Thermodynamic Analysis of Helium System Cycle for the Precooled Air-breathing Combined Engine
- Paper number
IAC-17,C4,9,5,x37206
- Author
Mr. Yan Zhu, Xi'an Aerospace Propulsion Institute, China
- Coauthor
Dr. Yuan Ma, Xi'an Aerospace Propulsion Institute, China
- Coauthor
Dr. Xiangyi NAN, Academy of Aerospace Propulsion Technology (CASC), China
- Coauthor
Dr. Guangxi Li, China
- Coauthor
Mr. Shangrong YANG, Science and Technology on Liquid Rocket Engine Laboratory, Xi’an Aerospace Propulsion Institute, China
- Year
2017
- Abstract
Precooled air-breathing combined engine is a typical scheme for the reusable hypersonic vehicle, a helium cycle is introduced between the air cycle and fuel cycle as the intermediate medium in order to improve the engine performance and reliability, and it has become an important research filed of such precooled engine. Based on the features of engine system, a mathematical model of helium cycle system including the main components was established in this paper. Through the calculation and analysis of its working process, the system charateristics and the variation law and thermodynamic cycle efficiency are obtained during the for the whole operating envelope. The analysis of thermodynamic loss shows that the energy loss of helium cycle system is from the internal irreversible factors which are non-isentropic compression and expansion, heat leakage and friction loss, and the magnitudes of all kinds losses have the same magnitude. The results indicate that increasing the maximum temperature and the lowest temperature ratio of the helium cycle will increase the external output power of the system. Since the heat dissipation is effectively utilized during the cycle, the cycle efficiency can still be maintained above 90\% in overall working conditions.
- Abstract document
- Manuscript document
IAC-17,C4,9,5,x37206.doc (🔒 authorized access only).
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