Effect of Combustor Outflow Conditions on the Flow Structure and Heat Transfer Cooling Characteristics of Turbine Vane Endwall

SUN Tianyi; ZHANG Kaiyuan; LI Zhigang; LI Jun

doi:10.7652/xjtuxb202301015

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Effect of Combustor Outflow Conditions on the Flow Structure and Heat Transfer Cooling Characteristics of Turbine Vane Endwall

更新时间：2025-07-09

- Effect of Combustor Outflow Conditions on the Flow Structure and Heat Transfer Cooling Characteristics of Turbine Vane Endwall
- Vol. 57, Issue 1, Pages: 152-163(2023)
- 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/xjtuxb202301015
  CLC： TK474.7
- Online First：10 January 2023，
  
  Published：2023
- 稿件说明：
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SUN Tianyi, ZHANG Kaiyuan, LI Zhigang, et al. Effect of Combustor Outflow Conditions on the Flow Structure and Heat Transfer Cooling Characteristics of Turbine Vane Endwall[J]. 2023, 57(1): 152-163.
DOI：

SUN Tianyi, ZHANG Kaiyuan, LI Zhigang, et al. Effect of Combustor Outflow Conditions on the Flow Structure and Heat Transfer Cooling Characteristics of Turbine Vane Endwall[J]. 2023, 57(1): 152-163. DOI： 10.7652/xjtuxb202301015.

摘要

论文数值研究了不同燃烧室旋流器时序位置与旋流方向工况下

涡轮静叶叶栅气动特征

端壁附近流动结构

总压损失系数和端壁、叶表传热与冷却特性以及冷却气的流动趋势; 建立了双环预混旋流器(TAPS)燃烧室简化模型

将其与涡轮第一级静叶叶栅进行整体数值计算。研究表明:本文计算采用的TAPS燃烧室模型旋流器出口旋流数为0.71

可以代表典型贫油预混燃烧室流动特征; 火焰筒内壁发散冷却气会在静叶端壁附近形成高总压区

燃烧室旋流使中间叶展位置总压降低; 正向旋流会在叶片前缘处分为两股

反向旋流则全部流入一个叶栅通道; 燃烧室旋流冲刷会显著提升叶片吸力面上游换热强度

正向旋流会对下端壁压力面侧的冷却效果产生负面影响; 槽缝射流局部吹风比在滞止点处最低

但旋流器正对叶片前缘时

旋流会削弱滞止点的影响; 静叶端壁流动结构与传热、冷却特性受到燃烧室出流条件的显著影响

在进行叶栅气动性能优化与冷却结构设计时需对其加以考虑。

Abstract

This paper

through the numerical analysis research

investigates the aerodynamic characteristics of the turbine vane cascade

flow structures near the turbine vane endwall

total pressure loss coefficient

heat transfer and cooling characteristics on the endwall and vane surface

and the flow trend of the cooling air under different conditions with different clocking positions and whirling directions of the combustor swirler. A simplified model of twin annular pre-mixing swirler(TAPS)combustor is established

and the overall numerical calculation is carried out by including the turbine nozzle vane cascade combined and the combustor section as a whole. The obtained results show that the TAPS combustor calculation model used in this paper has a swirl number of 0.71 at the outlet of the swirler

which can represent the typical flow characteristics of a lean-burn premixed combustor. The emission of cooling air from the inner wall of the flame tube leads to a high total pressure area near the vane endwall

while combustor swirling flow reduces the total pressure at mid-span position. The positive swirling flow is separated into two streams at the vane leading-edge

while the negative swirling flow enters one cascade as a whole. The combustor swirling flow significantly enhances the upstream heat transfer on the vane suction side. The positive swirling flow negatively affects the cooling effect on the pressure side of the hub endwall. The local blowing ratio of slot jet flow is the lowest at the stagnation point

but when the swirler is aligned with the vane leading-edge

the swirling flow weakens the influence of the stagnation point. The flow structure

heat transfer and cooling characteristics of the vane endwall are significantly affected by the combustor outflow conditions

which need to be considered when optimizing the aerodynamic performance of vane cascade and designing the cooling structure.

关键词

Keywords

references

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