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

孙添一; 张垲垣; 李志刚; 李军

doi:10.7652/xjtuxb202301015

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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

—————————————————————— | 更新时间：2025-07-09

- 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
- Effect of Combustor Outflow Conditions on the Flow Structure and Heat Transfer Cooling Characteristics of Turbine Vane Endwall
- 西安交通大学学报 2023年57卷第1期页码：152-163
- 作者机构：
  
  西安交通大学叶轮机械研究所,西安,710049
- 作者简介：
  
  : 2022-04-02。作者简介: 孙添一(1998—),男,博士生
  李军(通信作者),男,教授,博士生导师。基金项目: 国家自然科学基金资助项目(51936008)。
- 基金信息：
  
  : 2022-04-02。作者简介: 孙添一(1998—),男,博士生;李军(通信作者),男,教授,博士生导师。基金项目: 国家自然科学基金资助项目(51936008)。
- DOI：10.7652/xjtuxb202301015
  中图分类号： TK474.7
- 网络首发：2023-01-10，
  
  纸质出版：2023
- 稿件说明：
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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]. 2023, 57(1): 152-163.
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. DOI： 10.7652/xjtuxb202301015.

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

李军, 栗智宇, 李志刚, 等. 燃烧室和涡轮相互作用下高压涡轮级气热性能研究进展 [J]. 航空学报, 2021, 42(3): 136-161.

LI Jun, LI Zhiyu, LI Zhigang, et al.Aerothermal performance of high pressure turbine stage with combustor-turbine interactions: review [J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(3): 136-161.

BUNKER R S. Gas turbine heat transfer: ten remaining hot gas path challenges [J]. Journal of Turbomachinery, 2007, 129(2): 193-201.

JOHANSSON M, POVEY T, CHANA K, et al. Effect of low-NOX combustor swirl clocking on intermediate turbine duct vane aerodynamics with an upstream high pressure turbine stage: an experimental and computational study [J]. Journal of Turbomachinery, 2017, 139(1): 011006.

BEARD P F, ADAMS M G, NAGAWAKAR J R, et al. The LEMCOTEC 1/2 stage film-cooled HP turbine: design, integration and testing in the oxford turbine research facility [C]//Proceedings of 13th European Conference on Turbomachinery Fluid Dynamics Thermodynamics. Florence, Italy: European Turbomachinery Society, 2019: ETC201-216.

WERSCHNIK H. Aerodynamic impact of swirling combustor inflow on endwall heat transfer and the robustness of the film cooling design in an axial turbine [D]. Darmstadt, Germany: Technische Universität Darmstadt, 2017.

WERSCHNIK H, HILGERT J, WILHELM H, et al. Influence of combustor swirl on endwall heat transfer and film cooling effectiveness at the large scale turbine rig [J]. Journal of Turbomachinery, 2017, 139(8): 081007.

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. Manchester, UK: ISABE, 2017: ISABE-2017-21393.

SCHNEIDER M, SCHIFFER H P, LEHMANN K. Uncertainty propagation analyses of lean burn combustor exit conditions for a robust nozzle cooling design [J]. Journal of Turbomachinery, 2020, 142(5): 051003.

CUBEDA S, MAZZEI L, BACCI T, et al. Impact of predicted combustor outlet conditions on the aerothermal performance of film-cooled high pressure turbine vanes [J]. Journal of Engineering for Gas Turbines and Power, 2019, 141(5): 051011.

ZHANG Kaiyuan, LI Zhigang, LI Jun. Effect of inflow swirl on the vane endwall aerothermal performance with endwall misalignment at transonic condition [J]. International Journal of Heat and Mass Transfer, 2019, 144: 118662.

张文豪. 贫燃旋流燃烧室出流影响下的高压涡轮导叶气热特性数值研究 [D]. 西安: 西安交通大学, 2022.

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.

栗智宇, 张垲垣, 李志刚, 等. 燃烧室出口旋流对静叶栅端壁流动型态和传热冷却特性的影响 [J]. 西安交通大学学报, 2022, 56(4): 72-82.

LI Zhiyu, ZHANG Kaiyuan, LI Zhigang, et al.Effect of combustion chamber outlet swirling flow on flow pattern, heat transfer and cooling characteristics of turbine vane endwall [J]. Journal of Xi'an Jiaotong University, 2022, 56(4): 72-82.

ALQEFL M H, NAWATHE K P, CHEN Pingting, et al. Aero-thermal aspects of film cooled nozzle guide vane endwall: part 1 aerodynamics [J]. Journal of Turbomachinery, 2021, 143(12): 121009.

NAWATHE K P, ZHU Rui, LIN Enci, et al. Nozzle passage endwall effectiveness values with various combustor coolant flowrates: part 1 flowfield velocity and coolant concentration measurements [J]. Journal of Turbomachinery, 2021, 143(4): 041009.

孙添一, 李志刚, 李军. 发散冷却和前缘槽缝射流作用下涡轮静叶端壁流动结构的研究 [J]. 西安交通大学学报, 2022, 56(1): 120-129.

SUN Tianyi, LI Zhigang, LI Jun. Investigation on the flow structure of turbine vane endwall under effects of effusion cooling and leading edge slot jet [J]. Journal of Xi'an Jiaotong University, 2022, 56(1): 120-129.

孙添一, 李志刚, 李军. 发散冷却与槽缝射流对涡轮静叶端壁气热性能影响的研究 [J]. 推进技术, 2022, 43(8): 83-92.

SUN Tianyi, LI Zhigang, LI Jun. Effects of effusion cooling and slot jet flow on aerothermal performance of turbine vane endwall [J]. Journal of Propulsion Technology, 2022, 43(8): 83-92.

张垲垣, 李志刚, 宋立明, 等. 槽缝射流旋流比和密度比对涡轮端壁冷却和吸力面泛冷却性能的影响 [J]. 西安交通大学学报, 2018, 52(9): 95-101, 126.

ZHANG Kaiyuan, LI Zhigang, SONG Liming, et al.Effects of swirl ratio and density ratio of slot jet flow on the turbine endwall cooling and suction surface phantom cooling performance [J]. Journal of Xi'an Jiaotong University, 2018, 52(9): 95-101, 126.

MONGIA H C. Low emissions propulsion engine characterization process[M]//GUPTA A K, DE A, AGGARWAL S K, et al. Advances in Energy and Combustion: Safety and Sustainability. Berlin, Germany: Springer, 2022: 13-69.

FOUST M J, THOMSEN D, STICKLES R, et al. Development of the GE aviation low emissions TAPS combustor for next generation aircraft engines [C]//50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition. Reston, VA, USA: AIAA, 2012: AIAA 2012-936.

刘爱虢, 朱悦, 陈保东, 等. 三级旋流器旋流角匹配影响双环预混旋流燃烧室燃烧性能试验 [J]. 推进技术, 2017, 38(7): 1539-1547.

LIU Aiguo, ZHU Yue, CHEN Baodong, et al. Experiment on effects of triple swirler swirl angle matching on combustion performance of twins annular premixing swirler combustor [J]. Journal of Propulsion Technology, 2017, 38(7): 1539-1547.

MONGIA H, DODDS W. Low emissions propulsion engine combustor technology evolution past, present and future [C]//24th International Congress of Aeronautical Sciences. Bonn, Germany: ICAS, 2004: 2004-6.9.2.

SCHNEIDER M. Robust aero-thermal design of high pressure turbines at uncertain exit conditions of low-emission combustion systems [D]. Darmstadt, Germany: Technische Universität Darmstadt, 2019.

ROACHE P J. Quantification of uncertainty in computational fluid dynamics [J]. Annual Review of Fluid Mechanics, 1997, 29(1): 123-160.

LILLEY D G. Swirl flows in combustion: a review [J]. AIAA Journal, 1977, 15(8): 1063-1078.

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