Experimental Study on the Effect of Combustor Flow Split on Non-Uniform Aerothermal Characteristics at a Turbine Inlet

LI Jinze; YANG Xing; WANG Qun; LI Qingxuan; LI Ruocheng; Wang Xiangyu; FENG Zhenping

doi:10.7652/xjtuxb202610014

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Experimental Study on the Effect of Combustor Flow Split on Non-Uniform Aerothermal Characteristics at a Turbine Inlet

Special Topic Thermal-Fluid Analysis and System Optimization | 更新时间：2026-09-29

- Experimental Study on the Effect of Combustor Flow Split on Non-Uniform Aerothermal Characteristics at a Turbine Inlet
- Journal of Xi'an Jiaotong University Vol. 60, Issue 10, Pages: 160-172(2026)
- 作者机构：
  
  西安交通大学能源与动力工程学院，710049，西安
  西安交通大学陕西省叶轮机械及动力装备工程实验室，710049，西安
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202610014
  CLC： V231.1
- Received：07 January 2026，
  
  Online First：27 February 2026，
  
  Published：10 October 2026
- 稿件说明：
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LI Jinze, YANG Xing, WANG Qun, et al. Experimental Study on the Effect of Combustor Flow Split on Non-Uniform Aerothermal Characteristics at a Turbine Inlet[J/OL]. Journal of Xi'an Jiaotong University,2026,60 (10):160-172. https://doi.org/10.7652/xjtuxb202610014.
DOI：

LI Jinze, YANG Xing, WANG Qun, et al. Experimental Study on the Effect of Combustor Flow Split on Non-Uniform Aerothermal Characteristics at a Turbine Inlet[J/OL]. Journal of Xi'an Jiaotong University,2026,60 (10):160-172. https://doi.org/10.7652/xjtuxb202610014. DOI：

摘要

为研究燃烧室-涡轮相互作用并深入理解涡轮进口非均匀气热特性的形成机理和影响因素，搭建无化学反应扇形燃烧室模拟器试验台，复现并调节由热斑、旋流、总压梯度等耦合形成的涡轮进口非均匀气热场。将燃烧室流量分配解耦为带旋流的主流流量和内、外衬套冷气流量比两个关键参数，采用7孔探针及热电偶扫描获取5种工况下的涡轮进口截面气热场，揭示了燃烧室流量分配对涡轮进口非均匀特性的影响机制。试验结果表明：涡轮进口非均匀特性是燃烧室旋流与发散冷气之间气热耦合作用的结果，增加主流流量可增强旋流的动力效应并扩大其影响范围，主流流量增加20%时，截面周向平均旋流角和节距角的变化区间宽度分别扩大28.3%、减小33.5%；改变内、外衬套冷气流量比将导致旋流核心发生高度约10%的径向偏移，并显著改变冷气侧的压力与温度梯度。研究结果可为下一代航空发动机高压涡轮的气动及冷却设计提供关键气动热力边界条件，并为燃烧室-涡轮一体化设计提供有益的借鉴。

Abstract

To investigate the combustor-turbine interactions and to deepen understanding of the formation mechanism as well as the influencing factors of non-uniform aerothermal characteristics at a turbine inlet

a non-reacting sector combustor simulator was constructed. This facility was capable of reproducing and regulating coupled non-uniform characteristics at turbine inlets

including hot streaks

swirling flow

total pressure gradients

and high turbulence intensity. The combustor flow split was decoupled into two key parameters: the mainstream swirling flow rate and the inner-to-outer liner coolant flow ratio. A traverse system was employed to scan the thermal-flow field at the turbine inlet plane using a seven-hole probe equipped with a thermocouple under five operating conditions

revealing the influence mechanisms of combustor flow splits on non-uniform characteristics. The results indicate that the non-uniform characteristics at the turbine inlet are mainly due to the thermal-fluid coupling between the combustor's swirling flow and the effusion cooling flow. An increase in the mainstream swirl flow rate enhances the dynamic effect of the swirl and expands its influence area. Specifically

a 20% increase in the mainstream swirl flow rate causes the variation ranges of the circumferentially averaged swirl and pitch angles to be expanded by 28.3% and to be reduced by 33.5%

respectively. Altering the inner-to-outer coolant flow ratio causes a radial shift of the swirling core by approximately 10% of the passage height and significantly changes the pressure and temperature gradients on the coolant side. These findings provide critical aerothermal boundary conditions for aerodynamic and cooling design of high-pressure turbines in next-generation aero-engines

and offer valuable insights for integrated combustor-turbine design.

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references

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