ADVANCED ROCKET ENGINE--STORABLE
Abstract
The objective of this program was to demonstrate the engineering practicality and performance characteristics of a high chamber pressure, staged combustion engine. The program was to be conducted in two phases. Phase I was to demonstrate critical engine features by component testing. Specific accomplishments of the PHASE I program are as follows: (1) Master layouts for two engine designs were established. (2) A master layout was established for a propulsion system utilizing 20 engine modules in a cluster, with all modules exhausting into a single large forced-deflection nozzle. (3) Detail designs for all the engine components tested in this program were prepared. (4) The primary injector and combustion chamber for production of the turbine drive gas were demonstrated. (5) Performance and durability of the cooled thrust chamber and secondary Injector combination were demonstrated. (6) The feasibility of lubricating turbopump bearings with the storable propellants used in the engine was demonstrated. (7) Pump wear ring designs that permit high pump efficiency operation without need for high tolerances and with no risk of explosion hazard from pump rub were demonstrated. (8) The weight and practicality of two types of multipurpose housings for the turbopump and primary combustion chamber assembly were demonstrated. (9) Propellant flow control components and shutoff valves for the engine were demonstrated. (10) A layout design of the engine evolved from the testing effort was prepared.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1968
- Accession Number
- AD0390357
Entities
People
- J. A. Gibb
- R. A. Hankins
- R. Beichel
Organizations
- Aerojet Rocketdyne Holdings