Invention Application
- Patent Title: AIRCRAFT TURBOJET ENGINE FAN CASING
- Patent Title (中): 飞机涡轮发动机风扇
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Application No.: US13718532Application Date: 2012-12-18
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Publication No.: US20130111873A1Publication Date: 2013-05-09
- Inventor: Wouter BALK , François GALLET , Nicolas DEZEUSTRE , Oliver KERBLER
- Applicant: AIRCELLE , SNECMA
- Applicant Address: FR Paris FR Gonfreville L'orcher
- Assignee: SNECMA,AIRCELLE
- Current Assignee: SNECMA,AIRCELLE
- Current Assignee Address: FR Paris FR Gonfreville L'orcher
- Priority: FR1054845 20100618
- Main IPC: F02C3/08
- IPC: F02C3/08

Abstract:
An aircraft turbojet engine fan casing in the form of a box section is provided by the present disclosure. The box section includes a radially interior wall of which is able to form an internal skin of a cold air flow duct of a nacelle in which said turbojet engine is intended to be mounted, and a radially exterior wall of which is able to form an external skin of said nacelle, the box forming a module forming an entire thickness of the nacelle, and placed between an upstream portion of the nacelle, forming the air intake, and a downstream casing portion, on which a cascade edge of a thrust reverser can be fixed.
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