引气冷却模型对涡轴发动机总体性能的影响研究  

Research on the Influence of Bleeding and Cooling Model on the Performance of Turboshaft Engine

作　　者：胡秋晨 陈玉春[1] 贾琳渊[1] 黄兴[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《航空工程进展》2014年第1期109-115,共7页Advances in Aeronautical Science and Engineering

摘　　要：随着现代涡轴发动机性能的不断提高,其热力循环参数和引气量显著增加。针对这一问题,建立考虑压气机引气位置可变和涡轮中冷却气参与做功的涡轴发动机性能计算模型。当压气机引气位置变化时,采用流量平衡和功率平衡同时修正法计算发动机性能;涡轮冷却计算模型则考虑了第一级导向器叶片冷却气的做功。与传统涡轴发动机性能计算模型的计算结果对比表明:本文的计算模型能够合理反映引气量和引气位置对发动机特性的影响,更接近发动机的真实物理过程,可为发动机空气系统设计提供输入。With the constant improvement of performance of modern turboshaft engine, its thermodynamic cycle parameters and the amount of bleeding are significantly increased. To solve this problem, for free turbine tur- boshaft engine with high thermodynamic parameters and high-bleed, a new turboshaft performance calculation model which considers bleed position and cooling air expansion work is established. The model of air bleeding in the middle of the compressor corrects the flow balance and power balance at the same time. The turbine cooling model considers the cooling air expansion work. The calculation results obtained by the new model are analyzed and compared with that of simple turbine bleed and cooling model, which proves that the new model can obtain the influence of the amount of bleeding and bleeding position on the performance of turboshaft engine. The new model is close to the true physical process of turboshaft engine, and can offer input to the air system.

关 键 词：自由涡轮涡轴发动机 压气机引气模型 涡轮冷却模型 引气量 总体性能 

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]