等离子体激励对高温燃气涡轮叶顶间隙泄漏流抑制效果研究  

Study on the Suppression Effect of Plasma Actuation on Leakage Flow in High-Temperature Gas Turbine Blade Tip Clearance

作　　者：陈博 王天壹 宣益民[1] CHEN Bo;WANG Tianyi;XUAN Yimin(School of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《工程热物理学报》2025年第3期790-799,共10页Journal of Engineering Thermophysics

基　　金：国家科技重大专项(No.2017-Ⅲ-0010-0036)。

摘　　要：本文以某高压涡轮转子叶顶间隙泄漏流为研究对象,在构建涡轮环境燃气物性计算方法及变激励条件下等离子体最大电荷密度参数计算方法的基础上,采用数值模拟分析等离子体激励在高温燃气流条件下对涡轮叶顶间隙泄漏流的影响机制,探究不同外加激励条件下机匣激励器及其阵列式布置对泄漏流抑制效果的影响。研究表明,增加激励强度可以提高机匣激励器对泄漏流的抑制效果,单级激励器外加激励从0增加至200时,相对泄漏量减少24.78%。多级激励器协同作用可以提升抑制效果,但多激励器阵列式布置会产生级间电势干扰,改变电势和电场分布,产生促进泄漏流流动的因素,导致阵列式激励器对泄漏流的抑制效果相比单级激励器提升较小。This paper focuses on the leakage flow between high-pressure turbine rotor blades as the research subject.Based on the establishment of computational methods for gas properties in the turbine environment and the calculation of maximum charge density parameters of plasma under vari-able actuation conditions,numerical simulation analysis is adopted to investigate the impact mecha-nism of plasma actuation on leakage flow at turbine blade tip clearances under high-temperature gas flow conditions.It explores the effects of different external actuation conditions and the arrangement of the actuation devices,including shroud single-stage actuator and their array configurations,on the suppression of leakage flow.The research indicates that increasing actuation intensity can enhance the suppression effect of actuator on leakage flow.When external actuation is increased from 0 to 200 for a single-stage actuator,the relative leakage reduction is 24.78%.The synergistic effect of multi-stage actuators can further improve the suppression effect.However,the array arrangement of multiple actuators may lead to inter-stage potential interference,altering potential and electric field distributions,generating factors that promote leakage flow,thereby resulting in a relatively smaller improvement in suppression effect compared to single-stage actuator.

关 键 词：航空发动机 间隙泄漏流 等离子体激励 流动控制 介质阻挡放电 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]