Title:
NACELLE FOR AN AIRCRAFT BYPASS TURBOJET ENGINE
Document Type and Number:
WIPO Patent Application WO/2012/098322
Kind Code:
A3
Abstract:
The invention relates to a nacelle for a turbojet engine, having a longitudinal axis and a rear section including an annular flow path comprising walls (110) defining a space (3, 10) through which a main air flow (12) passes. The nacelle includes at least one device (100) for modulating the cross-section of the space (3, 10), comprising: means (102) for injecting an auxiliary flow (104) of a gas, configured to vary the orientation and/or speed of the auxiliary flow (104); suction means (106) for drawing in at least part of the injected auxiliary flow (112); and an internal auxiliary flow (109) return area (108) in one or more walls (110), said area being configured to allow the circulation of said part of the injected auxiliary flow (104) and the drawn-in auxiliary flow (112).
Inventors:
GONIDEC PATRICK (FR)
BLIN LAURENT ALBERT (FR)
BLIN LAURENT ALBERT (FR)
Application Number:
PCT/FR2012/050052
Publication Date:
September 13, 2012
Filing Date:
January 09, 2012
Export Citation:
Assignee:
AIRCELLE SA (FR)
GONIDEC PATRICK (FR)
BLIN LAURENT ALBERT (FR)
GONIDEC PATRICK (FR)
BLIN LAURENT ALBERT (FR)
International Classes:
F02K1/30; B64C21/02; B64D33/02; B64D33/04; F02C7/04
Foreign References:
| GB1298069A | 1972-11-29 | |||
| US6655632B1 | 2003-12-02 | |||
| EP1921291A2 | 2008-05-14 | |||
| FR1505592A | 1967-12-15 |
Attorney, Agent or Firm:
Cabinet GERMAIN & MAUREAU (Paris, FR)
Download PDF: