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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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A grooved capstrip, to straddle the metal edges of regenerative cooling channels, increases the strength and heat transfer characteristics of lightweight motor cases. This capstrip is so designed as to form a firm joint between the channels that form the rocket casing wall.
Energy transfer mechanisms in radiation, water, and regeneratively cooled, and MPD arc jet propulsion devices
Design criteria and fabrication techniques for regeneratively cooled rocket thrust chambers
Pneumatic flow comparator provides simple go, no-go evaluation of individual tubes. Flow characteristics of tubes used to form the walls of regeneratively cooled combustors must be identical within very close tolerances to ensure equally distributed coolant flow throughout the combustor wall.
Analytical and experimental study of regenerative cooling for FLOX methane engine with bulk boiling methane
Nickel-200 fatigue testing for thermal fatigue data on regeneratively cooled hypersonic research engine structures
Testing thermal barrier coatings for flame surface of regeneratively cooled chamber operating with FLOX/hydrocarbon propellants
Metal ribbon wrapped outer wall for regeneratively cooled combustion chamber
Regenerative cooling system for small rocket engine having restart capability and using noncryogenic hypergolic propellants
Fabrication and thermal performance of regeneratively cooled fluorine hydrogen thrust chamber
Method for shaping regeneratively cooled rocket motor casing having minimum thickness at each channel cross section
Regeneratively cooled rocket motor casing with tapered channels to insure minimum thicknesses at each channel cross section for necessary strength requirements
Regenerative cooling system for rocket combustion chamber using coolant tubes in convergent-divergent nozzle
Determination of thermal cycling capability of non-tubular regeneratively cooled thrust chambers for use in space shuttle propulsion systems
Regenerative cooling system design for rocket engines
A regeneratively cooled thrust chamber has been designed and fabricated, consisting of an inner TD nickel liner which was spin formed, welded, and machined and an outer shell of electroformed nickel. Coolant channels were produced in the outer surface of the inner liner by the electric discharge machining process before electroforming the shell. Accessory manifolds and piping were attached by welding. Manufacturing processes employed are described.
The activities leading to a tentative concept selection for a pressure-fed engine and propulsion support are outlined. Multiple engine concepts were evaluted through parallel engine major component and system analyses. Booster vehicle coordination, tradeoffs, and technology/development aspects are included. The concept selected for further evaluation has a regeneratively cooled combustion chamber and nozzle in conjuction with an impinging element injector. The propellants chosen are LOX/RP-1, and combustion stabilizing baffles are used to assure dynamic combustion stability.
An overview is presented of the results of the analyses conducted in support of the selected engine system for the pressure-fed booster stage. During initial phases of the project, a gimbaled, regeneratively cooled, fixed thrust engine having a coaxial pintle injector was selected as optimum for this configuration.