Accession Number:

AD0816779

Title:

ADVANCED WIRE-WOUND TUNGSTEN NOZZLES.

Descriptive Note:

Final rept. 1 Feb 66-15 Mar 67,

Corporate Author:

UNITED TECHNOLOGY CENTER SUNNYVALE CA

Personal Author(s):

• Greening, Thomas A.

Report Date:

1967-04-01

Pagination or Media Count:

96.0

Abstract:

This program was directed toward the demonstration of the capabilities of UTCs wire-wound tungsten, plasma-spray-bonded tungsten nozzle inserts. The wire-wound composite process involves the winding of high-strength wire over a mandrel and simultaneously binding the wires together by the use of a plasma-arc-sprayed matrix. The concept can be pictured as one in which the wire acts as a reinforcement for the plasma-sprayed matrix. The wire or filament is wound alternating layers are hoop and helically disposed to ensure adequate hoop and longitudinal strength and to interrupt stress paths for crack propagation. Based on extensive thermal and stress analyses, two wire-wound tungsten nozzle inserts were designed, fabricated, and assembled into complete nozzle units. The first unit incorporated a thick-block insert design, and the second employed a thin-shell design. These nozzles were test fired with a highly erosive and corrosive high-temperature aluminized solid propellant. Based on the results of these firings, a third nozzle was designed, built, and fired. This report describes the design and fabrication of the nozzles and includes firing data and conclusions regarding the feasibility of the wire-wound tungsten approach. Author

Descriptors:

• *TUNGSTEN)
• (*ROCKET NOZZLES
• (*FILAMENT WOUND CONSTRUCTION
• ROCKET NOZZLES)
• EXHAUST FLAMES
• MATERIALS
• ROCKET PROPELLANTS
• MANUFACTURING
• GRAPHITE
• THERMAL INSULATION
• SILICATES
• STEEL
• REFRACTORY METALS
• COMBUSTION CHAMBER LINERS
• CAPTIVE TESTS
• THERMAL STRESSES
• CORROSIVE LIQUIDS
• TEMPERATURE
• ALUMINUM
• CRACK PROPAGATION
• HEAT SINKS
• SUPPORTS

Subject Categories:

• Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE