NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Balancing low cost with reliable operation in the rotordynamic design of the ALS Liquid Hydrogen Fuel TurbopumpThe Air Force/NASA Advanced Launch System (ALS) Liquid Hydrogen Fuel Turbopump (FTP) has primary design goals of low cost and high reliability, with performance and weight having less importance. This approach is atypical compared with other rocket engine turbopump design efforts, such as on the Space Shuttle Main Engine (SSME), which emphasized high performance and low weight. Similar to the SSME turbopumps, the ALS FTP operates supercritically, which implies that stability and bearing loads strongly influence the design. In addition, the use of low cost/high reliability features in the ALS FTP such as hydrostatic bearings, relaxed seal clearances, and unshrouded turbine blades also have a negative influence on rotordynamics. This paper discusses the analysis conducted to achieve a balance between low cost and acceptable rotordynamic behavior, to ensure that the ALS FTP will operate reliably without subsynchronous instabilities or excessive bearing loads.
Document ID
19900055766
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Greenhill, L. M.
(GenCorp Aerojet, Propulsion Div., Sacramento, CA, United States)
Date Acquired
August 14, 2013
Publication Date
July 1, 1990
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 90-2741
Accession Number
90A42821
Funding Number(s)
CONTRACT_GRANT: NAS8-37593
Distribution Limits
Public
Copyright
Other

Available Downloads

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