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Active clearance control system for a turbomachineAn axial compressor is provided with a cooling air manifold surrounding a portion of the shroud, and means for bleeding air from the compressor to the manifold for selectively flowing it in a modulating manner axially along the outer side of the stator/shroud to cool and shrink it during steady state operating conditions so as to obtain minimum shroud/rotor clearance conditions. Provision is also made to selectively divert the flow of cooling air from the manifold during transient periods of operation so as to alter the thermal growth or shrink rate of the stator/shroud and result in adequate clearance with the compressor rotor.
Document ID
19820024490
Acquisition Source
Legacy CDMS
Document Type
Other - Patent
Authors
Johnston, R. P.
(NASA Lewis Research Center Cleveland, OH, United States)
Knapp, M. H.
(NASA Lewis Research Center Cleveland, OH, United States)
Coulson, C. E.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
May 11, 1982
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
Patent Application Number: US-PATENT-APPL-SN-060449
Patent Number: NASA-CASE-LEW-12938-1
Patent Number: US-PATENT-4,329,114
Accession Number
82N32366
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
NASA-CASE-LEW-12938-1|US-PATENT-4,329,114
Patent Application
US-PATENT-APPL-SN-060449
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