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Brush Seal Performance and Durability Issues Based on T-700 Engine Test ResultsThe integrity and performance of brush seals have been established. Severe bench and engine tests have shown high initial wear or run-in rates, material smearing at the interface, and bristle and rub-runner wear, but the brush seals did not fail. Short-duration (46 hr) experimental T-700 engine testing of the compressor discharge seal established over 1-percent engine performance gain (brush versus labyrinth). Long-term gains were established only as leakage comparisons, with the brush at least 20 percent better at controlling leakage. Long-term materials issues, such as wear and ultimately seal life, remain to be resolved. Future needs are cited for materials and analysis tools that account for heat generation, thermomechanical behavior, and tribological pairing to enable original equipment manufacturers to design high-temperature, high-surface-speed seals with confidence.
Document ID
19950005070
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Hendricks, R. C.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
March 1, 1994
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NASA-TM-106502
E-8520
NAS 1.15:106502
Accession Number
95N11483
Funding Number(s)
PROJECT: RTOP 232-01-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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