Preliminary design of a short afterburner for single-spool expendable turbojet engine
Само за регистроване кориснике
2011
Конференцијски прилог (Објављена верзија)
Метаподаци
Приказ свих података о документуАпстракт
A theoretical study related to a short afterburner design is presented in this paper. The objective is to enhance the performance of an existing single-spool expendable turbojet engine in terms of thrust, with a fixed-area exit nozzle. The expendable turbojet engines are generally used in the reconnaissance air vehicles where the engine is positioned in the fuselage near the center of gravity. Consequently, a longer exhaust duct exists before of the nozzle section which can house a short afterburner. An in-house FORTRAN language code is developed to evaluate the performance of single-spool expendable turbojet engine without afterburner and the results of the code are validated with the available experimental data. A short afterburner is designed based on the available length constraints. As a result of the limited length available for the afterburner, combustion chamber has to be considerably shorter than those usually used in the afterburners. Afterburner pressure loss and efficiency ...is calculated iteratively by using afterburner inlet conditions. It is found that by adding the designed short afterburner, about 20% increase in the thrust is achieved at the expense of 50% increase in specific fuel consumption.
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/123456789/1144 AB - A theoretical study related to a short afterburner design is presented in this paper. The objective is to enhance the performance of an existing single-spool expendable turbojet engine in terms of thrust, with a fixed-area exit nozzle. The expendable turbojet engines are generally used in the reconnaissance air vehicles where the engine is positioned in the fuselage near the center of gravity. Consequently, a longer exhaust duct exists before of the nozzle section which can house a short afterburner. An in-house FORTRAN language code is developed to evaluate the performance of single-spool expendable turbojet engine without afterburner and the results of the code are validated with the available experimental data. A short afterburner is designed based on the available length constraints. As a result of the limited length available for the afterburner, combustion chamber has to be considerably shorter than those usually used in the afterburners. Afterburner pressure loss and efficiency is calculated iteratively by using afterburner inlet conditions. It is found that by adding the designed short afterburner, about 20% increase in the thrust is achieved at the expense of 50% increase in specific fuel consumption. PB - American Institute of Aeronautics and Astronautics Inc. C3 - 49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition T1 - Preliminary design of a short afterburner for single-spool expendable turbojet engine DO - 10.2514/6.2011-575 ER -
@conference{ author = "Haider, B.A. and Davidović, Nikola and Durrani, N.", year = "2011", abstract = "A theoretical study related to a short afterburner design is presented in this paper. The objective is to enhance the performance of an existing single-spool expendable turbojet engine in terms of thrust, with a fixed-area exit nozzle. The expendable turbojet engines are generally used in the reconnaissance air vehicles where the engine is positioned in the fuselage near the center of gravity. Consequently, a longer exhaust duct exists before of the nozzle section which can house a short afterburner. An in-house FORTRAN language code is developed to evaluate the performance of single-spool expendable turbojet engine without afterburner and the results of the code are validated with the available experimental data. A short afterburner is designed based on the available length constraints. As a result of the limited length available for the afterburner, combustion chamber has to be considerably shorter than those usually used in the afterburners. Afterburner pressure loss and efficiency is calculated iteratively by using afterburner inlet conditions. It is found that by adding the designed short afterburner, about 20% increase in the thrust is achieved at the expense of 50% increase in specific fuel consumption.", publisher = "American Institute of Aeronautics and Astronautics Inc.", journal = "49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition", title = "Preliminary design of a short afterburner for single-spool expendable turbojet engine", doi = "10.2514/6.2011-575" }
Haider, B.A., Davidović, N.,& Durrani, N.. (2011). Preliminary design of a short afterburner for single-spool expendable turbojet engine. in 49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition American Institute of Aeronautics and Astronautics Inc... https://doi.org/10.2514/6.2011-575
Haider B, Davidović N, Durrani N. Preliminary design of a short afterburner for single-spool expendable turbojet engine. in 49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition. 2011;. doi:10.2514/6.2011-575 .
Haider, B.A., Davidović, Nikola, Durrani, N., "Preliminary design of a short afterburner for single-spool expendable turbojet engine" in 49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition (2011), https://doi.org/10.2514/6.2011-575 . .