超声速涡轮叶栅超声速气膜冷却数值研究

发布时间：2018-01-21 00:04

本文关键词： 超声速涡轮叶栅超声速气膜冷却数值模拟流动特征冷却特性　出处：《推进技术》2016年05期 　论文类型：期刊论文

【摘要】：为了研究超声速涡轮叶栅通道内的超声速气膜冷却,采用数值计算的方法,对主流压比2.33~4、冷气入射角度15°~45°条件下的涡轮叶栅超声速气膜流动和传热进行了研究。计算结果表明:超声速气膜射流与主流作用后产生的斜激波与尾缘激波交汇,形成两道反射激波,其中一道反射激波作用在气膜孔下游的叶片表面又形成了反射;在不同的主流压力下,超声速气膜射流在叶片法向和展向上展现出不同的发展特征,对转涡对(CVP)在展向上相互挤压,扼制了高温主流卷入叶片壁面;主流压比增加到4,气膜射流区在法向拉长,在展向相对较弱,导致主流在对转涡对(CVP)的作用下被卷入气膜射流的底层,壁面冷却效率降低;气膜入射角从15°增大到45°,冷却效率整体上呈先上升后下降趋势,在入射角30°时冷却效率相对最大,这与射流的穿透能力、冷却气流再覆壁面特征有关。
[Abstract]:In order to study supersonic film cooling in supersonic turbine cascade channel, the mainstream pressure ratio of 2.33 / 4 is calculated numerically. The supersonic film flow and heat transfer of turbine cascade at an incident angle of 15 掳to 45 掳have been studied. The confluence of oblique shock wave and trailing edge shock produced by supersonic film jet acting on the main stream. Two reflected shock waves are formed, one of which acts as a reflection on the blade surface downstream of the gas film hole. Under different mainstream pressure, supersonic gas film jet shows different development characteristics in normal direction and spread direction of blade. The opposite vortex pair CVP squeezes each other in the vertical direction, thus choking the high temperature mainstream into the blade wall. When the mainstream pressure ratio is increased to 4, the film jet region is elongated in the normal direction and relatively weak in the direction of direction, which results in the main stream being drawn into the bottom layer of the film jet under the action of the opposite vortex to the CVP, and the cooling efficiency of the wall decreases. When the incident angle of the gas film increases from 15 掳to 45 掳, the cooling efficiency increases first and then decreases, and the cooling efficiency is the largest at 30 掳, which is related to the penetration ability of the jet. The cooling flow is related to the characteristics of the overlying wall.
【作者单位】：南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室;
【基金】：国家自然科学基金(51306088,51106073) 江苏省自然科学基金(BK20130790)
【分类号】：V231.3
【正文快照】： 1引言随着涡轮喷气发动机技术的发展,高温升高压比成为其发展的重要方向,逐步提高的燃烧室出口温度给涡轮叶片带来了严酷的考验,仅依靠叶片材料的耐热性能已无法满足当前涡轮喷气发动机的研制需要。从压气机提取冷却空气对涡轮叶片进行保护,冷却空气形成的气膜覆盖涡轮导向叶

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