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Blade retainer assemblyA retaining assembly is provided for locking radially extending blades in a rotor disc associated with a gas turbine engine. The assembly includes a pair of spaced apart lugs axially extending from one side of the disc to form an access gap for insertion of a blade tang into a dovetail slot in the rotor disc. A pair of axially aligned inwardly facing recesses are disposed in the lugs. A retaining member resides in the recesses and extends across the gap to preclude egress of the blade tang from the dovetail slot. The retaining member includes at least one axially extending protrusion adapted to radially overlap and abuttingly engage a radially inwardly facing abutment surface on the lugs.
Document ID
19770020172
Acquisition Source
Legacy CDMS
Document Type
Other - Patent
Authors
Luebering, G. W.
(GE Cincinnati, United States)
Date Acquired
August 8, 2013
Publication Date
July 5, 1977
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
Patent Application Number: US-PATENT-APPL-SN-680067
Patent Number: NASA-CASE-LEW-12608-1
Patent Number: US-PATENT-4,033,705
Accession Number
77N27116
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
NASA-CASE-LEW-12608-1|US-PATENT-4,033,705
Patent Application
US-PATENT-APPL-SN-680067
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