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ALS liquid hydrogen turbopump: Advanced Development ProgramThe point of departure (POD) turbopump concept was reviewed and finalized. The basis for the POD was the configuration presented in the Aerojet proposal. After reviewing this proposal concept, several modifications were made. These modifications include the following: (1) the dual pump discharge arrangement was changed to a single discharge; (2) commonality of the turbine inlet manifold with the advanced launch system (ALS) liquid oxygen (LOX) TPA was dropped for this program; (3) the turbine housing flange arrangement was improved by relocating it away from the first stage nozzles; (4) a ten percent margin (five percent diameter increase) was built into the impeller design to ensure meeting the required discharge pressure without the need for increasing speed; (5) a ten percent turbine power margin was imposed which is to be obtained by increasing turbine inlet pressure if required; and (6) the backup concept, as an alternative to the use of cast impellers, now incorporates forged/machined shrouded impellers, rather than the unshrouded type originally planned.
Document ID
19910016882
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Shimp, Nancy R. (Aerojet TechSystems Co. Sacramento, CA, United States)
Claffy, George J. (Aerojet TechSystems Co. Sacramento, CA, United States)
Date Acquired
September 6, 2013
Publication Date
July 21, 1989
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
KGC4-M-2
NAS 1.26:183730
NASA-CR-183730
Accession Number
91N26196
Funding Number(s)
CONTRACT_GRANT: NAS8-37593
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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