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Formed platelet combustor liner construction feasibility, phase AEnvironments generated in high pressure liquid rocket engines impose severe requirements on regeneratively cooled combustor liners. Liners fabricated for use in high chamber pressures using conventional processes suffer from limitations that can impair operational cycle life and can adversely affect wall compatibility. Chamber liners fabricated using formed platelet technology provide an alternative to conventional regeneratively cooled liners (an alternative that has many attractive benefits). A formed platelet liner is made from a stacked assembly of platelets with channel features. The assembly is diffusion bonded into a flat panel and then three-dimensionally formed into a section of a chamber. Platelet technology permits the liner to have very precisely controlled and thin hot gas walls and therefore increased heat transfer efficiency. Further cooling efficiencies can be obtained through enhanced design flexibility. These advantages translate into increased cycle life and enhanced wall compatibility. The increased heat transfer efficiency can alternately be used to increase engine performance or turbopump life as a result of pressure drop reductions within the regeneratively cooled liner. Other benefits can be obtained by varying the materials of construction within the platelet liner to enhance material compatibility with operating environment or with adjoining components. Manufacturing cost savings are an additional benefit of a formed platelet liner. This is because of reduced touch labor and reduced schedule when compared to conventional methods of manufacture. The formed platelet technology is not only compatible with current state-of-the art combustion chamber structural support and manifolding schemes, it is also an enabling technology that allows the use of other high performance and potentially low cost methods of construction for the entire combustion chamber assembly. The contract under which this report is submitted contains three phases: (1) phase A - feasibility study and technology development; (2) phase B - sub-scale fabrication feasibility; and (3) phase C - large scale fabrication validation. This report covers the Phase A activities, which began in December of 1988.
Document ID
19930007508
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Hayes, W. A. (Aerojet-General Corp. Sacramento, CA, United States)
Janke, D. E. (Aerojet-General Corp. Sacramento, CA, United States)
Date Acquired
September 6, 2013
Publication Date
September 30, 1992
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NAS 1.26:184506
RPT/G0114.119
NASA-CR-184506
Accession Number
93N16697
Funding Number(s)
CONTRACT_GRANT: NAS8-37456
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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