Conjugate Heat Transfer on the Performance of Rotating Components in Ultra-Micro Gas Turbines

YAO Xuerui; XU Mengjuan; LIU Zhao; FENG Zhenping

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Conjugate Heat Transfer on the Performance of Rotating Components in Ultra-Micro Gas Turbines

更新时间：2026-04-15

- Conjugate Heat Transfer on the Performance of Rotating Components in Ultra-Micro Gas Turbines
- JOURNAL OF XI’AN JIAOTONG UNIVERSITY (2026)
- 作者机构：
  
  1.西安交通大学能源与动力工程学院，710049，西安
  2.西安交通大学机械工程学院，710049，西安
- 作者简介：
- 基金信息：
- DOI：
  CLC： TK47
- Received：14 February 2026，
  
  Revised：2026-04-14，
  
  Accepted：15 April 2026，
- 稿件说明：
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YAO Xuerui, XU Mengjuan, LIU Zhao, et al. Conjugate Heat Transfer on the Performance of Rotating Components in Ultra-Micro Gas Turbines[J/OL]. JOURNAL OF XI’AN JIAOTONG UNIVERSITY, 2026.
DOI：

YAO Xuerui, XU Mengjuan, LIU Zhao, et al. Conjugate Heat Transfer on the Performance of Rotating Components in Ultra-Micro Gas Turbines[J/OL]. JOURNAL OF XI’AN JIAOTONG UNIVERSITY, 2026. DOI：

摘要

为揭示超微型燃气轮机转子内部轴向传热对旋转部件气动性能的影响机制，并评估内部冷却结构对转子性能的恢复作用。本文采用流热耦合方法对一台350 W超微型燃气轮机转子开展流动与传热的数值模拟，对比分析了内部传热及轴内冷却对部件性能的影响。结果表明：内部传热使离心压气机压比下降5.56%，效率降低3.05%，向心透平输出功率下降10.96%，效率降低2.47%，但传热同时在一定程度上稳定了压气机与透平内部的流动结构，减小了流动损失。施加内部冷却结构后，压气机压比与效率分别提升1.13%与0.98%，透平输出功率升高2.90%，效率提高0.10%，悬臂轴温度降幅达45.1%。基于传热带来的流动稳定效应，提出在设计中适当采用更高叶片载荷的设计思路以补偿因传热导致的做功能力衰减；内部冷却结构能有效降低悬臂轴温度，改善轴承工作环境，为超微型燃气轮机在紧凑条件下的长期稳定运行提供有效的热防护方案。

Abstract

To reveal the influence mechanism of internal axial heat transfer within the rotor on the aerodynamic performance of rotating components in an ultra-micro gas turbine

and to evaluate the performance recovery effect of an internal cooling structure

a conjugate heat transfer method was employed to numerically simulate the flow and heat transfer in a 350 W ultra-micro gas turbine rotor. The effects of internal heat transfer and in-shaft cooling on component performance were comparatively analyzed. The results indicated that internal heat transfer reduced the centrifugal compressor pressure ratio by 5.56% and efficiency by 3.05%

and decreased the radial turbine output power by 10.96% and efficiency by 2.47%. However

the heat transfer also stabilized the internal flow structures of the compressor and turbine to a certain extent

thereby reducing flow losses. With the implementation of the internal cooling structure

the compressor pressure ratio and efficiency were increased by 1.13% and 0.98%

respectively

the turbine output power was raised by 2.90%

and the turbine efficiency was improved by 0.10%. Notably

the temperature of the cantilevered shaft was reduced by 45.1%. Based on the flow stabilization effect induced by heat transfer

a design strategy of appropriately adopting higher blade loading was proposed to compensate for the power output degradation caused by heat transfer. The internal cooling structure was shown to effectively lower the cantilevered shaft temperature and improve the bearing operating environment

thereby providing an effective thermal protection scheme for the long-term stable operation of ultra-micro gas turbines under compact configurations.

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