NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Small centrifugal pumps for low thrust rocketsThis paper presents the results of a combined analytical and experimental investigation of low specific speed pumps for potential use as components of propellant feed systems for low thrust rocket engines. Shrouded impellers and open face impellers were tested in volute type and vaned diffuser type pumps. Full- and partial-emission diffusers and full- and partial-admission impellers were tested. Axial and radial loads, head and efficiency versus flow, and cavitation tests were conducted. Predicted performance of two pumps are compared when pumping water and liquid hydrogen. Detailed pressure loss and parasitic power values are presented for two pump configurations. Partial-emission diffusers were found to permit use of larger impeller and diffuser passages with a minimal performance penalty. Normal manufacturing tolerances were found to result in substantial power requirement variation with only a small pressure rise change. Impeller wear ring leakage was found to reduce pump pressure rise to an increasing degree as the pump flowrate was decreased.
Document ID
19850061827
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Gulbrandsen, N. C.
(Rockwell International Corp. Canoga Park, CA, United States)
Furst, R. B.
(Rockwell International Corp. Canoga Park, CA, United States)
Burgess, R. M.
(Rockwell International Corp. Rocketdyne Div., Canoga Park, CA, United States)
Scheer, D. D.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 12, 2013
Publication Date
July 1, 1985
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 85-1302
Accession Number
85A43978
Funding Number(s)
CONTRACT_GRANT: NAS3-23164
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available