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Variable geometry device for turbine compressor outletA variable geometry device is provided for use with the compressor outlet of a turbine engine. The turbine engine includes a support housing, a compressor contained within the support housing and having a compressed air outlet and in which a pair of spaced walls define an annular and radially extending diffuser passageway. The inner end of the diffuser passageway is open to the compressed outlet while the outer end of the diffuser passageway is open to the combustion chamber for the turbine engine. A plurality of circumferentially spaced diffuser vanes are mounted to one of the diffuser walls and protrude across the diffuser passageway. An annular recessed channel is formed around the opposite diffuser wall and an annular ring is mounted within the channel. A motor is operatively connected to this ring and, upon actuation, displaces the ring transversely across the diffuser passageway to variably restrict the diffuser passageway. In addition, the ring includes a plurality of slots which register with the diffuser vanes so that the vane geometry remains the same despite axial displacement of the ring.
Document ID
20080005901
Acquisition Source
Legacy CDMS
Document Type
Other - Patent
Authors
Rogo, Casimir
Lenz, Herman N.
Date Acquired
August 24, 2013
Publication Date
October 1, 1985
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
Patent Application Number: US-PATENT-APPL-SN-199475
Patent Number: US-PATENT-4,544,325
Funding Number(s)
CONTRACT_GRANT: NAS3-23163
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
US-PATENT-4,544,325
Patent Application
US-PATENT-APPL-SN-199475
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