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Study of advanced rotary combustion engines for commuter aircraftPerformance, weight, size, and maintenance data for advanced rotary aircraft engines suitable for comparative commuter aircraft system evaluation studies of alternate engine candidates are provided. These are turbocharged, turbocompounded, direct injected, stratified charge rotary engines. Hypothetical engines were defined (an RC4-74 at 895 kW and an RC6-87 at 1490 kW) based on the technologies and design approaches used in the highly advanced engine of a study of advanced general aviation rotary engines. The data covers the size range of shaft power from 597 kW (800 hp) to 1865 kW (2500 hp) and is in the form of drawings, tables, curves and written text. These include data on internal geometry and configuration, installation information, turbocharging and turbocompounding arrangements, design features and technologies, engine cooling, fuels, scaling for weight size BSFC and heat rejection for varying horsepower, engine operating and performance data, and TBO and maintenance requirements. The basic combustion system was developed and demonstrated; however the projected power densities and performance efficiencies require increases in engine internal pressures, thermal loading, and rotative speed.
Document ID
19830009274
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Berkowitz, M.
(Curtiss-Wright Corp. Wood-Ridge, NJ, United States)
Jones, C.
(Curtiss-Wright Corp. Wood-Ridge, NJ, United States)
Myers, D.
(Curtiss-Wright Corp. Wood-Ridge, NJ, United States)
Date Acquired
September 4, 2013
Publication Date
February 1, 1983
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-CR-165399
NAS 1.26:165399
CW-WR-81-022F
Accession Number
83N17545
Funding Number(s)
CONTRACT_GRANT: NAS3-22140
PROJECT: RTOP 505-40-6B
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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