Accession Number:

AD0387034

Title:

ADVANCED CRYOGENIC ROCKET ENGINE PROGRAM AEROSPIKE NOZZLE CONCEPT -- MATERIALS AND PROCESSES

Descriptive Note:

Final rept.

Corporate Author:

ROCKETDYNE CANOGA PARK CA

Personal Author(s):

• Lary, F. B.

Report Date:

1967-11-01

Pagination or Media Count:

188.0

Abstract:

Reported herein are the results of Materials and Processes effort related to development and fabrication of experimental Aerospike thrust chamber hardware. This report includes information relative to the selection of materials and information concerning the fabrication of the 250K combustor bodies and injectors, the development of the small tapered thrust chamber tubes, and the development of tooling and successful brazing of the small tubes to backup structure, and the injectors. Fabrication details of the 2.5 and 20K segment hardware is also included. Highlighted are 1 Data for prediction of tube life, based on elevated temperature cycle strain tests, analytical calculations, and life cycle tests, 2 the development of small-diameter, tapered, variable wall thickness, formed tubes with an internal surface roughness requirement, 3 the brazing of the small tapered tubes to the backup structure utilizing the pressure bag concept, and 4 the thermographic method of braze bond inspection. Author

Descriptors:

• *LIQUID PROPELLANT ROCKET ENGINES
• *ROCKET NOZZLES
• MANUFACTURING
• COPPER ALLOYS
• STAINLESS STEEL
• PIPES
• COPPER
• BONDED JOINTS
• PRESSURE
• COMBUSTION CHAMBERS
• ENVIRONMENTAL TESTS
• FATIGUE(MECHANICS)
• MANIFOLDS(ENGINES)
• NICKEL ALLOYS
• FUEL INJECTORS
• RINGS
• THERMAL STRESSES
• BRAZING
• BERYLLIUM ALLOYS
• PLUG NOZZLES

Subject Categories:

• Metallurgy and Metallography
• Fabrication Metallurgy
• Liquid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE