Accession Number:

AD0368062

Title:

INTEGRATED COMPONENTS PROGRAM. VOLUME II. ENGINE SUBSYSTEMS DEVELOPMENT.

Descriptive Note:

Final rept. 16 Mar 63-6 May 65.

Corporate Author:

LIQUID ROCKET OPERATIONS AEROJET-GENERAL CORP SACRAMENTO CALIF

Personal Author(s):

Report Date:

1965-11-01

Pagination or Media Count:

480.0

Abstract:

Several advanced concepts for improving storable propellant liquid rocket engines were investigated both analytically and experimentally Parametric analyses and preliminary designs were conducted on advanced rocket engines embodying the staged combustion cycle, high chamber pressure 2000-4000 psia, and altitude compensating nozzles with high expansion ratios 50-200. Nozzle aerodynamic investigations established the relative value of different types of nozzles for advanced propulsion systems that utilize varying numbers of individual modular engines. Thrust chambers, injectors, and turbomachinery were designed, fabricated, and successfully tested at chamber pressures up to 2750 psia and pump discharge pressures up to 5400 psia. The basic feasibility of lubricating turbopump bearings with N2O4 and with AeroZINE 50 50-50 mixture of N2H4 and UDMH was demonstrated. The use of hydrostatic seals with these propellants was also shown to be feasible. Three configurations of heavy-weight test-stand engines embodying high chamber pressure and staged combustion both simulated and actual at 100,000 lb thrust were built and tested. Author

Subject Categories:

  • Liquid Propellant Rocket Engines
  • Liquid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE