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Compliant Foil Seal InvestigationsRoom temperature testing of an 8.5 inch diameter foil seal was conducted in the High Speed, High Temperature Turbine Seal Test Rig at the NASA Glenn Research Center. The seal was operated at speeds up to 30,000 rpm and pressure differentials up to 75 psid. Seal leakage and power loss data will be presented and compared to brush seal performance. The failure of the seal and rotor coating at 30,000 rpm and 15 psid will be presented and future development needs discussed.
Document ID
20040182398
Document Type
Conference Paper
Authors
Proctor, Margaret
(NASA Glenn Research Center Cleveland, OH, United States)
Delgado, Irebert
(Army Research Lab. United States)
Date Acquired
September 7, 2013
Publication Date
September 1, 2004
Publication Information
Publication: 2003 NASA Seal/Secondary Air System Workshop, Volume 1
Subject Category
Aircraft Propulsion And Power
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle20040182396Analytic Primary2003 NASA Seal/Secondary Air System Workshop
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