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Control means for a gas turbine engineA means is provided for developing a signal representative of the actual compressor casing temperature, a second signal representative of compressor inlet gas temperature, and a third signal representative of compressor speed. Another means is provided for receiving the gas temperature and compressor speed signals and developing a schedule output signal which is a representative of a reference casing temperature at which a predetermined compressor blade stabilized clearance is provided. A means is also provided for comparing the actual compressor casing temperature signal and the reference casing temperature signal and developing a clearance control system representative of the difference. The clearance control signal is coupled to a control valve which controls a flow of air to the compressor casing to control the clearance between the compressor blades and the compressor casing. The clearance control signal can be modified to accommodate transient characteristics. Other embodiments are disclosed.
Document ID
19830023332
Acquisition Source
Legacy CDMS
Document Type
Other - Patent
Authors
Beitler, R. S.
(General Electric Co. Cincinnati, United States)
Sellers, F. J.
(General Electric Co. Cincinnati, United States)
Bennett, G. W.
(General Electric Co. Cincinnati, United States)
Date Acquired
September 4, 2013
Publication Date
July 6, 1982
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
Patent Number: US-PATENT-4,338,061
Patent Number: NASA-CASE-LEW-14586-1
Patent Application Number: US-PATENT-APPL-SN-163122
Accession Number
83N31603
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
US-PATENT-4,338,061|NASA-CASE-LEW-14586-1
Patent Application
US-PATENT-APPL-SN-163122
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