Noise control chevron for a nozzle, and nozzle and turboshaft engine provided with such a chevron
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02K-001/48
F02K-001/38
출원번호
US-0672796
(2008-08-04)
등록번호
US-8887489
(2014-11-18)
우선권정보
FR-07 05847 (2007-08-14)
국제출원번호
PCT/FR2008/001165
(2008-08-04)
§371/§102 date
20100209
(20100209)
국제공개번호
WO2009/053554
(2009-04-30)
발명자
/ 주소
Sylla, Amadou André
Huber, Jérôme
Pelagatti, Olivier
Prat, Damien
Debatin, Klaus
출원인 / 주소
Airbus Operations (SAS)
대리인 / 주소
Novak Druce Connolly Bove + Quigg LLP
인용정보
피인용 횟수 :
0인용 특허 :
5
초록▼
According to the invention, the shape of each of said chevrons is defined: by two lateral sides (21, 22) having front ends (21A, 22A) that are connected to said nozzle (4, 10) and that, when moving away from the latter, converge towards each other without joining so that the rear ends (21R, 22R) of
According to the invention, the shape of each of said chevrons is defined: by two lateral sides (21, 22) having front ends (21A, 22A) that are connected to said nozzle (4, 10) and that, when moving away from the latter, converge towards each other without joining so that the rear ends (21R, 22R) of said lateral walls (21, 22) are spaced from each other; and by a curvilinear transverse line (23.1) connecting the rear ends (21R, 22R) of said lateral walls (21, 22) by forming two rounded side protrusions (24.1, 25.1) separated by an intermediate rounded recess (26.1).
대표청구항▼
1. A chevron (20.1, 20.2, 20.3) which is positioned at the periphery of an outlet orifice (5, 11) for the jet (7, 9) from a turbojet engine nozzle (4, 10) for the purposes of attenuating the noise of said jet and the shape of which is delimited: by two at least approximately rectilinear lateral side
1. A chevron (20.1, 20.2, 20.3) which is positioned at the periphery of an outlet orifice (5, 11) for the jet (7, 9) from a turbojet engine nozzle (4, 10) for the purposes of attenuating the noise of said jet and the shape of which is delimited: by two at least approximately rectilinear lateral sides (21, 22) of which front ends (21A, 22A) are secured to said nozzle (4, 10) and which, with increasing distance therefrom, converge toward one another without meeting so that rear ends (21R, 22R) of said lateral sides (21, 22) are separated from one another; andby a transverse line (23.1, 23.2, 23.3) which connects the rear ends (21R, 22R) of said lateral sides (21, 22) thereby forming two lateral protrusions (24.1, 25.1-24.2, 25.2-24.3, 25.3) separated by an intermediate recess (26.1, 26.2, 26.3),wherein said transverse line (23.1, 23.2, 23.3) is curvilinear in such a way that said lateral protrusions (24.1, 25.1-24.2, 25.2-24.3, 25.3) and said intermediate recess (26.1, 26.2, 26.3) are rounded,wherein the lateral sides (21, 22) of said chevrons are inclined symmetrically to one another with respect to a median longitudinal axis the overall direction of which is that of said jet (7, 9),wherein said rounded lateral protrusions (24.2, 25.2; 24.3, 25.3) are offset from one another along said median longitudinal axis of said chevron (20.2, 20.3),wherein no portion of the transverse line extends from the two lateral protrusions toward the nozzle as far as do the rectilinear lateral sides, andwherein the transverse line and the intermediate recess are asymmetrical about the median longitudinal axis. 2. A turbojet engine nozzle of which the jet outlet orifice (5, 11) is provided with chevrons distributed at its periphery in order to attenuate the noise of said jet, wherein said chevrons are those specified in claim 1. 3. The nozzle as claimed in claim 2, wherein said chevrons are all identical. 4. A bypass turbojet engine comprising a nozzle for the cold flow and a nozzle for the hot flow, wherein at least one of said nozzles is as specified in claim 2. 5. A bypass turbojet engine comprising a nozzle for the cold flow and a nozzle for the hot flow, wherein said nozzle for the cold flow and said nozzle for the hot flow are as specified in claim 2. 6. A turbojet engine nozzle of which the jet outlet orifice (5, 11) is provided with chevrons distributed at its periphery in order to attenuate the noise of said jet, wherein said chevrons are those specified in claim 1, wherein two consecutive chevrons differ from and are symmetric to one another with respect to the overall direction of said jet (7, 9).
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이 특허에 인용된 특허 (5)
Feuillard,Philippe; Hemeury,Philippe; Gerri,Christian, Chevron-type primary exhaust nozzle for aircraft turbofan engine, and aircraft comprising such a nozzle.
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