Title:
ロケットエンジンのインジェクタ要素
Document Type and Number:
Japanese Patent JP6906601
Kind Code:
B2
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.
Inventors:
Parker, Douglas S.
Cap, Daniel Pea.
Dodd, Frederick E.
Cap, Daniel Pea.
Dodd, Frederick E.
Application Number:
JP2019502010A
Publication Date:
July 21, 2021
Filing Date:
June 29, 2017
Export Citation:
Assignee:
AeroJet Rocket Dyne Incorporated
International Classes:
F02K9/52
Domestic Patent References:
| JP2008274937A |
Foreign References:
| US3426534 | ||||
| EP2757243A1 | ||||
| US20110219743 | ||||
| US20100257839 |
Attorney, Agent or Firm:
Hiromichi Kobayashi
Tomioka Kiyoshi
Tomioka Kiyoshi