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Liquid oxygen turbopump technology
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Nielson, C. E. |
| Copyright Year | 1981 |
| Description | A small, high-pressure, LOX turbopump was designed, fabricated and tested. The pump is a single-stage centrifugal type with power to the pump supplied by a single-stage partial-admission axial-impulse turbine. Design conditions included an operating speed of 7330 rad/s (70,000 rpm), pump discharge pressure of 2977 N/sqcm (4318 psia), and a pump flowrate of 16.4 Kg/s (36.21 lb/s). The turbopump contains a self-compensating axial thrust balance piston to eliminate axial thrust loads on the bearings during steady-state operation. Testing of the turbopump was achieved usng a gaseous hydrogen high-pressure flow to drive the turbine, which generally is propelled by LOX/LH2 combustion products, at 1041K (1874 R) inlet temperature and at a design pressure ratio of 1.424. Test data obtained with the turbopump are presented which include head-flow-efficiency performance, suction performance, balance piston performance and LOX seal performance. Mechanical performance of the turbopump is also discussed. |
| File Size | 12780623 |
| Page Count | 258 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19820003595 |
| Archival Resource Key | ark:/13960/t20c9s763 |
| Language | English |
| Publisher Date | 1981-11-01 |
| Access Restriction | Open |
| Subject Keyword | Mechanical Engineering Pistons Suction Turbine Pumps Liquid Oxygen High Speed Head Flow Centrifugal Pumps Reliability Engineering Operational Problems Reusable Spacecraft Pump Seals Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
