 旋转条件下

旋流冷却传热强度比冲击冷却提高了27.6%; 与静止条件相比

旋转数为0.819时冲击冷却传热强度减小了30.0%

旋流冷却传热强度减小了18.6%; 叶片旋流腔旋转半径增大时

冷气周向速度稍有减小

靶面平均Nu略有减小; 叶片安装角增大时

旋流冷却流场和平均Nu不变

周向平均Nu分布均匀性降低。

Abstract

A vortex chamber model under rotating conditions is established to study the application of vortex cooling in aircraft engine turbine rotor blades. The flow and heat transfer behaviors of impingement and vortex cooling under static and rotating conditions are compared and analyzed. The effects of rotating radius and blade setting angle on rotor vortex cooling behavior are studied. Results show that the rotation of blade vortex chamber can change the aerodynamic and thermal performance of vortex cooling significantly. Under rotating conditions

the centrifugal and Coriolis forces are generated in the vortex chamber. The centrifugal force pushes cooling air to the shroud direction and enhances cooling air crosswise impact effect

driving the high heat transfer region deviating downstream. The Coriolis force direction is axial upstream or downstream. It will induce axial back flow of cooling air and enhance cooling air mixing. Therefore

the circumferential velocity of injected cooling air is decreased

thus obviously decreasing the heat transfer intensity. Under rotating conditions

the heat transfer intensity of vortex cooling is 27.6% higher than impingement cooling. Compared with static conditions

the heat transfer intensity of impingement cooling and vortex cooling under rotating conditions will decrease by 30.0% and 18.6%

respectively. When the rotating radius of blade vortex chamber increases

the circumferential velocity of cooling air and the target wall's globally averaged Nusselt number will decrease slightly. With the decrease of blade setting angle

the vortex cooling flow field and the globally averaged Nusselt number almost keep unchanged

and the circumferentially averaged Nusselt number distribution turns more nonuniform.

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references

KREITH F, MARGOLIS D. Heat transfer and friction in turbulent vortex flow [J]. Applied Scientific Research: Section A, 1959, 8(1): 457-473.

CHANG F, DHIR V K. Mechanisms of heat transfer enhancement and slow decay of swirl in tubes using tangential injection [J]. International Journal of Heat Fluid Flow, 1995, 16(2): 78-87.

GLEZER B, MOON H K, O'CONNELL T. A novel technique for the internal blade cooling [C]∥ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition. New York, USA: ASME, 1996: V004T09A015.

HEDLUND C R, LIGRANI P M, GLEZER B, et al. Heat transfer in a swirl chamber at different temperature ratios and Reynolds numbers [J]. International Journal of Heat Mass Transfer, 1999, 42(22): 4081-4091.

LING J P C W, IRELAND P T, HARVEY N W. Measurement of heat transfer coefficient distributions and flow field in a model of a turbine blade cooling passage with tangential injection [C]∥ASME Turbo Expo 2006: Power for Land, Sea, and Air. New York, USA: ASME, 2006: 325-340.

BRUSCHEWSKI M, SCHERHAG C, SCHIFFER H P, et al. Influence of channel geometry and flow variables on cyclone cooling of turbine blades [J]. Journal of Turbomachinery, 2015, 138(6): 061005

DU Changhe, LI Liang, LI Sen, et al. Effects of aerodynamic parameters on steam vortex cooling behavior for gas turbine blade leading edge [J]. Proceedings of the Institution of Mechanical Engineers: Part A Journal of Power and Energy, 2016, 230(4): 354-365.

DU Change, LI Liang, WU Xin, et al. Effect of jet nozzle geometry on flow and heat transfer performance of vortex cooling for gas turbine blade leading edge [J]. Applied Thermal Engineering, 2016, 93: 1020-1032.

杜长河, 范小军, 李亮, 等. 喷嘴长宽比和雷诺数对旋流冷却流动与传热特性的影响 [J]. 西安交通大学学报, 2015, 49(12): 124-129.

DU Changhe, FAN Xiaojun, LI Liang, et al. Effects of jet nozzle aspect ratio and Reynolds number on flow and heat transfer characteristics of vortex cooling [J]. Journal of Xi'an Jiaotong University, 2015, 49(12): 124-129.

范小军, 杜长河, 李亮. 气膜孔几何位置对旋流冷却流动与传热特性的影响 [J]. 西安交通大学学报, 2016, 50(7): 32-38.

FAN Xiaojun, DU Changhe, LI Liang. Effect of bleed hole location on vortex cooling flow and heat transfer performance [J]. Journal of Xi'an Jiaotong University, 2016, 50(7): 32-38.

ZHANG F, WANG X, LI J. Effects of coolants on the flow and heat transfer characteristics in a non-rotating and rotating two-pass rectangular channel [J]. International Journal of Heat and Mass Transfer, 2015, 91: 390-400.

WAGNER J H, JOHNSON B V, HAJEK T J. Heat transfer in rotating passages with smooth walls and radial outward flow [J]. Journal of Turbomachinery, 1991, 113(1): 42-51.

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