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Turbine engine variable geometry deviceA variable geometry device for use with the turbine nozzle of a turbine engine of the type having a support housing and a combustion chamber contained within the support housing. A pair of spaced walls in the support housing define an annular and radially extending nozzle passageway. The outer end of the nozzle passageway is open to the combustion chamber while the inner end of the nozzle passageway is open to one or more turbine stages. A plurality of circumferentially spaced nozzle vanes are mounted to one of the spaced walls and protrude across the nozzle passageway. An annular opening is formed around the opposite spaced wall and an annular ring is axially slidably mounted within the opening. A motor is operatively connected to this ring and, upon actuation, axially displaces the ring within the nozzle passageway. In addition, the ring includes a plurality of circumferentially spaced slots which register with the nozzle vanes so that the vane geometry remains the same despite axial displacement of the ring.
Document ID
20080005895
Acquisition Source
Legacy CDMS
Document Type
Other - Patent
Authors
Rogo, Casimir
Lenz, Herman N.
Date Acquired
August 24, 2013
Publication Date
November 12, 1985
Subject Category
Aircraft Propulsion And Power
Funding Number(s)
CONTRACT_GRANT: NAS3-22005
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
US-PATENT-4,552,308
Patent Application
US-PATENT-APPL-SN-199469

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