IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0741393
(2007-04-27)
|
등록번호 |
US-7681400
(2010-04-21)
|
우선권정보 |
FR-06 51542(2006-04-28) |
발명자
/ 주소 |
- Daris, Thomas
- Prouteau, Jackie Raymond Julien
- Schenher, Frederic Henri Paul
- Brunet, Edgar
|
출원인 / 주소 |
|
대리인 / 주소 |
Oblon, Spivak, McClelland, Maier & Neustadt, L.L.P.
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인용정보 |
피인용 횟수 :
0 인용 특허 :
3 |
초록
▼
A propulsion gas exhaust assembly in an aircraft propelled by hot gases produced along an axis of the aircraft by a gas generator is disclosed. The propulsion gas exhaust assembly includes a transition element emerging in two duct elements each communicating with an ejection half-nozzle, wherein eac
A propulsion gas exhaust assembly in an aircraft propelled by hot gases produced along an axis of the aircraft by a gas generator is disclosed. The propulsion gas exhaust assembly includes a transition element emerging in two duct elements each communicating with an ejection half-nozzle, wherein each of the two duct elements forms an elbow downstream of the transition element.
대표청구항
▼
The invention claimed is: 1. A propulsion gas exhaust assembly, in an aircraft propelled by hot gases produced along an axis of the aircraft by a gas generator, comprising: a transition element that emerges in first and second duct elements, each of the first and second duct element communicating w
The invention claimed is: 1. A propulsion gas exhaust assembly, in an aircraft propelled by hot gases produced along an axis of the aircraft by a gas generator, comprising: a transition element that emerges in first and second duct elements, each of the first and second duct element communicating with a first and second ejection half-nozzle, respectively, wherein each of the first and second duct elements includes an elbow disposed downstream of the transition element, each elbow is defined by a first portion that guides the gas flow in a radial direction away from the axis of the aircraft and a second portion disposed downstream of the first portion, the second portion of each elbow guiding the gas flow in a radial direction toward said axis of the aircraft such that the gas flow downstream of each elbow is returned to the axis, wherein elements disposed inside the duct that are upstream of the elbow are not visible when the assembly is viewed in an upstream direction from a location downstream of the first and second ejection half-nozzles. 2. The assembly as claimed in claim 1, wherein the first and second elbows are disposed in the same plane and are symmetrical with respect to each other. 3. The assembly as claimed in claim 1, wherein the gas generator is a gas turbine engine. 4. The assembly as claimed in claim 3, wherein the transition element comprises a cylindrical upstream portion. 5. The assembly as claimed in claim 4, wherein the cross section of the transition element changes toward the downstream, from the cylindrical cross section shape progressively to a shape with two adjacent elliptical cross sections. 6. The assembly as claimed in claim 5, wherein the elliptical cross section of the first and second duct elements includes a vertical or horizontal major axis. 7. The assembly as claimed in claim 1, wherein a main propulsion gas flow is divided into a first and a second flow in the first and second duct element, respectively, for an ejection into the first and the second half-nozzle, respectively, and the assembly further comprises at least one of a means of distributing the main flow into each of the two half-nozzles or a means of orienting the thrust vector produced by each of the two half-nozzles. 8. The assembly as claimed in claim 7, wherein said means of distributing and means of orienting are fluid injection or mechanical. 9. The assembly as claimed in claim 7, wherein said half-nozzles are placed for a yaw orientation of the thrust vector. 10. The assembly as claimed in claim 7, wherein said half-nozzles are placed for a pitch or roll control. 11. The assembly as claimed in claim 9, further comprising first and second pairs of half-nozzles, the first pair for the yaw orientation, the second pair for the pitch control. 12. The assembly as claimed in claim 8, wherein the means for controlling the distribution of the flows comprises means for fluid injection at a throat of each of the half-nozzles. 13. The assembly as claimed in claim 12, wherein the gas generator is a turboengine, and the fluid injection means are supplied by air tapped from a compressor of the generator. 14. The assembly as claimed in claim 7, wherein the main flow is generated by two gas generators, and the assembly further comprises a means of orienting the thrust vector produced by each of the two half-nozzles. 15. A turbomachine comprising an exhaust assembly as claimed in claim 1. 16. The assembly as claimed in claim 1, wherein Lelbow/Lchannel is between 0.5 and 0.7, wherein Lelbow is a distance between an entrance plane of the transition element to a point where the elbow is at a maximum lateral deviation from the axis of the aircraft in an axial direction, and Lchannel is a distance between the entrance plane of the transition element to a throat of the half-nozzles in the axial direction. 17. The assembly as claimed in claim 1, wherein the first elbow is separate from the second elbow. 18. The assembly as claimed in claim 12, wherein the means for controlling the distribution of the flows further comprises means for fluid injection at an inner divergent wall of each of the half-nozzles.
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