Effect of Combustor Outflow Conditions on the Flow Structure and Heat Transfer Cooling Characteristics of Turbine Vane Endwall

被引：1
|
作者：
Sun T. [1 ]
Zhang K. [1 ]
Li Z. [1 ]
Li J. [1 ]
机构：
[1] Institute of Turbomachinery, Xi'an Jiaotong University, Xi'an
来源：
Hsi-An Chiao Tung Ta Hsueh/Journal of Xi'an Jiaotong University | 2023年 / 57卷 / 01期
关键词：
combustor swirling flow; effusion cooling; flow structure; vane endwall;
D O I：
10.7652/xjtuxb202301015
中图分类号：
学科分类号：
摘要：
This paper, through the numerical analysis research, investigates the aerodynamic characteristics of the turbine vane cascade, flow structures near the turbine vane endwall, total pressure loss coefficient, heat transfer and cooling characteristics on the endwall and vane surface, and the flow trend of the cooling air under different conditions with different clocking positions and whirling directions of the combustor swirler. A simplified model of twin annular pre-mixing swirler(TAPS)combustor is established, and the overall numerical calculation is carried out by including the turbine nozzle vane cascade combined and the combustor section as a whole. The obtained results show that the TAPS combustor calculation model used in this paper has a swirl number of 0.71 at the outlet of the swirler, which can represent the typical flow characteristics of a lean-burn premixed combustor. The emission of cooling air from the inner wall of the flame tube leads to a high total pressure area near the vane endwall, while combustor swirling flow reduces the total pressure at mid-span position. The positive swirling flow is separated into two streams at the vane leading-edge, while the negative swirling flow enters one cascade as a whole. The combustor swirling flow significantly enhances the upstream heat transfer on the vane suction side. The positive swirling flow negatively affects the cooling effect on the pressure side of the hub endwall. The local blowing ratio of slot jet flow is the lowest at the stagnation point, but when the swirler is aligned with the vane leading-edge, the swirling flow weakens the influence of the stagnation point. The flow structure, heat transfer and cooling characteristics of the vane endwall are significantly affected by the combustor outflow conditions, which need to be considered when optimizing the aerodynamic performance of vane cascade and designing the cooling structure. © 2023 Xi'an Jiaotong University. All rights reserved.
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页码：152 / 163
页数：11
相关论文
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