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Composite seal for turbomachineryA gas path seal suitable for use with a turbine engine or compressor is provided. A shroud wearable or abradable by the abrasion of the rotor blades of the turbine or compressor shrouds the rotor blades. A compliant backing surrounds the shroud. The backing is a compliant material covered with a thin ductile layer. A mounting fixture surrounds the backing.
Document ID
19800018159
Acquisition Source
Legacy CDMS
Document Type
Other - Patent
Authors
Bill, R. C. (NASA Lewis Research Center Cleveland, OH, United States)
Ludwig, L. P. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
June 10, 1980
Subject Category
Mechanical Engineering
Report/Patent Number
Patent Number: US-PATENT-4,207,024
Patent Application Number: US-PATENT-APPL-SN-801290
Patent Application Number: US-PATENT-APPL-SN-931090
Patent Number: US-PATENT-4,135,851
Patent Number: NASA-CASE-LEW-12131-2
Accession Number
80N26658
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
US-PATENT-4,207,024|US-PATENT-4,135,851|NASA-CASE-LEW-12131-2
Patent Application
US-PATENT-APPL-SN-801290|US-PATENT-APPL-SN-931090

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