ADVANCED CRYOGENIC ROCKET ENGINE PROGRAM STAGED-COMBUSTION CONCEPT.
Abstract
Phase I is an evaluation of the critical technology associated with the staged-combustion bell-nozzle engine system. Experimental evaluation is being conducted in the areas of the main burner, turbopump bearings, engine controls preburner, and the staged combustion rig. Engine system (module) preliminary design and application studies are being conducted. In the Module Design Study, the engine configuration definition studies were completed, and a Phase II demonstrator engine configuration was selected. The parametric engine data were revised to reflect the use of the lightweight, two-position nozzle. Under the turbopump components Sub-Task, the endurance testing of the hydrogen turbopump bearing is in process to demonstrate long life at design speed and load conditions. Under the Module Control SYSTEM Sub-Task, three flow divider valve assemblies and two mixture ratio valves are available for use. The Preburner Demonstration Sub-Task was completed, and dynamic combustion stability was demonstrated. Under the Staged Combustion Rig Sub-Task, 17 test firings were attempted. During these test attempts stand safety circuits and starting procedures were adjusted and three data producing tests were accomplished. No parts distress has been detected and testing to demonstrate 250K staged combustion performance is continuing.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1967
- Accession Number
- AD0384236
Entities
People
- Robert Atherton
Organizations
- Pratt & Whitney