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Mechanical characteristics of stability-bleed valves for a supersonic inletMechanical characteristics of a set of direct-operated relief valves used in a throat-bypass stability-bleed system designed for the YF-12 aircraft inlet are described. A comparison of data taken before and after the windtunnel tests (at room temperature) showed that both the effective spring rate and the piston friction had decreased during the wind tunnel tests. In neither the effective spring rate nor the piston friction was the magnitude of change great enough to cause significant impairment of overall system effectiveness. No major valve mechanical problems were encountered in any of the tests. During high temperature bench tests, piston frictional drag increased. The friction returned to its initial room temperature value when the stability-bleed valve was disassembled and reassembled. The problem might be solved by using a different material for the piston sleeve bearing and the piston rings.
Document ID
19780005120
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Neiner, G. H. (NASA Lewis Research Center Cleveland, OH, United States)
Dustin, M. O. (NASA Lewis Research Center Cleveland, OH, United States)
Cole, G. L. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
December 1, 1977
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-TM-X-3483
E-8852
Accession Number
78N13063
Funding Number(s)
PROJECT: RTOP 743-03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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