Title:
AIRCRAFT ENGINE COMBUSTOR
Document Type and Number:
WIPO Patent Application WO/2024/057775
Kind Code:
A1
Abstract:
An aircraft engine combustor equipped with a cylindrical member for demarcating an internal space which extends along an axis, and a fuel nozzle which is positioned in a manner such that at least a part thereof is positioned inside the internal space, and has an injection hole through which a liquid fuel is injected toward the inner-circumferential surface of the cylindrical member, wherein the cylindrical member is configured in a manner such that the entirety, in the circumferential direction, of a tip end surface extending radially outward from the discharge port end of the inner-circumferential surface has a first contact angle relative to the liquid fuel which is less than 90°.
Inventors:
IKEDA YUTAKA (JP)
FUJIMOTO YOHEI (JP)
FUJIMOTO YOHEI (JP)
Application Number:
PCT/JP2023/028748
Publication Date:
March 21, 2024
Filing Date:
August 07, 2023
Export Citation:
Assignee:
MITSUBISHI HEAVY IND AERO ENGINES LTD (JP)
International Classes:
F23R3/28; B05B7/04; B05B7/10; F02C3/24; F02C7/00; F02C7/232
Domestic Patent References:
| WO2020049861A1 | 2020-03-12 | |||
| WO2019094817A1 | 2019-05-16 |
Foreign References:
| JP2009250240A | 2009-10-29 | |||
| JP2009274065A | 2009-11-26 | |||
| JP2005207634A | 2005-08-04 | |||
| JP2005106411A | 2005-04-21 | |||
| JP2004085123A | 2004-03-18 | |||
| US4842197A | 1989-06-27 |
Attorney, Agent or Firm:
SSIP PATENT ATTORNEY CORPORATION (JP)
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