面向方案设计阶段的发动机质量评估方法  

Estimation Method of Aeroengine Weight at Concept Design Stage

作　　者：胡殿印 胡丹[1,3] 霍枫[3] 樊江[1,2] 陈高翔[1,2] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191 [2]先进航空发动机协同创新中心,北京100191 [3]中航工业沈阳发动机设计研究所,沈阳110015

出　　处：《航空发动机》2016年第2期27-33,共7页Aeroengine

基　　金：国家自然科学基金(51305012;51375031);航空科学基金(2014ZB51)资助

摘　　要：为了在航空发动机方案设计阶段准确地预估发动机质量,提高质量估算模型的估算精度,针对发动机方案设计阶段的特点,建立了航空发动机质量估算初级模型;考虑转子件的应力水平要求,完善了轮盘、叶片、轴等典型转子件的质量估算高级模型。建立了相应的模型数据库,并开发了面向方案设计阶段的发动机质量评估平台。利用该平台分别对初级模型和叶片、盘、轴等典型转子件的高级模型进行了计算验证。结果表明:初级模型的估算误差在25%之内,高级模型转子件的估算误差在7%之内。证明所提出的质量估算初、高级模型具有较高的精度,可用于发动机方案设计阶段的质量评估。In order to accurately estimate the weight of aeroengine in the stage of concept design and improve prediction accuracy of evaluation model. Aiming at design characteristics in the stage of aeroengine concept design, a primary model was established. Meanwhile,in view of the strength requirements,advanced models to predict the weights of the components including disk, blade and shaft were improved. Model database was established and the aeroengine weight estimation platform for concept design stage was developed. The primary model and advanced model were calculated and verificated by the platform. The results show that the errors of the primary and advanced weight models are 25% and 7% respectively, confirming that the primary model and advanced model have higher accuracy and can be used for evaluating the components＇ weights in the concept design of aeroengine.

关 键 词：质量预估 初级模型 高级模型 应力水平 方案设计阶段 航空发动机 

分 类 号：V232.3[航空宇航科学与技术—航空宇航推进理论与工程]