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Propulsion Systems with Air Precooling for Aerospaceplane
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English
Abstract
Using LH2 heat sink capacity for air precooling in turbojets allows to increase specific impulse and in many cases to reduce specific mass (mass-to-sea level thrust ratio).
A number of precooled turbojet schemes are considered. Classification of turbojet according to the cooled air amount and depth of cooling is proposed. ATR with extended precooling (Tout=100K) is examined in more detail.
For propulsion systems including different types of engines, running simultaneously the concept of LH2 heat sink capacity concentration for turbojet air precooling is proposed.
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Citation
Rudakov, A. and Balepin, V., "Propulsion Systems with Air Precooling for Aerospaceplane," SAE Technical Paper 911182, 1991, https://doi.org/10.4271/911182.Also In
References
- Aoki T. Ogawara A. Study of LACE for SSTO space plane IAF-88-252
- Powell T.H. Glickstein M.R. Precooled turbojet engine cycle for high Mach number applications AIAA-88-2946