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Damping seals for turbomachineryA rotor seal is proposed that restricts leakage like a labyrinth seal, but extends the stabilizing speed range beyond twice the first critical speed. The dynamic parameters were derived from bulk flow equations without requiring a dominant axial flow. The flow is considered incompressible and turbulent. Damping seals are shown to be feasible for extending the speed range of high performance turbomachinery beyond the limit imposed by conventional seals.
Document ID
19820012309
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Vonpragenau, G. L.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
September 4, 2013
Publication Date
March 1, 1982
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NAS 1.60:1987
M-373
NASA-TP-1987
Accession Number
82N20183
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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