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Design of aircraft turbine fan drive gear transmission systemThe following basic types of gear reduction concepts were studied as being feasible power train systems for a low-bypass-ratio, single-spool, geared turbofan engine for general aircraft use: (1) single-stage external-internal reduction, (2) gears (offset shafting), (3) multiple compound idler gear system (concentric shafting), and (4) star gear planetary system with internal ring gear final output member (concentric shafting-counterrotation). In addition, studies were made of taking the accessories drive power off both the high-speed and low-speed shafting, using either face gears or spiral bevel gears. Both antifriction and sleeve-type bearings were considered for the external-internal and star-planet reduction concepts.
Document ID
19720004764
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Dent, E.
(General Motors Corp. Indianapolis, IN, United States)
Hirsch, R. A.
(General Motors Corp. Indianapolis, IN, United States)
Peterson, V. W.
(General Motors Corp. Indianapolis, IN, United States)
Date Acquired
September 2, 2013
Publication Date
March 1, 1970
Publication Information
Publisher: NASA
Subject Category
Machine Elements And Processes
Report/Patent Number
NASA-CR-72735
Accession Number
72N12413
Funding Number(s)
CONTRACT_GRANT: NAS3-12417
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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