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Internal flow measurements of the SSME fuel preburner injector element using real time neutron radiographyDue to observations of unsteady flow in the Space Shuttle Main Engine fuel preburner injector element, several flow studies have been performed. Real time neutron radiography tests were recently completed. This technique provided real time images of MiL-c-7024 and Freon-22 flow through an aluminum liquid oxygen post model at three back pressures (0, 150, and 545 psig) and pressure drops up to 1000 psid. Separated flow appeared only while operating at back pressures of 0 and 150 psig. The behavior of separated flow was similar to that observed for water in a 3x acrylic model of the LOX post. On the average, separated flow appeared to reattach near the exit of the post when the ratio of pressure drop to supply pressure was about 0.75.
Document ID
19900055056
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lindsay, John T.
(Michigan, University Ann Arbor, United States)
Elam, Sandy
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Koblish, Ted
(Michigan Univ. Ann Arbor, MI, United States)
Lee, Phil
(Michigan Univ. Ann Arbor, MI, United States)
Mcauliffe, Dave
(Textron Aerospace Development Center Walled Lake, MI, United States)
Date Acquired
August 14, 2013
Publication Date
July 1, 1990
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 90-2293
Accession Number
90A42111
Distribution Limits
Public
Copyright
Other

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