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Thin-film Sensors for Space Propulsion TechnologySSME components such as the turbine blades of the high pressure fuel turbopump are subjected to rapid and extreme thermal transients that contribute to blade cracking and subsequent failure. The objective was to develop thin film sensors for SSME components. The technology established for aircraft gas turbine engines was adopted to the materials and environment encountered in the SSME. Specific goals are to expand the existing thin film sensor technology, to continue developing improved sensor processing techniques, and to test the durability of aircraft gas turbine engine technology in the SSME environment. A thin film sensor laboratory is being installed in a refurbished clean room, and new sputtering and photoresist exposure equipment is being acquired. Existing thin film thermocouple technology in an SSME environment are being tested. Various coatings and their insulating films are being investigated for use in sensor development.
Document ID
19850019656
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kim, W. S.
(NASA Lewis Research Center Cleveland, OH, United States)
Englund, D. R.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 12, 2013
Publication Date
May 1, 1985
Publication Information
Publication: Struct. Integrity and Durability of Reusable Space Propulsion Systems
Subject Category
Spacecraft Instrumentation
Accession Number
85N27968
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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