Mounting system inserted between an aircraft engine and a rigid structure of an attachment strut fixed under a wing of this aircraft
원문보기
IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0059440
(2005-02-17)
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우선권정보 |
FR-04 50444(2004-03-04) |
발명자
/ 주소 |
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출원인 / 주소 |
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대리인 / 주소 |
Oblon, Spivak, McClelland, Maier & Neustadt, P.C.
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인용정보 |
피인용 횟수 :
7 인용 특허 :
6 |
초록
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This invention relates to a mounting system (1) inserted between an aircraft engine and a rigid structure of a strut, comprising a thrust resistance device (20) comprising a spreader beam (28) provided with two lateral lower ends (32a) placed such that a horizontal plane passes through them and thro
This invention relates to a mounting system (1) inserted between an aircraft engine and a rigid structure of a strut, comprising a thrust resistance device (20) comprising a spreader beam (28) provided with two lateral lower ends (32a) placed such that a horizontal plane passes through them and through a longitudinal axis of the engine. Moreover, the device (20) is also fitted with two fittings (44) each comprising a forward end ( 44a) through which the said horizontal plane also passes and fixed to a forward part of a central casing (22), and an aft end (44b) connected to one of the ends (32a). Furthermore, the spreader beam is connected to the forward mount and to the rigid structure through its upper end (30b).
대표청구항
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The invention claimed is: 1. Mounting system (1) inserted between an aircraft engine (2) and a rigid structure (4) of an attachment strut (6) fixed under a wing (8) of an aircraft, the system including a forward mount (16), an aft mount (18), and a device (20) for resisting thrusts generated by the
The invention claimed is: 1. Mounting system (1) inserted between an aircraft engine (2) and a rigid structure (4) of an attachment strut (6) fixed under a wing (8) of an aircraft, the system including a forward mount (16), an aft mount (18), and a device (20) for resisting thrusts generated by the engine (2 ), characterized in that the said thrust resistance device (20) comprises a spreader beam (28) provided with an upper arm ( 30) and two lateral lower arms (32), the upper and lateral lower arms (30,32) being fixed and fitted with an upper end (30b) and two lateral lower ends (32a) of the spreader beam (28), the two lateral lower ends (32a) being placed such that a horizontal plane passes through them and through a longitudinal axis (5) of the engine (2), the thrust resistance device (20) also being fitted with two fittings ( 44) on each side of the engine (2) and each comprising a forward end (44a) through which the horizontal plane passing through the longitudinal axis (5) of the engine (2) also passes, and fixed to a forward part of a central casing (22) of the engine, and an aft end (44b) connected to one of the two lateral lower ends (32a) of the spreader beam (28 ), and in that the said spreader beam (28) is also connected to the forward mount (16) of the mounting system, and to the rigid structure (4) of the attachment strut (6) through its upper end (30b). 2. Mounting system (1) according to claim 1, characterized in that the said spreader beam (28) is connected to the forward mount (16) through at least one swivel pin (34) oriented along a transverse direction (Y) of the aircraft. 3. Mounting system (1) according to claim 2, characterized in that each swivel pin (34) passes through a double headed end (17a) of a forward mount body (17), and a lower end (30a) of the upper arm (30) of the said spreader beam (28). 4. Mounting system (1) according to any one of the above claims, characterized in that the upper end (30b) of the upper arm (30) is connected to the rigid structure (4) of the attachment strut (6) through a connecting rod (36). 5. Mounting system (1) according to claim 4, characterized in that the said connecting rod (36) is oriented approximately along a longitudinal direction (X) of the aircraft, and in that an aft end (36b) of the said connecting rod (36) cooperates with a forward part of an upper stringer (10) of the rigid structure (4) of the attachment strut (6). 6. Mounting system (1) according to claim 5, characterized in that the upper end (30b) of the upper arm (30) is connected to a forward end (36a) of the said connecting rod (36) through at least one swivel pin (38) oriented along a transverse direction (Y) of the aircraft, and in that a fitting (40) fixed to the forward part of the upper stringer ( 10) of the rigid structure (4) of the attachment strut ( 6) is connected to the aft end (36b) of the said connecting rod (36) through at least one swivel pin (42) oriented along this same transverse direction (Y) of the aircraft. 7. Mounting system (1) according to claim 6, characterized in that the upper end (30b) of the upper arm (30) and the said fitting (40) are double headed. 8. Mounting system (1) according to claim 1, characterized in that each aft end (44b) of the two fittings (44) fixed to the forward part of the central casing ( 22) of the engine (2) is connected to one of the two lateral lower ends (32a) of the spreader beam (28) using a connecting rod (46). 9. Mounting system (1) according to claim 1, characterized in that the upper arm (30) of the spreader beam ( 28) is straight and is oriented along a vertical direction (Z) of the aircraft, and in that the two lateral lower arms (32) combined form an approximate half-ring. 10. Mounting system (1) according to claim 1, characterized in that the said system comprises a forward mount (16 ) fixed to the forward part of the central casing (22) of the engine (2) and a forward end of a pyramid (14) forming a forward part of the rigid structure (4) of the strut (6), and in that the said system also comprises an aft mount (18) fixed to an aft part of the central casing (22) of the engine (2) and the rigid structure (4) of the strut (6). 11. Mounting system (1) according to claim 10, characterized in that the upper arm (30) of the spreader beam ( 28) is arranged so as to pass through the said pyramid (14) of the rigid structure (4) of the strut (6). 12. Attachment strut (6) of an aircraft engine ( 2) under a wing (8) of an aircraft, the said strut being provided with a mounting system (1) inserted between the said engine (2) and a rigid structure (4) of this strut, characterized in that the said mounting system (1) is a system according to claim 1.
이 특허에 인용된 특허 (6)
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Hodgkinson Carl (Derby GB2), Engine mount including engine mount failure indicator.
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Seaquist John D. ; Culbertson Chris, Horizontally opposed trunnion forward engine mount system supported beneath a wing pylon.
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Murphy Patrick (Bellevue WA), Mounting apparatus for fan jet engine having mixed flow nozzle installation.
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Rodgers Leonard J.,GB2 ; Newton Arnold C.,GB2 ; Berry James P.,GB2 ; Farrar Peter G. G.,GB2 ; Udall Kenneth F.,GB2, Mounting for coupling a turbofan gas turbine engine to an aircraft structure.
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Nightingale Douglas J. (Bellview WA), Mounting for gas turbine powerplant.
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Smith Michael A. (Tacoma WA), Strut supported inlet.
이 특허를 인용한 특허 (7)
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Balk, Wouter, Attachment of a multiflow turbojet engine to an aircraft.
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Diochon, Lionel; Cetout, Jean-Michel; LaFont, Laurent, Engine assembly for aircraft.
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Woolley, Allen Madsen; Clegg, Brian Kelby; Just, Michael Scott; Patel, Rameshchandra Dahyabhai, Engine pylon structure.
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Chen, George; Mkhitarian, Harry; Sentosa, Samuel; Su, David P., Method and apparatus for recharging batteries in a more efficient manner.
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Penda, Allan R.; Merry, Brian D.; Suciu, Gabriel L.; Dye, Christopher M., Single plane mount system for gas turbine engine.
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MacFarlane, Ian Alexander, Turboprop engine with compressor turbine shroud.
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Macfarlane, Ian Alexander, Turboprop engine with compressor turbine shroud.
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