Study on the Influence of Mach Number and Tip Cutback on the Aerodynamic Loss and Heat Transfer Characteristics of Turbine Rotor Tips

JIANG Shoumin; JIANG Hongmei; TAO Zhi; YAN Yifei; LU Shaopeng; CUI Xin; SONG Liming

doi:10.7652/xjtuxb202503009

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Study on the Influence of Mach Number and Tip Cutback on the Aerodynamic Loss and Heat Transfer Characteristics of Turbine Rotor Tips

更新时间：2026-01-06

- Study on the Influence of Mach Number and Tip Cutback on the Aerodynamic Loss and Heat Transfer Characteristics of Turbine Rotor Tips
- Journal of Xi’an Jiaotong University Vol. 59, Issue 3, Pages: 89-98(2025)
- 作者机构：
  
  1.西安交通大学能源与动力工程学院， 710049，西安
  2.中国航发沈阳发动机研究所， 110015，沈阳
  3.上海交通大学航空航天学院， 200240，上海
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202503009
  CLC： TK471
- Received：22 May 2024，
  
  Online First：16 October 2024，
  
  Published：10 March 2025
- 稿件说明：
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JIANG Shoumin, JIANG Hongmei, TAO Zhi, et al. Study on the Influence of Mach Number and Tip Cutback on the Aerodynamic Loss and Heat Transfer Characteristics of Turbine Rotor Tips[J]. Journal of Xi’an Jiaotong University, 2025, 59(3): 89-98.
DOI：

JIANG Shoumin, JIANG Hongmei, TAO Zhi, et al. Study on the Influence of Mach Number and Tip Cutback on the Aerodynamic Loss and Heat Transfer Characteristics of Turbine Rotor Tips[J]. Journal of Xi’an Jiaotong University, 2025, 59(3): 89-98. DOI： 10.7652/xjtuxb202503009.

摘要

为了掌握马赫数和肩壁尾切构型对涡轮转子叶尖气动和传热特性的影响，利用瞬态传热测试技术在跨声速条件下开展了叶栅总压损失和叶尖传热系数的测量，并结合数值仿真揭示了上述因素

的影响机理。结果表明，随着出口马赫数（

=0.45，0.60，0.75）的增加，叶尖附近的叶尖泄漏涡和上通道涡的强度和尺度逐渐增大，导致叶栅总压损失系数大幅增加。随着出口马赫数增大，叶尖表面传热系数的分布趋势基本不变，但是由于泄漏流速度增大，导致叶尖表面传热系数显著增大。在

=0.75工况下，对比了吸力侧尾切和压力侧尾切两种构型与基准叶尖模型的气动与传热特性。相比基准模型，吸力侧尾切构型和压力侧尾切构型均能降低叶尖区域的气动损失，降低幅度分别为4.1%和4.2%。与基准模型相比，吸力侧尾切构型增大了切口附近的传热系数，但显著降低了叶尖尾缘区域的传热系数；压力侧尾切构型则大幅增加了叶尖尾缘附近的传热系数。

Abstract

To investigate the effects of Mach number and tip cutback configurations on the aerodynamic and thermal characteristics of turbine rotor tips

transient heat transfer measurement is conducted under transonic conditions to measure the total pressure loss and tip heat transfer coefficient of the blade row. Numerical simulations are also utilized to reveal the impact mechanisms of these factors. The results show that with increasing exit Mach numbers (

=0.45

0.60

0.75)

the strength and scale of the tip leakage vortex and upper passage vortex near the tip gradually increase

leading to a significant increase in the total pressure loss coefficient of the blade row. As the exit Mach number increases

the distribution trend of the tip surface heat transfer coefficient remains essentially unchanged

but due to the increase in leakage flow velocity

the tip surface heat transfer coefficient significantly increases. Under the

=0.75 condition

the aerodynamic and heat transfer characteristics of the suction side cutback and pressure side cutback configurations are compared with the baseline blade tip model. Compared to the baseline model

both the suction side cutback and pressure side cutback configurations can reduce the aerodynamic loss in the tip region by 4.1% and 4.2%

respectively. Compared to the baseline model

the suction side cutback configuration increases the heat transfer coefficient near the cutback but significantly reduces the heat transfer coefficient in the tip trailing edge region; while the pressure side cutback configuration significantly increases the heat

transfer coefficient near the tip trailing edge.

关键词

Keywords

references

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