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A laboratory model of a hydrogen/oxygen engine for combustion and nozzle studiesA small laboratory diagnostic thruster was developed in order to evaluate approaches for the use of temperature and pressure sensors for the investigation of low thrust rocket flowfields. Tests were performed at chamber pressures of about 255 kPa, 370 kPa, and 500 kPa with oxidizer/fuel mixture ratios between 4.0 and 8.0. Two gaseous hydrogen/gaseous oxygen injector designs were tested with 60 and 75 fuel film cooling. The results of hot-wire tests showed the thruster and instrumentation designs to be effective. Azimuthal temperature distributions were found to be a function of operating conditions and hardware configuration. Results indicated that small differences in injector design can result in dramatically different thruster performance and wall temperature behavior. However, the importance of these injector effects may be decreased by operating at a high fuel film cooling rate.
Document ID
19930065714
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Morren, Sybil H.
(NASA Lewis Research Center Cleveland, OH, United States)
Myers, Roger M.
(Sverdrup Technology, Inc. Brook Park, OH, United States)
Benko, Stephen E.
(NASA Lewis Research Center Cleveland, OH, United States)
Arrington, Lynn A.
(Sverdrup Technology, Inc. Brook Park, OH, United States)
Reed, Brian D.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 16, 2013
Publication Date
June 1, 1993
Subject Category
Ground Support Systems And Facilities (Space)
Report/Patent Number
AIAA PAPER 93-1825
Meeting Information
Meeting: AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit
Location: Monterey, CA
Country: United States
Start Date: June 28, 1993
End Date: June 30, 1993
Sponsors: SAE, ASEE, AIAA, ASME
Accession Number
93A49711
Distribution Limits
Public
Copyright
Other

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