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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 yieldingly deformable porous material covered with a thin ductile layer. A mounting fixture surrounds the backing.
Document ID
19820011666
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
October 20, 1981
Subject Category
Mechanical Engineering
Report/Patent Number
Patent Number: NASA-CASE-LEW-12131-3
Patent Application Number: US-PATENT-APPL-SN-096255
Patent Application Number: US-PATENT-APPL-SN-801290
Patent Number: US-PATENT-4,207,024
Patent Application Number: US-PATENT-APPL-SN-931090
Patent Number: US-PATENT-4,295,786
Patent Number: US-PATENT-4,135,851
Accession Number
82N19540
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
NASA-CASE-LEW-12131-3|US-PATENT-4,207,024|US-PATENT-4,295,786|US-PATENT-4,135,851
Patent Application
US-PATENT-APPL-SN-096255|US-PATENT-APPL-SN-801290|US-PATENT-APPL-SN-931090

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