燃烧室流量分配对涡轮进口非均匀气热特性影响的试验研究

李金泽; 杨星; 王群; 李庆烜; 李若诚; 汪翔宇; 丰镇平

doi:10.7652/xjtuxb202610014

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燃烧室流量分配对涡轮进口非均匀气热特性影响的试验研究

专题热流分析与系统优化 | 更新时间：2026-09-29

- 燃烧室流量分配对涡轮进口非均匀气热特性影响的试验研究
- Experimental Study on the Effect of Combustor Flow Split on Non-Uniform Aerothermal Characteristics at a Turbine Inlet
- 西安交通大学学报 2026年60卷第10期页码：160-172
- 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：
  
  李金泽（1997-），男，博士生；
  丰镇平（通信作者），男，教授，博士生导师。
- 基金信息：
  
  国家科技重大专项资助项目(J2019-Ⅱ-0008-0028)
- DOI：10.7652/xjtuxb202610014
  中图分类号： V231.1
- 收稿：2026-01-07，
  
  网络首发：2026-02-27，
  
  纸质出版：2026-10-10
- 稿件说明：
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李金泽, 杨星, 王群, 等. 燃烧室流量分配对涡轮进口非均匀气热特性影响的试验研究[J/OL]. 西安交通大学学报,2026,60 (10):160-172. https://doi.org/10.7652/xjtuxb202610014.

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.
李金泽, 杨星, 王群, 等. 燃烧室流量分配对涡轮进口非均匀气热特性影响的试验研究[J/OL]. 西安交通大学学报,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

Notaristefano A, Gaetani P.Impact of swirling entropy waves on a high pressure turbine [J].Journal of Turbomachinery, 2022, 144(3): 031010.

王志多, 王志豪, 张文豪, 等.燃烧室出流影响下的高压涡轮气热机理及设计研究综述[J].推进技术, 2026, 47(2): 6-28.

Wang Zhiduo, Wang Zhihao, Zhang Wenhao, et al. Review on high-pressure turbine aero-thermal mechanisms and design under effects of combustor exit flow[J]. Journal of Propulsion Technology, 2026, 47(2): 6-28.

晏武英.美欧航空发动机重大科技专项计划分析[J].航空动力, 2021(2): 39-44.

Yan Wuying.Analysis to major scientific and technological projects of aero engines of USA and Europe[J].Aerospace Power, 2021(2): 39-44.

Yin Hong, Liu Shi, Feng Yongxin, et al. Experimental test rig for Combustor-Turbine interaction research and test results analysis [C]//ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. New York, USA: ASME, 2015: V02AT38A001.

周杨, 张扬, 苏欣荣, 等.进口旋流周向位置对高压涡轮进口导叶气动特性的影响[J].航空动力学报, 2018, 33(2): 402-410.

Zhou Yang, Zhang Yang, Su Xinrong, et al. Effect of pitchwise position of inlet swirl on aerodynamic characteristics of high-pressure turbineIGV[J].Journal of Aerospace Power, 2018, 33(2): 402-410.

王志多.进口热斑等非均匀性对燃气透平级气动与传热特性影响的研究[D].西安: 西安交通大学, 2018.

刘高文, 刘松龄.热斑在1-1/2级涡轮内的非定常迁移数值模拟[J].航空动力学报, 2004, 19(6): 855-859.

Liu Gaowen, Liu Songling.Numerical simulation of unsteady hot streak migration in a 1-1/2stage turbine[J]. Journal of Aerospace Power, 2004, 19(6): 855-859.

赵庆军.无导叶对转涡轮流动特性分析及其进口热斑迁移机理研究[D].北京: 中国科学院工程热物理研究所, 2007.

丰镇平, 王志多, 刘兆方.燃气透平进口热斑迁移及其影响机制研究进展[J].中国电机工程学报, 2014, 34(29): 5120-5130.

Feng Zhenping, Wang Zhiduo, Liu Zhaofang.Review on research of hot streak migration mechanisms in gas turbine stage[J].Proceedings of the CSEE, 2014, 34(29): 5120-5130.

谢金伟, 刘志刚, 张晓东, 等.涡轮叶栅进口热斑迁移及其影响因素研究试验装置设计[J].燃气涡轮试验与研究, 2018, 31(2): 1-7.

Xie Jinwei, Liu Zhigang, Zhang Xiaodong, et al. Design of an experimental apparatus for turbine cascade inlet hot streak migration and influences research[J]. Gas Turbine Experiment and Research, 2018, 31(2): 1-7.

Koupper C. Unsteady multi-component simulations dedicated to the impact of the combustion chamber on the turbine of aeronautical gas turbines [D].Toulouse, France: Institut National Polytechnique de Toulouse, 2015.

Koupper C, Gicquel L, Duchaine F, et al. Experimental and numerical calculation of turbulent timescales at the exit of an engine representative combustor simulator [J].Journal of Engineering for Gas Turbines and Power, 2016, 138(2): 021503.

Bacci T, Caciolli G, Facchini B, et al. Flowfield and temperature profiles measurements on a combustor simulator dedicated to hot streaks generation [C]//ASME Turbo Expo 2015: Turbine Technical Conference and Exposition.New York, NY, USA: ASME, 2015: V05CT17A001.

Wilhelm M, Schmidt M, Goertz F, et al. Influence of combustor swirl on turbulence at the large scale turbine rig (LSTR)[C]//International Symposium of Air Breathing Engines. Indianapolis, IN, USA: ISABE, 2017: 21393.

Adams M G, Povey T, Hall B F, et al. Commissioning of a combined hot-streak and swirl profile generator in a transonic turbine test facility [J].Journal of Engineering for Gas Turbines and Power, 2020, 142(3): 031008.

Adams M G, Beard P F, Stokes M R, et al. Effect of a combined hot-streak and swirl profile on cooled 1.5stage turbine aerodynamics: an experimental and computational study [J].Journal of Turbomachinery, 2021, 143(2): 021011.

Amend J, Lubbock R, Ornan F, et al. Lean-burn combustor simulator for an engine-component test facility: an experimental and computational study [J].Journal of Turbomachinery, 2023, 145(6): 061014.

Amend J.Effect of lean-burn combustor outlet flows on nozzle guide vane aerothermal performance: an experimental and computational study [D].Oxford, UK: University of Oxford, 2024.

Amend J, Chowdhury N, Povey T.Impact of lean-burn combustor flow on nozzle guide vane performance [J]. Journal of Turbomachinery, 2025, 147(1): 011001.

Notaristefano A, Gaetani P.The role of turbine operating conditions on combustor-turbine interaction: partⅠ change in expansion ratio [J].Journal of Turbomachinery, 2023, 145(5): 051001.

Notaristefano A, Gaetani P.Modeling of combustor non-uniformities evolution through a high-pressure turbine stage [J].Journal of Turbomachinery, 2024, 146(6): 061008.

Notaristefano A, Persico G, Gaetani P.Turbulence measurements downstream of a combustor simulator designed for studies on the combustor-turbine interaction [J].International Journal of Turbomachinery, Propulsion and Power, 2024, 9(1): 4.

Pinelli L, Giannini G, Marconcini M, et al. The impact of the off-design conditions on the entropy wave interaction with a high-pressure turbine stage [J]. Journal of Turbomachinery, 2024, 146(4): 041003.

Feng Zhenping, Liu Zhaofang, Shi Yan, et al. Effects of hot streak and airfoil clocking on heat transfer and aerodynamic characteristics in gas turbine [J].Journal of Turbomachinery, 2016, 138(2): 021002.

Li Yifei, Su Xinrong, Yuan Xin.The effect of mismatching between combustor and HP vanes on the aerodynamics and heat load in a 1-1/2stages turbine [J].Aerospace Science and Technology, 2019, 86: 78-92.

Zhang Wenhao, Wang Zhiduo, Wang Zhihao, et al. Study on heat transfer characteristics of NGVs influenced by non-reacting lean burn combustor simulator flow [J].International Journal of Thermal Sciences, 2022, 172(Part A): 107313.

Zhang Shenghui, Ding Shuiting, Liu Peng, et al. Effect of hot streak on aerothermal performance of high pressure turbine guide vane under different swirl intensities [J].Aerospace, 2022, 9(10): 579.

孙添一, 张垲垣, 李志刚, 等.燃烧室出流条件对涡轮静叶端壁流动结构和传热冷却特性的影响[J].西安交通大学学报, 2023, 57(1): 152-163.

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].Journal of Xi'an Jiaotong University, 2023, 57(1): 152-163.

Song Hui, Ye Lin, Wang Xinyu, et al. Assessing the effect of swirl flow on the film cooling effectiveness of a vane pressure surface [J].International Communications in Heat and Mass Transfer, 2025, 160: 108327.

李继保, 索建秦.航空发动机主燃烧室设计[M].北京: 科学出版社, 2022: 37-39.

Schaeffer C B, Barringer M D, Lynch S P, et al. Influence of dilution and effusion flows in generating variable inlet profiles for a high-pressure turbine [J]. Journal of Turbomachinery, 2025, 147(3): 031003.

Li J Z, Yang X, Wang X Y, et al. Experimentally-resolved flow and thermal fields at the exit of an annular non-reacting combustor sector [EB/OL].[2025-12-10]https: //gpps.global/wp-content/uploads/2025/09/GPPS-TC-2025_paper_076.pdf.

Huang Ying, Yang V.Dynamics and stability of leanpremixed swirl-stabilized combustion [J].Progress in Energy and Combustion Science, 2009, 35(4): 293-364.

马兴宇, 明晓.七孔探针测量剪切流场的误差分析和实验验证[J].空气动力学学报, 2012, 30(1): 57-62.

Ma Xingyu, Ming Xiao.Experimental research and error analysis on seven-hole probe measurements of shearing flow field[J].Acta Aerodynamica Sinica, 2012, 30(1): 57-62.

Moffat R J.Describing the uncertainties in experimental results [J].Experimental Thermal and Fluid Science, 1988, 1(1): 3-17.

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