INTEGRATED COMPONENTS PROGRAM. VOLUME II. ENGINE SUBSYSTEMS DEVELOPMENT.
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1965
- Accession Number
- AD0368062
Entities
Organizations
- Aerojet Rocketdyne Holdings