涡轮内等温燃烧数学模型的建立与研究

Abstract

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

CLC Number:

V231.1

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.

References

[1] Sirignano W A, Delplanque J P, Liu F. Selected challenges in jet and rocket engine combustion research. AIAA-1997-2701, 1997.
[2] Sirignano W A, Liu F. Performance increases for gas turbine engines through combustion inside the turbine. Journal of Propulsion and Power, 1999, 15(1): 111-118.
[3] Ramohalli K N R. Isothermal combustion for improved efficiencies. AIAA-1987-1999, 1987.
[4] Liu F, Sirignano W A. Turbojet and turbofan engine performance increases through turbine burners. AIAA-2000-0741, 2000.
[5] Andriani R, Gamma F, Ghezzi U, et al. Design proposals for constant temperature turbine engine for propulsion system. AIAA-2001-3750, 2001.
[6] Chen G, Hoffman M A, Davis R L. Improvements in gas-turbine performance through the use of multiple turbine inter-stage burners. AIAA-2004-374, 2004.
[7] Liew K H, Urip E, Yang S L, et al. A complete parametric cycle analysis of a turbofan with an interstage turbine burner. AIAA-2003-685, 2003.
[8] Qi S J, Cai Y H, Wang Z X, et al. Application of after-burning between high and low turbines to improve performance of two-spool turbofan engine. Journal of Propulsion Technology, 2002, 23(6): 453-456.(in Chinese) 齐少军, 蔡元虎, 王占学, 等. 用高低涡轮间补燃提高双轴涡扇发动机性能.推进技术, 2002, 23(6): 453-456.
[9] Pan X, Ge N. Parametric (on-design) analysis for a separate-exhaust turbofan engine with interstage turbine burner. Gas Turbine Experiment and Research, 2007, 20(3): 34-38. (in Chinese) 潘旭, 葛宁. 带涡轮燃烧室的涡扇发动机设计点性能分析. 燃气涡轮试验与研究, 2007, 20(3): 34-38.
[10] Li Q, Fan W. Parametric cycle analysis of dual-spool mixed-exhaust turbofan with interstage turbine burner. AIAA-2007-651, 2007.
[11] Sun Z H, Cai Y H, Tu Q Y. Parametric cycle analysis of mixed exhaust turbofan with interstage turbine burner. Journal of Propulsion Technology, 2010, 31(2): 139-142. (in Chinese) 孙泽晖, 蔡元虎, 屠秋野. 带混排涡轮级间燃烧的涡扇发动机循环参数. 推进技术, 2010, 31(2): 139-142.
[12] Cheng B L, Tang H, Xu X, et al. Performance study on turbofan engine with turbine inter burner. Aeroengine, 2010, 36(6): 18-21. (in Chinese) 程本林, 唐豪, 徐夏,等. 带TIB的涡扇发动机性能研究. 航空发动机, 2010, 36(6): 18-21.
[13] Cheng B L. A new concept of turbojet and turbofan engine performance increases through turbine inter-blade burner. Nanjing: College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, 2011. (in Chinese) 程本林. 提高涡轮发动机性能的新概念方法——涡轮通道内补燃循环性能研究. 南京: 南京航空航天大学能源与动力学院, 2011.
[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.
[15] Shen W D, Jiang Z M, Tong J G. Engineering thermodynamics. 3rd ed. Beijing: Higher Education Press, 2001: 89-90. (in Chinese) 沈维道, 蒋智敏, 童钧耕. 工程热力学. 3版.北京: 高等教育出版社, 2001: 89-90.
[16] Walsh P P, Fletcher P. Gas turbine performance. Blackwell: Science Ltd, 1998: 113-117.

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

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