公开(公告)号：US11629670B2

公开(公告)日：2023-04-18

申请号：US17516465

申请日：2021-11-01

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： Keum Oh Lee ,  Byoung Jik Lim ,  Kee Joo Lee

IPC: F02K9/52 ,  F02K9/95 ,  F02K9/60 ,  B33Y80/00

Abstract: An injection device for injecting an oxidizer for a liquid rocket includes a housing, a plate disposed inside the housing and having an injection hole to eject an oxidizer, a duct disposed above the plate to guide the oxidizer, and a manifold with one end connected to the injection hole of the plate and the other end connected to the duct, wherein the oxidizer may be distributed to the injection hole at an equal flow rate.

公开(公告)号：US11598290B2

公开(公告)日：2023-03-07

申请号：US17539846

申请日：2021-12-01

Applicant: KOREA AEROSPACE RESEARCH INSTITUTE

Inventor： Keum Oh Lee ,  Byoung Jik Lim ,  Jun Sung Lee ,  Kee Joo Lee ,  Jae Sung Park

IPC: F02K9/64 ,  F02K9/97 ,  F02K9/44

Abstract: A combustor of a liquid rocket engine includes a nozzle unit including a regenerative cooling channel, in which the nozzle unit includes a fuel manifold outer shell, a combustor inner shell, and a combustor outer shell having a downward channel inlet, and the combustor includes a fuel inlet connected to a nozzle neck of the nozzle unit, a fuel manifold formed between the fuel manifold outer shell and the combustor outer shell, and in which fuel introduced from the fuel inlet flows, a downward channel connected in communication with the fuel manifold through the downward channel inlet, and extending in a downward direction from an upper portion of the combustor, a diverting manifold provided at a distal end of the nozzle unit and connected in communication with the downward channel, and an upward channel connected in communication with the diverting manifold and extending in an upward direction of the combustor.