涡轮内等温燃烧数学模型的建立与研究  

Establishment and Research on Mathematical Model of Isothermal Combustion Process Inside the Turbine

作　　者：郑海飞[1] 唐豪[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《航空学报》2012年第8期1400-1405,共6页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(51076064);江苏省"六大人才高峰"第五批高层次人才项目(2008136)~~

摘　　要：针对目前在涡轮内燃烧技术的研究中,等温燃烧数学模型较为复杂以及这些模型中利用了较为复杂的熵进行计算等工程技术问题,从等温过程的基本热力过程原理出发,推导出新的涡轮内等温燃烧数学模型。通过数学模型之间的比较与分析以及计算结果与文献之间的比较与分析之后,得出结论:①在采用涡轮内燃烧技术的航空发动机总体热力性能计算中,推导出的涡轮内等温燃烧数学模型的应用具有可行性;②新建立的涡轮内等温燃烧数学模型更为简便,可以大幅度地提高编程效率和计算效率,在工程实际中具有较好的应用性。The present mathematical models of the isothermal combustion process inside the turbine employed in engineering analysis are all complex involving complex entropies. This paper proposes a mathematical model of the combustion inside the turbine derived from the basic principle of the isothermal process. By comparison and analysis between the proposed and earlier mathematical models, and by comparison and analysis between the earlier and new calculated results, the following conclusions can be drawn： a） Analysis of the overall performance of an aircraft engine using combustion inside the turbine demonstrates that the present mathematical model is superior; b） The new mathematical model is simpler and more convenient, since the programming and computational efficiency can be greatly improved. Therefore it has great potential for application in engineering practice.

关 键 词：燃气涡轮 总体性能 热力循环 数学模型 熵 等温燃烧 

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]