换热效应对燃气涡轮发动机过渡态性能的影响  

Effects of heat soakage on transient performance of gas turbine engine

作　　者：屠秋野[1,2] 贾锐[1,2] 薛萱[1,2] 郑恒 严红明 

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]先进航空发动机协同创新中心,北京100191 [3]中国航空发动机集团有限公司商用航空发动机有限责任公司,上海200241

出　　处：《航空动力学报》2017年第3期630-636,共7页Journal of Aerospace Power

摘　　要：在非定常换热模型基础上,提出了换热效应不影响旋转部件功的假设,以及气冷涡轮换热的简化处理方法,建立了考虑换热效应的发动机过渡态性能计算模型.针对某双转子涡扇发动机加减速过程进行了数值模拟.结果表明:换热效应对整机性能的影响主要表现为各部件的响应滞后,而低压转子的响应滞后最为明显;压气机的换热时间常数小于涡轮;在旋转部件中,叶片的换热时间常数最小,轮毂次之,机匣最大.With an unsteady heat transfer model, an assumption of neglecting the effects of heat transfer on the work of rotating components and a simplified heat transfer model of cooled turbine were put forward, and a transient engine model was built by taking the heat soakage into account. The numerical simulation results of a turbofan engine transient performance showed that, the main effects of heat transfer soakage on the engine performance were attributable to the response delay in each component, which was more serious in low pressure components. The thermal time constants of the compressor were smaller than those of the turbine. For the thermal time constants of the same component, the blade was the smallest, the hub was larger, and the casing was the largest.

关 键 词：燃气涡轮发动机 过渡态 换热效应 性能模拟 响应滞后 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]