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compound cycle engine for helicopter applicationThe compound cycle engine (CCE) is a highly turbocharged, power-compounded, ultra-high-power-density, lightweight diesel engine. The turbomachinery is similar to a moderate-pressure-ratio, free-power-turbine gas turbine engine and the diesel core is high speed and a low compression ratio. This engine is considered a potential candidate for future military helicopter applications. Cycle thermodynamic specific fuel consumption (SFC) and engine weight analyses performed to establish general engine operating parameters and configurations are presented. An extensive performance and weight analysis based on a typical 2-hour helicopter (+30 minute reserve) mission determined final conceptual engine design. With this mission, CCE performance was compared to that of a contemporary gas turbine engine. The CCE had a 31 percent lower-fuel consumption and resulted in a 16 percent reduction in engine plus fuel and fuel tank weight. Design SFC of the CCE is 0.33 lb/hp-hr and installed wet weight is 0.43 lb/hp. The major technology development areas required for the CCE are identified and briefly discussed.
Document ID
19930001160
Document Type
Contractor Report (CR)
Authors
Castor, Jere
(Garrett Turbine Engine Co. Phoenix, AZ, United States)
Martin, John
(Garrett Turbine Engine Co. Phoenix, AZ, United States)
Bradley, Curtiss
(Garrett Turbine Engine Co. Phoenix, AZ, United States)
Date Acquired
September 6, 2013
Publication Date
September 30, 1987
Subject Category
AIRCRAFT PROPULSION AND POWER
Report/Patent Number
GTEC-21-5854-1
NASA-CR-180824
AVSCOM-TR-87-C-30
NAS 1.26:180824
Funding Number(s)
PROJECT: DA PROJ. 1L1-61102-AH-45
CONTRACT_GRANT: NAS3-24346
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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