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Study of a LH2-fueled topping cycle engine for aircraft propulsionAn analytical investigation was made of a topping cycle aircraft engine system which uses a cryogenic fuel. This system consists of a main turboshaft engine which is mechanically coupled (by cross-shafting) to a topping loop which augments the shaft power output of the system. The thermodynamic performance of the topping cycle engine was analyzed and compared with that of a reference (conventional-type) turboshaft engine. For the cycle operating conditions selected, the performance of the topping cycle engine in terms of brake specific fuel consumption (bsfc) was determined to be about 12 percent better than that of the reference turboshaft engine. Engine weights were estimated for both the topping cycle engine and the reference turboshaft engine. These estimates were based on a common shaft power output for each engine. Results indicate that the weight of the topping cycle engine is comparable to that of the reference turboshaft engine. Previously announced in STAR as N83-34942
Document ID
19840032420
Document Type
Conference Paper
Authors
Turney, G. E. (NASA Lewis Research Center Cleveland, OH, United States)
Fishbach, L. H. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 12, 2013
Publication Date
October 1, 1983
Subject Category
AIRCRAFT PROPULSION AND POWER
Report/Patent Number
AIAA PAPER 83-2543
Distribution Limits
Public
Copyright
Other