Boost injection turbine exhaust cycle (BITEC)
US12180914B1 · kind B1 · utility
0Cited by
16References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Aug 28, 2023 |
| Grant date | Dec 31, 2024 |
| Priority date | — |
| Expiry date | Aug 28, 2043 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K9/52
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rocket propulsion system that may include a supersonic rocket nozzle with a supersonic divergent section, and a heat transfer system configured to transfer heat from the supersonic rocket nozzle to a propellant where a portion of the propellant may be selectively injected, combusted, and expanded in the supersonic nozzle generating an additional thrust. In examples, the heated propellant may be used to power a pump system to feed the rocket engine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.