Influences of Rotating Radius and Blade Setting Angle on Rotor Vortex Cooling Flow and Heat Transfer Characteristics

doi:10.7652/xjtuxb201705006

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Influences of Rotating Radius and Blade Setting Angle on Rotor Vortex Cooling Flow and Heat Transfer Characteristics

更新时间：2025-07-09

- Influences of Rotating Radius and Blade Setting Angle on Rotor Vortex Cooling Flow and Heat Transfer Characteristics
- Vol. 51, Issue 5, Pages: 37-42+148(2017)
- 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
  CLC： TK474.7
- Online First：10 May 2017，
  
  Published：2017
- 稿件说明：
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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：

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

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李森

范小军 1

邹佳生 1

李亮 2

杜长河 1

李亮 2

周源远 1

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Related Institution

School of Energy and Power Engineering, Xi'an Jiaotong University

Shaanxi Engineering Laboratory of Turbomachinery and Power Equipment

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