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Performance Comparison of Axisymmetric and Three-dimensional Hydrogen Film Coolant Injection in a 110N Hydrogen/oxygen RocketAn experimental performance comparison of two geometrically different fuel film coolant injection sleeves was conducted on a 110 N gaseous hydrogen/oxygen rocket. One sleeve had slots milled axially down the walls and the other had a smooth surface to give axisymmetric flow. The comparison was made to investigate a conclusion in an earlier study that attributed a performance underprediction to a symplifying modeling assumption of axisymmetric fuel film flow. The smooth sleeve had higher overall performance at one film coolant percentage and approximately the same or slightly better at another. The study showed that the lack of modeling of three-dimensional effects was not the cause of the performance underprediction as speculated in earlier analytical studies.
Document ID
19930007525
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Arrington, Lynn A. (Sverdrup Technology, Inc. Brook Park, OH., United States)
Reed, Brian D. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
December 1, 1992
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NASA-TM-105967
E-7490
AIAA PAPER 92-3390
NAS 1.15:105967
Meeting Information
Meeting: Joint Propulsion Conference and Exhibit
Location: Nashville, TN
Country: United States
Start Date: July 6, 1992
End Date: July 8, 1992
Sponsors: SAE, ASEE, AIAA, ASME
Accession Number
93N16714
Funding Number(s)
PROJECT: RTOP 506-42-31
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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