Staged combustion liquid rocket engine cycle with the turbopump unit and preburner integrated into the structure of the combustion chamber
US11149691B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 4, 2020 |
| Grant date | Oct 19, 2021 |
| Priority date | — |
| Expiry date | Sep 4, 2040 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/601
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Devices and methods of rocket propulsion are disclosed. In one aspect, a staged combustion liquid rocket engine with preburner and turbopump unit (TPU) integrated into the structure of the combustion chamber is described. An initial propellant mixture is combusted in a preburner combustion chamber formed as an annulus around a main combustion chamber, the combustion products from the preburner driving the turbine of the TPU and subsequently injected into the main combustion chamber for secondary combustion along with additional propellants, generating thrust through a supersonic nozzle. The preburner inner cylindrical wall is shared with the outer cylindrical wall of the engine's main combustion chamber and the turbine is axially aligned with the main combustion chamber. Liquid propellants supplied to the engine are utilized for regenerative cooling of the combustion chamber and preburner, where the liquid propellants are gasified in cooling manifolds before injection into the preburner and main combustion chamber.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.