Accession Number:

AD0902890

Title:

Expansion-Deflection Nozzle

Descriptive Note:

Final rept. 1 May 1971-24 Jan 1972

Corporate Author:

AEROJET LIQUID ROCKET CO SACRAMENTO CA

Personal Author(s):

Report Date:

1972-07-12

Pagination or Media Count:

224.0

Abstract:

A nine-month exploratory development program was conducted to analyze, design, fabricate, and test hardware to gather data on the operation of an expansion-deflection nozzle. The technical effort consisted of the analysis and design of a nominal 25,000-lb thrust, 1500 psia chamber pressure, expansion- deflection thrust chamber using LO2LH2 propellants at a mixture ratio of 61. Several chamber segments and an annular uncooled thrust chamber were designed using an anticipated flight configuration thrust chamber design as a baseline. An annular and a segment injector were analyzed and designed for use on the thrust chambers. The segment injector and both water-cooled and heat sink chambers were fabricated and tested at sea level conditions. The injector demonstrated acceptable operation at chamber pressures of 300 and 750 psi.

Subject Categories:

  • Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE