航空发动机预旋供气系统盖板腔换热特性研究

doi:10.3901/JME.2025.22.282

摘要/Abstract

摘要： 预旋供气系统中盖板腔作为主要的换热元件，对其性能有重要影响。为了研究盖板腔内部的换热特性，首先采用数值计算分析盖板腔内涡轮盘壁面的换热系数与努塞尔数的径向分布规律，揭示主流冲击和旋流对换热的影响机理。随后，提出基于牛顿冷却公式的高速金属转盘对流换热系数测量的新方法，搭建试验平台开展预旋供气系统换热试验研究与验证，阐明旋转马赫数和压比对涡轮盘壁面平均换热参数的影响。研究结果表明，涡轮盘壁面换热主要受主流冲击影响，旋流的影响相对较小。压比与主流冲击密切相关，而旋转马赫数与旋流密切相关。因此，改变工况实质上是改变主流和旋流对换热的影响权重。数值结果与试验结果吻合良好，偏差均在10%以内。试验结果显示，在压比一定的条件下，旋转马赫数从0.27增加到0.64时，平均对流换热系数提高了11.1%～23.2%；在旋转马赫数一定的条件下，压比从1.05增加到1.15时，平均对流换热系数提高了44.7%～60.5%。研究结果可为预旋供气系统的结构设计提供依据。

关键词: 预旋供气系统, 盘腔换热, 对流换热系数, 旋转马赫数, 努塞尔数

Abstract: The cover-plate cavity is the main heat exchange component in the pre-swirl system and has a significant impact on its performance. This study first studies the heat transfer mechanism inside the cover plate cavity through numerical calculations, and then conducts heat transfer experiments on the pre-swirl system using a new measurement method based on the Newton’s law of cooling formula, to verify the rationality of the numerical results. The study mainly analyzes the radial distribution characteristics of the heat transfer coefficient and Nusselt number on the turbine disk wall surface in the cover plate cavity. The results show that the heat transfer on the turbine disk wall surface is mainly affected by the mainstream impact, and the effect of swirling flow is relatively small. The pressure ratio is strongly correlated with the mainstream impact, while the rotational Mach number is strongly correlated with the swirling flow. Changing the operating conditions essentially changes the weight of the influence of the mainstream and swirling flow on heat transfer parameters. The numerical results and experimental results have deviations of less than 10%. From the experimental results, when the pressure ratio is constant, increasing the rotational Mach number from 0.27 to 0.64 increases the average heat transfer coefficient by 11.1% to 23.2%; when the rotational Mach number is constant, increasing the pressure ratio from 1.05 to 1.15 increases the average heat transfer coefficient by 44.7%～60.5%. The research results of this study can provide a design basis for the structural design of pre-swirl systems.

Key words: pre-swirl system, disk cavity heat transfer, convective heat transfer coefficient, rotating mach number, nusselt number

中图分类号:

V235

马佳乐, 刘高文, 吴帅, 孔晓治, 林阿强. 航空发动机预旋供气系统盖板腔换热特性研究[J]. 机械工程学报, 2025, 61(22): 282-293.

MA Jiale, LIU Gaowen, WU Shuai, KONG Xiaozhi, LIN Aqiang. Study on Heat Transfer Characteristics of Cover-plate Cavity in Pre-swirl System of Aircraft Engine[J]. Journal of Mechanical Engineering, 2025, 61(22): 282-293.

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