Injector element for rocket engine
US11635045B2 · kind B2 · utility
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14References
14Claims
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Assignee
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Key dates
| Filing date | Jun 29, 2017 |
| Grant date | Apr 25, 2023 |
| Priority date | — |
| Expiry date | Nov 17, 2039 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K9/52
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An injector element for a liquid propellant rocket engine includes an oxidizer conduit, a central cavity that is fluidly coupled with the oxidizer conduit downstream of the oxidizer conduit, a first annulus that at least partially surrounds the oxidizer conduit and is fluidly coupled with an ignition fluid supply downstream of the ignition fluid supply, and a second annulus that at least partially surrounds the oxidizer conduit and is fluidly coupled with a fuel supply downstream of the fuel supply. The second annulus is fluidly coupled between the first annulus and the central cavity.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.