大涵道涡扇发动机高温高压燃烧室试验器法兰保温方法研究  

Research on flange insulation method of high-temperature and high-pressure combustion test facility for large bypass turbofan engine

作　　者：孟刚 何鑫 王银 袁逸人 MENG Gang;HE Xin;WANG Yin;YUAN Yiren(AECC Commercial Aircraft Engine Co.,Ltd,Shanghai 200241,China)

机构地区：[1]中国航发商用发动机有限责任公司,上海200241

出　　处：《推进技术》2024年第10期236-246,共11页Journal of Propulsion Technology

基　　金：国家大型飞机重大专项。

摘　　要：高温高压燃烧室试验器是我国大飞机大涵道涡扇发动机研制的重要试验平台。目前,国内同类试验器的进气参数仅停留在3 MPa和700℃以内的水平。针对高温高压燃烧室试验器进气法兰的保温方法,参考国外更高水平的燃烧室试验器设计了外部保温、外部加热、内部保温及内外同时保温4种方案,并采用有限元分析和美国ASME相关标准计算了不同升/降温速率下每种保温方案对应的温度场、应力场、疲劳和蠕变损伤。仿真结果表明,内部屏蔽隔热保温方式既能满足进气保温和升温速率要求,又能降低疲劳损伤和蠕变损伤,满足高温高压燃烧室试验器使用的长寿命要求。High-temperature and high-pressure combustion test facility is an important test platform for the development of large bypass turbofan engines for large aircraft in China.At present,the air inlet parameters of the Chinese similar test facilities only stay within the level of 3 MPa and 700°C.In terms of insulation method of air inlet flange for high-temperature and high-pressure combustion test facility,four schemes of external insula⁃tion,external heating,internal insulation and simultaneous internal and external insulation are designed with ref⁃erence to the designing experience of much advanced foreign test facilities.Finite element analysis and American ASME related standards were used to calculate the temperature field,stress field,fatigue and creep damage of the flange corresponding to each insulation scheme at different air temperature rise/drop rates.The simulation re⁃sults show that the internal shielding method can not only meet the requirements of inlet air thermal insulation and heating rate,but also reduce fatigue damage and creep damage,and meet the long-life requirement of the test facility.

关 键 词：大涵道涡扇发动机 高温高压燃烧室 试验器 法兰保温 疲劳 蠕变 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]