Rocket engine turbopump
US8864441B1 · kind B1 · utility
Assignee
Inventor
Key dates
| Filing date | Aug 9, 2011 |
| Grant date | Oct 21, 2014 |
| Priority date | — |
| Expiry date | Aug 16, 2033 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF04D13/04
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rocket engine turbopump with a main rotor shaft supporting a liquid oxygen impeller on a forward end and a turbine on an aft end, and with a multiple stage liquid hydrogen impeller in-between. Two hydrostatic bearings support the main rotor shaft such that the liquid oxygen impeller and the turbine are both overhung. A balancing piston is used to balance the main rotor shaft in an axial direction. This structure allows for the main rotor shaft to be of such a large diameter that the turbopump is capable of operating at around 70,000 rpm that can produce a liquid hydrogen outlet pressure of around 4,000 psia in a turbopump having a diameter of less than 10 inches.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.