上海交通大学学报

上海交通大学学报

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低速大尺寸压气机静叶蜂窝与篦齿间隙泄漏流（网络首发）

  

  1. 1.上海交通大学航空航天学院；2.中国航发商用航空发动机有限责任公司压气机部；3.中国航发商用航空发动机有限责任公司先进技术部
  • 基金资助:
    国家自然科学基金(No.51576124，52076129)资助项目

Leakage Flow Between Honeycomb and Labyrinth in Stator of Low-Speed Research Compressor

  1. （1. School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai 200240, China; 2. Compressor Department, AECC Commercial Aircraft Engine Co., Shanghai 200240, China; 3. Advanced Technology Department, AECC Commercial Aircraft Engine Co., Shanghai 200240, China）

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摘要： 压气机静叶根部内环蜂窝与轮盘篦齿形成封严容腔，腔内的间隙泄漏流对轴流压气机的气动性能产生重要影响。本文以低速大尺寸压气机（LSRC）前1.5级为研究对象，通过数值模拟讨论了蜂窝封严相较于光壁结构以及蜂窝封严结构在两种篦齿封严间隙下对压气机气动性能的影响。性能计算结果表明，0.2mm封严间隙下，使用蜂窝内环结构的压气机效率低于使用光壁内环的压气机。原因在于容腔泄流导致总温升高。容腔泄漏流特性对比及详细流场分析表明，蜂窝结构使得容腔泄漏流量和旋流角同时增加，容腔以及蜂窝内的气流产生了强烈的相互作用，从而形成更复杂的漩涡流动，这使得封严容腔和蜂窝内的总温升高，最终导致压气机效率降低。使用蜂窝内环结构时，压气机效率会随封严间隙的减小而升高。零间隙蜂窝模型和0.2mm间隙蜂窝模型相比，其总温比的下降导致等熵效率上升；零间隙模型泄漏流量和旋流角都大幅降低，综合导致泄漏流掺混损失基本相当；零间隙模型虽然由于间隙的减小使得泄漏流平均总温上升，但由于泄漏流量的大幅减少，压气机效率有所升高。本文的研究结果揭示了在实际压气机中，不同间隙下静叶蜂窝与篦齿封严结构的泄漏流对性能的影响及其机理，并对蜂窝封严容腔的工程设计具有一定的参考价值。

关键词: 低速大尺寸压气机, 蜂窝, 篦齿, 封严间隙, 泄漏流

Abstract: The honeycomb at the inner band of the compressor stator and the labyrinth on the disk form a sealed cavity, and the clearance leakage flow in the cavity has an important influence on the aerodynamic performance of the axial flow compressor. In this paper, the first 1.5 stage of a lowspeed research compressor (LSRC) was taken as the research object, and the influence of honeycomb seal structure on the aerodynamic performance of the compressor compared with the slide wall and honeycomb seal structure at two kinds of labyrinth seal clearance was discussed by numerical simulation. The performance calculation results show that the isentropic efficiency of the 1.5-stage compressor using the honeycomb cavity model of 0.2mm clearance is slightly lower than that of the slide wall cavity model because of the higher total temperature rise caused by the leakage flow in the cavity. A comparison of cavity leakage flow characteristics and a detailed flow field analysis shows that the honeycomb structure simultaneously increases the cavity leakage flow and swirl angle. The airflow within the cavity and the honeycomb interact strongly, creating a complex vortex flow that significantly raises the total temperature in both the seal cavity and the honeycomb. This increase in temperature ultimately reduces compressor efficiency. Compared with the zeroclearance honeycomb model and the 0.2mm clearance honeycomb model, the decrease in total temperature ratio leads to an increase in isentropic efficiency. The leakage flow and swirl angle of the zero-clearance model are greatly reduced, and the mixing loss of leakage flow does not change significantly. In the zero-clearance model, although the average total temperature of the leakage flow increases due to the decrease of the clearance, the compressor efficiency improves due to the substantial reduction of the leakage flow rate. The research results of this paper reveal the quantitative relationship and mechanism of the influence of leakage flow at different clearances on the performance of the honeycomb and the labyrinth seal structure of the stator in the actual compressor, which has a certain reference value for the engineering design of the honeycomb seal cavity.

Key words: low-speed research compressor (LSRC), honeycomb, labyrinth, seal clearance, leakage

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