Actions for Study of LH2-fueled topping cycle engine for aircraft propulsion

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Study of LH2-fueled topping cycle engine for aircraft propulsion

Author
Fishbach, L. H.
Published
JAN 1, 1983.
Physical Description
1 electronic document
Additional Creators
Turney, G. E.
Online Version

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Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
An 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.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19830026671.
Accession ID: 83N34942.
NAS 1.15:83466.
E-1735.
NASA-TM-83466.
Aircraft Design Systems and Operations Meeting; 17-19 Oct. 1983; Fort Worth, TX; United States.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15711490