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High Head Unshrouded Impeller Pump Stage TechnologyObjective to develop an unshrouded impeller design, which a meets the performance requirements of a 3-stage fuel pump with a 2-stage pump design, has been accomplished. Performance of the baseline unshrouded impeller has been experimentally verified. Unshrouded impeller trade study and final 6+6 unshrouded impeller configuration has been presented. Structurally viable, 6+6-impeller design concept has been produced. Based on results presented in this study, at a nominal 10% tip-clearance, the 6+6 impeller design would increase payload to orbit by almost 625 lbs. per engine. The RLV vehicle requires 7 engines, therefore, application of high head unshrouded technology would increase payload capability by as much as 4,375 lbs. per vehicle.
Document ID
20000113674
Acquisition Source
Marshall Space Flight Center
Document Type
Preprint (Draft being sent to journal)
Authors
Williams, Robert W.
(NASA Marshall Space Flight Center Huntsville, AL United States)
Skelley, Stephen E.
(NASA Marshall Space Flight Center Huntsville, AL United States)
Stewart, Eric T.
(NASA Marshall Space Flight Center Huntsville, AL United States)
Droege, Alan R.
(NASA Marshall Space Flight Center Huntsville, AL United States)
Prueger, George H.
(Boeing Co. Canoga Park, CA United States)
Chen, Wei-Chung
(Boeing Co. Canoga Park, CA United States)
Williams, Morgan
(Boeing Co. Canoga Park, CA United States)
Turner, James E.
Date Acquired
September 7, 2013
Publication Date
January 1, 2000
Subject Category
Mechanical Engineering
Report/Patent Number
AIAA Paper 2000-3243
Report Number: AIAA Paper 2000-3243
Meeting Information
Meeting: Joint Propulsion
Location: Huntsville, AL
Country: United States
Start Date: July 16, 2000
End Date: July 19, 2000
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NRA8-21
PROJECT: RTOP 713-23-57
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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