This paper concerns to the inverted turbo-jet engine intended for operation in the range of Mach numbers from 0 to 6. In the present engine configuration, which is based on the inverted Brayton cycle, the sequence of the core-engine components was arranged in the order: turbine - heat exchanger - compressor - combustor. It should also be noted that the inverted Brayton cycle has also been considered for application to stationary power generation systems in the role of a bottoming cycle. An improved version of the inverted turbo-jet engine (ITE), has also been proposed in the present paper, incorporates an additional combustor installed between the inlet and the turbine. At low speeds this additional burner allows a heat input upstream of the initial turbine to augment thrust. The fuel-rich mode of operation is expected to be beneficial, as speed increases. In summary, the inverted turbojet engine can produce sufficient thrust compared to another engine concepts and it reveals high energy efficiency over the wide speed of range.
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ASME Turbo Expo 2005: Power for Land, Sea, and Air
June 6–9, 2005
Reno, Nevada, USA
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
0-7918-4728-4
PROCEEDINGS PAPER
Inverted Turbo-Jet Engine for Hypersonic Propulsion
Yoshiharu Tsujikawa,
Yoshiharu Tsujikawa
Osaka Prefecture University, Sakai, Japan
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Ken-Ichi Kaneko,
Ken-Ichi Kaneko
Osaka Prefecture University, Sakai, Japan
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Shusuke Tokumoto
Shusuke Tokumoto
Osaka Prefecture University, Sakai, Japan
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Yoshiharu Tsujikawa
Osaka Prefecture University, Sakai, Japan
Ken-Ichi Kaneko
Osaka Prefecture University, Sakai, Japan
Shusuke Tokumoto
Osaka Prefecture University, Sakai, Japan
Paper No:
GT2005-68947, pp. 343-349; 7 pages
Published Online:
November 11, 2008
Citation
Tsujikawa, Y, Kaneko, K, & Tokumoto, S. "Inverted Turbo-Jet Engine for Hypersonic Propulsion." Proceedings of the ASME Turbo Expo 2005: Power for Land, Sea, and Air. Volume 5: Turbo Expo 2005. Reno, Nevada, USA. June 6–9, 2005. pp. 343-349. ASME. https://doi.org/10.1115/GT2005-68947
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