涡轮内等温燃烧数学模型的建立与研究

流体力学与飞行力学

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涡轮内等温燃烧数学模型的建立与研究

郑海飞, 唐豪

南京航空航天大学能源与动力学院, 江苏南京 210016

收稿日期:2011-10-18 修回日期:2012-01-04 出版日期:2012-08-25 发布日期:2012-08-23
通讯作者: 唐豪 E-mail:hao.tang@nuaa.edu.cn
基金资助:
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)

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

ZHENG Haifei, TANG Hao

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received:2011-10-18 Revised:2012-01-04 Online:2012-08-25 Published:2012-08-23
Supported by:
National Natural Science Foundation of China (51076064);Jiangsu. Six Professional Talent Peak (2008136)

摘要/Abstract

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。

关键词: 燃气涡轮, 总体性能, 热力循环, 数学模型, 熵, 等温燃烧

Abstract: 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.

Key words: gas turbine, overall performance, thermodynamic cycle, mathematical model, entropy, isothermal combustion

中图分类号:

V231.1

郑海飞, 唐豪. 涡轮内等温燃烧数学模型的建立与研究[J]. 航空学报, 2012, 33(8): 1400-1405.

ZHENG Haifei, TANG Hao. Establishment and Research on Mathematical Model of Isothermal Combustion Process Inside the Turbine[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, 33(8): 1400-1405.

参考文献

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[14] Chiu Y T. A performance study of a super-cruise engine with isothermal combustion inside the turbine. Blacksburg, Virginia, USA: Virginia Polytechnic Institute and State University, 2004.
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[16] Walsh P P, Fletcher P. Gas turbine performance. Blackwell: Science Ltd, 1998: 113-117.

E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

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

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