Invention Grant
- Patent Title: Cooling mechanism of combustion chamber, rocket engine having cooling mechanism, and method of manufacturing cooling mechanism
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Application No.: US15556461Application Date: 2016-03-09
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Publication No.: US10787998B2Publication Date: 2020-09-29
- Inventor: Daiki Watanabe , Masaki Adachi , Hiroyuki Kobayashi , Akihide Kurosu , Hideto Kawashima , Nobuki Negoro
- Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD. , Japan Aerospace Exploration Agency
- Applicant Address: JP Tokyo JP Tokyo
- Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.,JAPAN AEROSPACE EXPLORATION AGENCY
- Current Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.,JAPAN AEROSPACE EXPLORATION AGENCY
- Current Assignee Address: JP Tokyo JP Tokyo
- Agency: Wenderoth, Lind & Ponack, L.L.P.
- Priority: com.zzzhc.datahub.patent.etl.us.BibliographicData$PriorityClaim@d63477e
- International Application: PCT/JP2016/057429 WO 20160309
- International Announcement: WO2016/143827 WO 20160915
- Main IPC: F02K9/64
- IPC: F02K9/64 ; F02K9/40 ; F23R3/00 ; F23M5/08 ; F02K9/97 ; F01D5/18
Abstract:
A cooling mechanism includes a bottom wall (22) in contact with a combustion chamber, an upper wall (30), and a cooling passage (40) arranged between the bottom wall (22) and the upper wall (30). The cooling passage (40) includes a first passage (50) extending to a first direction, a second passage (60) extending to the first direction, and a connection section (70) connected with the first passage (50) and the second passage (60). The second passage (60) is arranged to have an offset to the first passage (50) in a second direction perpendicular to the first direction and along the bottom wall (22).
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