方腔折流燃烧室冷态流场研究  

A study on the flowfield of a z-flowpath combustor

作　　者：于宗明[1] 黄勇[1] 王方[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院/航空发动机气动热力重点实验室,北京100191

出　　处：《推进技术》2010年第5期533-538,共6页Journal of Propulsion Technology

摘　　要：方腔折流燃烧室是针对小型燃气涡轮发动机所设计的新型燃烧室设计方案,其目的是为了克服常规回流燃烧室所存在的总压损失较大、出口温度分布控制困难等问题。通过对方腔折流燃烧室和回流燃烧室的冷态流场进行数值模拟,发现在相同的工况下,方腔折流燃烧室具有对称的头部流场,其回流区空间尺度是常规回流燃烧室的9.4倍,回流强度是常规回流燃烧室的1.8倍,而火焰筒壁面总面积仅为常规回流燃烧室的51%,进出口总压损失仅为常规回流燃烧室的69.4%。Reverse flow combustors were widely used in small and micro gas turbine engines.The high pressure loss and inadequate main flow dilution were two intrinsic problems for them.In order to improve the combustion capability,a new conceptual z-flowpath combustor was proposed.The new combustor consisted of two 45° yawing instead of returning in the main flow-path.The prediction showed that the flowfield of the primary zone in the z-flowpath combustor was highly symmetrical,the size and the intensity of the recirculation zone were about 9.4 and 1.8 times greater than the normal reverse flow combustor,respectively,while the pressure loss and the total area of the flame tube wall of the z-flowpath combustor were decreased dramatically to be 69.4% and 51% of that in the reverse flow combustor,respectively.

关 键 词：燃烧室 方腔折流燃烧室 流动分布 数值仿真 

分 类 号：V235.113[航空宇航科学与技术—航空宇航推进理论与工程]