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Design study of shaft face seal with self-acting lift augmentation. 5: Performance in simulated gas turbine engine operationThe feasibility and the noncontact operation of the self-acting seal was demonstrated over a range of simulated gas turbine engine conditions from 200 to 500 ft/sec sliding speed. Sealed pressure differentials were 50 to 300 psi and sealed temperatures were 150 to 1200 F. Low leakage (about 1/10 that of conventional labyrinth seals) was exhibited in two endurance runs (200 and 338 hr) at 400 ft/sec, 200 psi and 1000 F (gas temperature). For these endurance runs, the self-acting pad wear was less than 3.8 micrometers (0.00015 in.); this low wear was attributed to the noncontact operation of the primary seal. Operating problems identified were fretting wear of the secondary seal and erosion of the primary seal by hard particles.
Document ID
19720004770
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Ludwig, L. P. (NASA Lewis Research Center Cleveland, OH, United States)
Johnson, R. L. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
December 1, 1971
Subject Category
Machine Elements And Processes
Report/Patent Number
E-6312
NASA-TN-D-6563
Accession Number
72N12419
Funding Number(s)
PROJECT: RTOP 132-15
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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