Parametric analysis of expendable type single-spool turbojet engine with a short afterburner
Само за регистроване кориснике
2011
Конференцијски прилог (Објављена верзија)
Метаподаци
Приказ свих података о документуАпстракт
A parametric, on-design performance analysis of an existing single-spool expendable turbojet engine with a short afterburner is presented in this paper. A design point mathematical model of the engine is developed to obtain the optimum system performance conditions and is implemented in a FORTRAN code. This model utilizes the engine design parameters, such as operating flight conditions, compressor pressure ratio, turbine inlet temperature, and afterburner exit temperature to predict the engine performance parameters, such as specific thrust and specific fuel consumption. Based on the same flight conditions and engine design parameters, an analysis is done by using commercial software, GasTurb, used for the performance analysis of gas turbine engines. The results obtained from the developed design point code are in a good agreement with the GasTurb and the available experimental data. Subsequently, the effects of adding a short afterburner on the performance of the engine are studied u...sing a parametric analysis. A theoretical database for different performance parameters is obtained as a design reference for the future work.
Извор:
49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, 2011Издавач:
- American Institute of Aeronautics and Astronautics Inc.
Колекције
Институција/група
Mašinski fakultetTY - CONF AU - Haider, B.A. AU - Davidović, Nikola AU - Durrani, N. PY - 2011 UR - https://machinery.mas.bg.ac.rs/handle/123456789/1143 AB - A parametric, on-design performance analysis of an existing single-spool expendable turbojet engine with a short afterburner is presented in this paper. A design point mathematical model of the engine is developed to obtain the optimum system performance conditions and is implemented in a FORTRAN code. This model utilizes the engine design parameters, such as operating flight conditions, compressor pressure ratio, turbine inlet temperature, and afterburner exit temperature to predict the engine performance parameters, such as specific thrust and specific fuel consumption. Based on the same flight conditions and engine design parameters, an analysis is done by using commercial software, GasTurb, used for the performance analysis of gas turbine engines. The results obtained from the developed design point code are in a good agreement with the GasTurb and the available experimental data. Subsequently, the effects of adding a short afterburner on the performance of the engine are studied using a parametric analysis. A theoretical database for different performance parameters is obtained as a design reference for the future work. PB - American Institute of Aeronautics and Astronautics Inc. C3 - 49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition T1 - Parametric analysis of expendable type single-spool turbojet engine with a short afterburner DO - 10.2514/6.2011-574 ER -
@conference{ author = "Haider, B.A. and Davidović, Nikola and Durrani, N.", year = "2011", abstract = "A parametric, on-design performance analysis of an existing single-spool expendable turbojet engine with a short afterburner is presented in this paper. A design point mathematical model of the engine is developed to obtain the optimum system performance conditions and is implemented in a FORTRAN code. This model utilizes the engine design parameters, such as operating flight conditions, compressor pressure ratio, turbine inlet temperature, and afterburner exit temperature to predict the engine performance parameters, such as specific thrust and specific fuel consumption. Based on the same flight conditions and engine design parameters, an analysis is done by using commercial software, GasTurb, used for the performance analysis of gas turbine engines. The results obtained from the developed design point code are in a good agreement with the GasTurb and the available experimental data. Subsequently, the effects of adding a short afterburner on the performance of the engine are studied using a parametric analysis. A theoretical database for different performance parameters is obtained as a design reference for the future work.", publisher = "American Institute of Aeronautics and Astronautics Inc.", journal = "49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition", title = "Parametric analysis of expendable type single-spool turbojet engine with a short afterburner", doi = "10.2514/6.2011-574" }
Haider, B.A., Davidović, N.,& Durrani, N.. (2011). Parametric analysis of expendable type single-spool turbojet engine with a short afterburner. in 49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition American Institute of Aeronautics and Astronautics Inc... https://doi.org/10.2514/6.2011-574
Haider B, Davidović N, Durrani N. Parametric analysis of expendable type single-spool turbojet engine with a short afterburner. in 49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition. 2011;. doi:10.2514/6.2011-574 .
Haider, B.A., Davidović, Nikola, Durrani, N., "Parametric analysis of expendable type single-spool turbojet engine with a short afterburner" in 49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition (2011), https://doi.org/10.2514/6.2011-574 . .