基于微小孔冷却的燃烧室先进冷却技术研究综述  

A Review of Advanced Cooling Technology for Combustor Based on Micro-hole

作　　者：张鹏峰[1] 蔡文哲 Zhang Pengfeng;Cai Wenzhe(Naval Military Representative Office in the Third Research Academy, CASIC, Beijing;Beihang University,Beijing 100191, China;Beijing Power Machinery Institute, Beijing 100074, China;100074, China)

机构地区：[1]海军驻航天三院军事代表室,北京100074 [2]北京航空航天大学,北京100191 [3]北京动力机械研究所,北京100074

出　　处：《战术导弹技术》2018年第2期95-101,共7页Tactical Missile Technology

摘　　要：通过对涡轮发动机用微小孔冷却技术的研究现状进行总结分析,介绍了冲击冷却、发散冷却、异型孔冷却、冲击-发散冷却等复合冷却技术的原理、特点、发展以及应用情况。研究表明冲击冷却和气膜冷却作为单一冷却手段,难以获得较高的冷却效率。现代高热力循环参数的涡轮发动机往往采用冲击/发散/对流等复合冷却方案,部分复合冷却方案能够满足出口温度1850K的燃烧室应用需求。与此同时,采用RANS模型开展微小孔冷却技术数值模拟研究的方法是一种可行的手段,其中标准K-ε具有较高精度,但仍需发展更高精度的冷却仿真模型。Base on the present research on micro-hole cooling technology in combustor of turbo engine,the development and application of advanced composite cooling technology,such as impingement-cooling,discrete hole cooling and special-shaped hole cooling,impingement/effusion cooling are introduced.Impingement-cooling and discrete hole cooling as a single is difficult to directly apply to turbine engines which have high thermal cycle parameters.But application of both impingement cooling system and effusion cooling system design can meet the demand of advanced turbine vane whose inlet temperature of reach up to 1850 K or higher.Meanwhile,the RANS model,especially the standard K-ε model,is a feasible method to numerically simulate the process of micro-hole cooling,but more accurate model should be developed.

关 键 词：燃烧室 微小孔 复合冷却 

分 类 号：V235.11[航空宇航科学与技术—航空宇航推进理论与工程]