Effects of Circumferential Casing Groove on Tip Leakage Flow Structures and Aerodynamic Characteristics of Transonic Turbine

被引：0
|
作者：
Li W.-Q. [1 ]
Tao Z. [1 ]
Song L.-M. [1 ]
Li J. [1 ]
Feng Z.-P. [1 ]
机构：
[1] School of Energy and Power Engineering, Xi’an Jiaotong University, Xi’an
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2023年 / 44卷 / 02期
关键词：
Aerodynamic characteristics; Circumferential casing groove configuration; Control of leakage flow; Rotor blade tip; Transonic turbine stage;
D O I：
10.13675/j.cnki.tjjs.2208024
中图分类号：
学科分类号：
摘要：
In order to control the tip leakage flow and improve the flow field quality of the turbine blade tip，a circumferential casing groove configuration was proposed. Taking the typical transonic turbine stage TTM（Thermal Turbomachinery and Machine Dynamics）as the research object，the effects of circumferential casing grooves （CG）with different heights on tip leakage flow structures and aerodynamic characteristics of turbine were investigated numerically. The results show that due to the introduction of CG，the vortex system topology in the tip region changes a lot. The tip leakage vortex（TLV）is divided into two parts，with the TLV-1 passing through the upper passage vortex（UPV）and being consumed gradually and the TLV-2 rebuilding behind the CG and extending to the trailing edge. As a result，the strength and size of the TLV are reduced. In addition，due to the weakening of the pressure side leg of horseshoe vortex（HVP）caused by the swirling of the CG and the suppression and consumption of the TLV-1，the UPV is far away from the casing and the interaction between the UPV and the TLV is weakened，leading to the reduction of the strength and size of the UPV. Overall，as the height of CG increases，the tip leakage rate decreases gradually，and the total-to-static efficiency of the turbine stage increases first and then decreases. Compared with the casing without any treatment，when the height of CG equals twice the tip gap，the tip leakage rate decreases by 0.15%，and the total-to-static efficiency of the turbine stage increases by 0.31%. © 2023 Journal of Propulsion Technology. All rights reserved.
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