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Design, fabrication and test of the RL10 derivative II chamber/primary nozzleThe design, fabrication and test of the RL10-II chamber/primary nozzle was accomplished as part of the RL10 Product Improvement Program (PIP). The overall goal of the RL10 PIP was to gain the knowledge and experience necessary to develop new cryogenic upper stage engines to fulfill future NASA requirements. The goal would be reached by producing an RL10 engine designed to be reusable, operate at several thrust levels, and have increased performance. The goals for the chamber/primary nozzle task were: (1) to design a reusable assembly capable of operation at increased mixture ratio and low thrust; (2) to fabricate three assemblies using new or updated techniques where possible; and (3) to test one assembly to verify the design and construction. The design and fabrication phases produced an assembly having improved features such as single piece reinforcing band segments (i.e., Mae West segments) and relocated tube exit braze joints (i.e., hooked tube exit). In addition, a computer program was developed to design the chamber tubes to meet both performance and heat transfer requirements. The test phase showed the specific impulse of the test bed engine system to be as predicted. These results, along with the heat transfer data obtained, sufficiently proved the overall design of the RL10-II recontoured and shortened chamber/primary nozzle assembly.
Document ID
19890014148
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Marable, R. W.
(Pratt and Whitney Aircraft West Palm Beach, FL, United States)
Date Acquired
September 5, 2013
Publication Date
April 1, 1989
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
FR-19625
NASA-CR-179595
NAS 1.26:179595
Accession Number
89N23519
Funding Number(s)
CONTRACT_GRANT: NAS3-24738
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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