Accession Number:

AD0909397

Title:

Injector/Chamber Scaling Evaluation.

Descriptive Note:

Final rept. Jul 68-Feb 70,

Corporate Author:

AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA

Personal Author(s):

• Silver, Roy A.

Report Date:

1972-08-01

Pagination or Media Count:

299.0

Abstract:

This report describes the results of the testing performed at the Air Force Rocket Propulsion Laboratory. The purpose of this program was to demonstrate the performance, stability, injectorchamber compatibility and long-duration operation of low-cost scalable pressure-fed engines which use storable propellants. Tests were conducted at the 250,000-pound-thrust level with thrust chamber assemblies using two different design approaches a pintle injector designed by TRW Systems and a modular injector designed by Rocketdyne. Short-duration tests were performed to measure performance, stability and effects of design variation. Long-duration tests were conducted to demonstrate performance, injectorchamber compatibility, and to measure the performance potential of low-cost ablative chambers. The program goals of achieving 90 percent of theoretical specific impulse, 140-second-duration firing and low-cost thrust chamber assemblies were all achieved.

Descriptors:

• *STORABLE ROCKET PROPELLANTS
• *FUEL INJECTORS
• *COMBUSTION CHAMBERS
• LIQUID PROPELLANT ROCKET ENGINES
• METHYL HYDRAZINES
• HEAT SINKS
• HEAT TRANSFER
• THRUST
• SPECIFIC IMPULSE
• PRESSURE
• COMBUSTION
• STABILITY
• COMBUSTION CHAMBER LINERS
• MANIFOLDS(ENGINES)
• ABLATION
• MANUFACTURING
• FUEL INJECTION
• PERFORMANCE(ENGINEERING)

Subject Categories:

• Combustion and Ignition
• Liquid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE