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The j-2x oxidizer turbopump - design, development, and test
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Brozowski, Laura A. Marsh, Matthew W. Shinguchi, Brian H. Beatty, D. Preston |
| Copyright Year | 2011 |
| Description | Pratt and Whitney Rocketdyne (PWR), a NASA subcontractor, is executing the Design, Development, Test, and Evaluation (DDT&E) of a liquid oxygen, liquid hydrogen two hundred ninety-four thousand pound thrust rocket engine initially intended for the Upper Stage (US) and Earth Departure Stage (EDS) of the Constellation Program Ares-I Crew Launch Vehicle (CLV). A key element of the design approach was to base the new J-2X engine on the heritage J-2S engine which was a design upgrade of the flight proven J-2 engine used to put American astronauts on the moon. This paper will discuss the design trades and analyses performed to achieve the required uprated Oxidizer Turbopump performance; structural margins and rotordynamic margins; incorporate updated materials and fabrication capability; and reflect lessons learned from legacy and existing Liquid Rocket Propulsion Engine turbomachinery. These engineering design, analysis, fabrication and assembly activities support the Oxidizer Turbopump readiness for J-2X engine test in 2011. |
| File Size | 27225 |
| Page Count | 3 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20120002824 |
| Archival Resource Key | ark:/13960/t57d7vv6k |
| Language | English |
| Publisher Date | 2011-12-05 |
| Access Restriction | Open |
| Subject Keyword | Launch Vehicles And Launch Operations Fabrication Lessons Learned Rotor Dynamics Turbine Pumps Ares 1 Launch Vehicle Turbomachinery Oxygen-hydrocarbon Rocket Engines Astronauts Engine Tests Liquid Propellant Rocket Engines Oxidizers J-2 Engine Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
