Engineering topics

Carpenter, H. W.

Publications and source records attributed to Carpenter, H. W..

7 records

NASA NTRS1985

Ceramics for advanced O2/H2 application

Ceramics are prime candidate materials for advanced rocket engines because they possess high-temperature capability, a tolerance for aggressive environments, and low density. A program was conducted to assess the applicability of structural ceramics to advanced versions of the Space Shuttle main engine (SSME). Operating conditions of ceramic turbine components were defined and each component in the hot-gas path was assessed in regard to materials selection, manufacturing process and feasibility, and relative structural reliability. The conclusion is that ceramic components would be viable in advanced SSME turbopumps.

Carpenter, H. W.↗

NASA NTRS1971

Granular two-phase insulation systems

Easily prepared system, consisting of matrix of hollow zirconia microspheres containing dispersed tungsten powder, produces minimum-cost, prototype test specimen. Combination represents basic concept of highly reflective dispersed phase in low density insulative matrix and is stable at 2200 K. Other combinations of materials are suggested.

Carpenter, H. W.↗

NASA NTRS1971

Protective coating system for a regeneratively cooled thrust chamber Final report, 1 Feb. 1969 - 31 Dec. 1970

Protective coating of phosphate-bonded zirconia for regeneratively cooled thrust chambers

Carpenter, H. W.↗

NASA NTRS1970

Simple bonding technique for high-temperature ceramic coatings

Coatings, consisting of zirconia powder bonded with orthophosphoric acid and a small amount of hydrofluoric acid, are hard, strong, and refractory, resist thermal shock, and provide good thermal protection. After the aqueous coating is applied to a metallic surface, only a 600 deg F cure is required before service.

Accountius, O. E.↗

NASA NTRS1970

Heat-barrier coatings for combustion chambers

Arc-plasma-sprayed layered coating of graded Inconel and zirconia protects film-coolant ring below injector plate of rocket engine combustion chamber. Interfacial temperature is designed for minimum buildup of stress and to avoid melting of the metal phase in the graded layers.

Carpenter, H. W.↗

NASA NTRS1969

Protective coating system for a regeneratively cooled thrust chamber Final report, 30 Jun. 1967 - 31 Jan. 1969

Ceramic thermal protective coating system for regeneratively cooled hydrogen oxygen thrust chamber

Carpenter, H. W.↗

NASA NTRS1966

Intergranular metal phase increases thermal shock resistance of ceramic coating

Dispersed copper phase increases the thermal shock resistance of a plasma-arc-sprayed coating of zirconia used as a heat barrier on a metal substrate. A small amount of copper is deposited on the granules of the zirconia powder before arc-spraying the resultant powder composite onto the substrate.

Carpenter, H. W.↗