气冷涡轮叶片多学科耦合仿真

曾军; 廖文轩; 张剑; 崔亭亭; 张晓晶; 王闰龙

doi:10.7638/kqdlxxb-2025.0155

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气冷涡轮叶片多学科耦合仿真

研究专栏—涡轮动力系统流固热耦合仿真关键技术 | 更新时间：2026-05-28

- 气冷涡轮叶片多学科耦合仿真
- Multidisciplinary coupling simulation for cooled turbine blade
- 空气动力学学报 2025年43卷第8期页码：100-110
- 作者机构：
  
  1. 中国航发四川燃气涡轮研究院,成都,610500
  2. 哈尔滨工业大学能源科学与工程学院,哈尔滨,150001
- 作者简介：
  
  曾军*（1967—），男，四川仁寿人，研究员，研究方向：航空发动机涡轮气动设计. E-mail：gtezj@163.com
- 基金信息：
- DOI：10.7638/kqdlxxb-2025.0155
  中图分类号： V231.3
- 纸质出版：2025
- 稿件说明：
移动端阅览
曾军, 廖文轩, 张剑, 等. 气冷涡轮叶片多学科耦合仿真[J]. 空气动力学学报, 2025, 43(8): 100−110.

ZENG Jun, LIAO Wenxuan, ZHANG Jian, et al. Multidisciplinary coupling simulation for cooled turbine blade[J]. 2025, 43(8): 100-110.
曾军, 廖文轩, 张剑, 等. 气冷涡轮叶片多学科耦合仿真[J]. 空气动力学学报, 2025, 43(8): 100−110. DOI： 10.7638/kqdlxxb-2025.0155

ZENG Jun, LIAO Wenxuan, ZHANG Jian, et al. Multidisciplinary coupling simulation for cooled turbine blade[J]. 2025, 43(8): 100-110. DOI： 10.7638/kqdlxxb-2025.0155.

摘要

涡轮叶片跨学科设计涉及气动、结构、传热与强度等多领域耦合。随着航空发动机涡轮前温度的持续提升，传统设计方法面临严峻挑战。现有工程方法普遍采用学科解耦的串行设计模式，对计算模型和方法进行了不同程度的简化。本文以某双级涡轮一级动叶为研究对象开展多学科耦合仿真研究。首先，为验证方法的可靠性，进行了网格无关性及涡轮叶片冷效试验验证。其次，在此基础上，对多学科耦合仿真方法与工程方法的结果进行了对比分析。研究结果表明：在气动性能计算方面，耦合仿真方法与工程方法具有良好的一致性，各气动参数（级膨胀比、级效率、一动全环进/出口流量、一动进/出口绝对马赫数等）差异均在1.30%以内；温度场分布呈现非均匀差异，叶片表面最高、最低及平均温度差异分别为0.41%、–7.63%及–4.89%；强度计算方面，叶身最大径向位移及轴向位移差异分别为–10.20%和–7.24%，振动特性频率（静频和动频）最大差异为1.50%。这些差异的主要原因在于多学科耦合仿真方法基于高保真度几何模型及全三维计算方法，保留了气膜孔等细节结构，较好考虑了气动-热力-结构的多场耦合效应，从而为气冷涡轮叶片设计提供了一种有效的方法。

Abstract

Turbine blade interdisciplinary design involves coupling among multiple disciplines such as aerodynamics

structures

heat transfer

and strength. With the continuous increase in turbine inlet temperatures of aero-engines

traditional design methods face severe challenges. Conventional engineering methods typically adopt a sequential and decoupled design process for disciplines (including aerodynamics

heat transfer

and strength)

applying various simplifications to computational models and methods. This paper conducts a multidisciplinary coupled simulation study focusing on the first-stage rotor blade of a two-stage turbine. To ensure the reliability of the verification method

grid independence verification and experimental validation of the turbine blade cooling effectiveness were first performed. Subsequently

a comparison was made between the results from the multidisciplinary coupled simulation method and those from the conventional engineering methods. The findings indicate that: in terms of aerodynamic performance calculation

the coupled simulation method and the engineering method show good consistency

with differences in all aerodynamic parameters (stage expansion ratio

stage efficiency

first-stage rotor full-annulus inlet/outlet flow rates

first-stage rotor inlet/outlet absolute Mach numbers

etc.) being within 1.30%. The temperature field distribution exhibits non-uniform differences

with blade surface temperature discrepancies of 0.41% (maximum)

–7.63% (minimum)

and –4.89% (average). In strength calculations

the differences in maximum radial displacement and axial displacement of the blade body are –10.20% and –7.24%

respectively

while the maximum discrepancy in vibration characteristic frequencies (static and dynamic frequencies) is 1.50%. These differences primarily arise because the multidisciplinary coupled simulation method is based on high-fidelity geometric models and fully three-dimensional computational techniques

retains detailed structures such as film cooling holes

and better accounts for the multi-field coupling effects of aerodynamics

thermodynamics

and structures

thereby providing an effective approach for the design of air-cooled turbine blades.

关键词

Keywords

references

BOHN D, BONHOFF B, SCHONENBORN H. IGTC-108 Combined aerodynamic and thermal analysis of a high-pressure turbine nozzle guide vane (Organized Session I: Advanced computational simulation and design)[C]//Proceedings of the 1995 Yokohama International Gas Turbine Congress, Gas Turbine Society of Japan, 1995.

SOHN H S, URWILLER C, KONAN S M, et al. Conjugate heat transfer analysis for gas turbine cooled stator[C]//ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers Digital Collection, 2012. doi: 10.1115/gt2012-68196

SOHN H S, PARK S, KIM J J, et al. Conjugate heat transfer analysis for gas turbine blade[C]//Proceedings of the KFMA Annual Meeting, 2018.

LÜCK H, SCHÄFER M, SCHIFFER H P. Simulation of thermal fluid-structure interaction in blade-disc configuration of an aircraft turbine model[C]//ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers Digital Collection, 2014. doi: 10.1115/gt2014-26316

GANINE V, AMIRANTE D, HILLS N J. Aero-thermo-mechanical modelling and validation of transient effects in a high pressure turbine internal air system[C]//ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition, 2016. doi: 10.1115/gt2016-57739

ALTUNA A, CHAQUET J M, CORRAL R, et al. Application of a fast loosely coupled fluid/solid heat transfer method to the transient analysis of low-pressure-turbine disk cavities[C]//ASME Turbo Expo 2013: TurbomachineryTechnical Conference and Exposition. San Antonio, Texas, USA. American Society of Mechanical Engineers, 2013. doi: 10.1115/gt2013-95426

CHAQUET J M, CORRAL R, PASTOR G, et al. Validation of a coupled fluid/solid heat transfer method[C]//ASME Turbo Expo 2011: TurbomachineryTechnical Conference and Exposition. Vancouver, British Columbia, Canada. ASMEDC, 2011. doi: 10.1115/gt2011-45951

MARCHUKOV E Y, EGOROV I, POPOV G, et al. Multidisciplinary optimization of the working process of uncooled axial turbine according to efficiency and strength criteria[C]//ASME Turbo Expo 2013:TurbomachineryTechnical Conference and Exposition. Charlotte, North Carolina, USA. American Society of Mechanical Engineers, 2017. doi: 10.1115/gt2017-64843

ANTON S. Strength reliability of turbine rotor ensuring based on multidisciplinary optimization[C]//29th Congress of the International Council of the Aeronautical Sciences, 2014.

ZENG J, QING X J. External heat transfer predictions of turbine cascades[J]. Journal of Aerospace Power, 2008, 23(7): 1198−1204 (in Chinese).

ZENG J, QING X J. Conjugate flow and heat transfer investigation of a turbine cascade[J]. Journal of Aerospace Power, 2009, 24(6): 1204−1210 (in Chinese).

ZENG J, ZHANG W T, WANG P F, et al. Conjugate heat transfer analysis for cooled low pressure turbine rotor blade[J]. Journal of Propulsion Technology, 2020, 41(6): 1268−1275 (in Chinese).

WANG M J, XUE W P, CHEN A L, et al. Turbine blade conjugated heat transfer analysis method based on parametric modeling[J]. Journal of Propulsion Technology, 2024, 45(4): 105−115 (in Chinese).

CAI L X, HOU Y F, LI F, et al. Impacts of startup, shutdown and load variation on transient temperature and thermal stress fields within blades of gas turbines[J]. Journal of Thermal Science, 2022, 31(3): 727−740. doi: 10.1007/s11630-022-1603-z

CAI L X, HE Y, WANG S S, et al. Thermal-fluid-solid coupling analysis on the temperature and thermal stress field of a nickel-base superalloy turbine blade[J]. Materials, 2021, 14(12): 3315. doi: 10.3390/ma14123315

ZHANG Y D, ZOU Z P, YAO L C. Multidisciplinary coupling simulation of low pressure turbine in working profile[J]. Journal of Engineering Thermophysics, 2024, 45(5): 1374−1384 (in Chinese).

ZENG J, ZHANG J. Application of computational fluid dynamics in aero-engine development[J]. Gas Turbine Experiment and Research, 2025, 38(2): 58−72 (in Chinese). doi: 10.3724/j.GTER.20250031

HUANG Q N, LIU Z Q, ZHU M F, et al. Aeroengine design manual. Vol. 10: Turbine [M]. Beijing: Aviation Industry Press, 2001 (in Chinese).

WANG H G, LU H Y, YU H Z, et al. Aeroengine design manual. Vol. 16: Air system and heat transfer analysis [M]. Beijing: Aviation Industry Press, 2001 (in Chinese).

YIN Z Y, OU Y X, REN P Z, et al. Aeroengine design manual. Vol. 18: Strength analysis of blade, disk and main shaft [M]. Beijing: Aviation Industry Press, 2001 (in Chinese).

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