한국항공운항학회지 (Journal of the Korean Society for Aviation and Aeronautics)
- 제15권1호
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- Pages.1-10
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- 2007
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- 1225-9705(pISSN)
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- 2466-1791(eISSN)
브레이튼과 펄스 데토네이션 복합 엔진 사이클의 열역학적 성능 해석
Thermodynamic Analysis of Hybrid Engine Cycle of Brayton and Pulse Detonation Engine
- 발행 : 2007.03.31
초록
When detonation is occurred, the working fluid is compressed itself, though there are no other devices that compress the fluid. As a result, an engine which uses detonation for a combustion process doesn't need moving parts so that the engine can be lighter than other engines ever exist, and such an engine is often referred to as a pulse detonation engine. Since using detonation has higher performance than using deflagration, many studies have been attempting to control and analyze the engines using detonation as combustion. The purpose of this study is to analyze the hybrid cycle which is consisted of Brayton and Pulse Detonation Engine cycle. At first, we set the theoretical basis of detonation analysis, and after that we consider two hybrid cycles; a turbojet hybrid cycle and a turbofan hybrid cycle. The more energy released, the higher detonation Mach number the detonation wave has. In general, a cycle which has a detonation process has higher performances but thermal efficiency of hybrid turbofan engine.