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1. 发明授权

US5192023A Jet engine provided with a thrust reverser 失效
标题翻译：喷气发动机配有推力反向器
公开(公告)号：US5192023A
公开(公告)日：1993-03-09
申请号：US573481
申请日：1990-08-24
申请人： Etienne Fage , Jean-Pierre Lair
发明人： Etienne Fage , Jean-Pierre Lair
IPC分类号： F02K1/11 , F02K1/60
CPC分类号： F02K1/60 , F02K1/11 , Y02T50/671
摘要： A jet engine for an aircraft has a thrust reverser including one or more doors which define at least a part of the throat of the engine's nozzle. The engine further includes a latch mechanism for retaining the doors in a stowed position. The doors may be deployed for reversal of engine thrust, but are also capable while stowed of being pivoted in a limited way to change the cross-section area of the throat of the nozzle.
摘要翻译：用于飞机的喷气发动机具有推力反向器，其包括限定发动机喷嘴的喉部的至少一部分的一个或多个门。发动机还包括用于将门保持在收起位置的闩锁机构。门可以部署用于反转发动机推力，而且还能够以有限的方式枢转以改变喷嘴的喉部的横截面积。

2. 发明授权

US5775639A Thrust reverser with pivoting doors which can move in translation 失效
标题翻译：具有可翻转运动的旋转门的推力倒车器
公开(公告)号：US5775639A
公开(公告)日：1998-07-07
申请号：US544445
申请日：1995-11-17
申请人： Etienne Fage
发明人： Etienne Fage
IPC分类号： F02K1/60 , F02K1/76
CPC分类号： F02K1/76 , F02K1/60 , F05D2250/34 , Y02T50/671 , Y10T292/1023 , Y10T292/282
摘要： A thrust reverser with doors (5, 6) for an aircraft jet engine includes a radial stop which includes elements (16, 28) integral with the front end of each door (5, 6) and capable of interacting with mating elements (15, 3) that are integral with the engine. The radial stop is designed to prevent the deployment of the door in an advanced position of its axis of pivoting (P--P) and to allow this deployment in a retreated position of the axis of pivoting (P--P).
摘要翻译：具有用于飞机喷气式发动机的门（5,6）的推力反向器包括径向止动件，其包括与每个门（5,6）的前端成一体的元件（16,28），并且能够与配合元件 3）与发动机是一体的。径向止动器被设计成防止门处于其枢转轴线（P-P）的先进位置并允许其部署在枢转轴线（P-P）的撤回位置。

3. 发明授权

US4362015A Double jet gas turbine engine equipped with a thrust reverser 失效
标题翻译：配备推力反向器的双喷气涡轮发动机
公开(公告)号：US4362015A
公开(公告)日：1982-12-07
申请号：US144675
申请日：1980-04-28
申请人： Etienne Fage
发明人： Etienne Fage
IPC分类号： F02K1/60 , F02K3/06
CPC分类号： F02K1/60
摘要： The present invention relates to a gas turbine engine which is provided with a thrust reverser with unfoldable doors and which is of the double jet type, i.e. comprising a central generator emitting a jet of hot gas and surrounded by an annular by-pass conduit through which a jet of relatively cold gas passes, wherein said turbine engine comprises means for restricting the passage of the jet of relatively cold gas in said annular by-pass conduit when the doors of the thrust reverser are unfolded. The invention results in a simplification of the structure of the doors of the thrust reverser.
摘要翻译：本发明涉及一种燃气轮机发动机，其具有可展开的门并具有双喷射型的推力反向器，即包括发射热气体射流并由环形旁路管道围绕的中央发生器相对冷气体的气流通过，其中所述涡轮发动机包括用于在推力反向器的门展开时限制在所述环形旁通管道中的相对冷气体的射流通过的装置。本发明导致推力反向器的门的结构的简化。

4. 发明授权

US5310117A Jet engine provided with a thrust reverser 失效
标题翻译：喷气发动机配有推力反向器
公开(公告)号：US5310117A
公开(公告)日：1994-05-10
申请号：US13964
申请日：1993-02-05
申请人： Etienne Fage , Jean-Pierre Lair
发明人： Etienne Fage , Jean-Pierre Lair
IPC分类号： F02K1/11 , F02K1/60 , F02K1/10 , F02K1/12
CPC分类号： F02K1/60 , F02K1/11 , Y02T50/671
摘要： A jet engine for an aircraft has a thrust reverser including one or more doors which define at least a part of the throat of the engine's nozzle. The engine further includes a latch mechanism for retaining the doors in a stowed position. The doors may be deployed for reversal of engine thrust, but are also capable while stowed of being pivoted in a limited way to change the cross-section area of the throat of the nozzle.
摘要翻译：用于飞机的喷气发动机具有推力反向器，其包括限定发动机喷嘴的喉部的至少一部分的一个或多个门。发动机还包括用于将门保持在收起位置的闩锁机构。门可以部署用于反转发动机推力，而且还能够以有限的方式枢转以改变喷嘴的喉部的横截面积。

5. 发明授权

US4966327A Jet engine provided with a thrust reverser 失效
标题翻译：喷气发动机配有推力反向器
公开(公告)号：US4966327A
公开(公告)日：1990-10-30
申请号：US263224
申请日：1988-10-27
申请人： Etienne Fage , Jean-Pierre Lair
发明人： Etienne Fage , Jean-Pierre Lair
IPC分类号： F02K1/11 , F02K1/60
CPC分类号： F02K1/11 , F02K1/60 , Y02T50/671
摘要： A jet engine for an aircraft has a thrust reverser including one or more doors which define at least a part of the throat of the engine's nozzle. The engine further includes a latch mechanism for retaining the doors in a stowed position. The doors may be deployed for reversal of engine thrust, but are also capable while stowed of being pivoted in a limited way to change the cross-section area of the throat of the nozzle.
摘要翻译：用于飞机的喷气发动机具有推力反向器，其包括限定发动机喷嘴的喉部的至少一部分的一个或多个门。发动机还包括用于将门保持在收起位置的闩锁机构。门可以部署用于反转发动机推力，而且还能够以有限的方式枢转以改变喷嘴的喉部的横截面积。

6. 发明授权

US4422605A Reverser for jet engine 失效
标题翻译：喷气发动机逆变器
公开(公告)号：US4422605A
公开(公告)日：1983-12-27
申请号：US300989
申请日：1981-09-10
申请人： Etienne Fage
发明人： Etienne Fage
IPC分类号： F02K1/60 , F02K1/76 , B64D33/04
CPC分类号： F02K1/766 , F02K1/60
摘要： The invention relates to a thrust reverser for the jet engine of an aircraft. According to the invention, the unlocking of the doors with a view to passage from their folded position to their extended position, is effective only after they have been previously brought into a super-retracted position with respect to the folded position and said reverser comprises stops which allow the doors to pass from the folded position to the super-retracted position only when the rpm of said engine is lower than a threshold close to idling rpm. The invention is particularly applicable to ensuring operational safety of thrust reversers.
摘要翻译：本发明涉及一种用于飞行器的喷气发动机的推力反向器。根据本发明，门的解锁以便从折叠位置通过到其延伸位置，仅在先前已经相对于折叠位置进入超缩回位置之后才有效，并且所述反向器包括止动件这允许门只有当所述发动机的转速低于接近空转转速的阈值时，才能从折叠位置传递到超缩回位置。本发明特别适用于确保推力反向器的操作安全性。

7. 发明授权

US5956939A Bypass jet engine with confluent nozzle, rotating members which control the bypass air flow and a thrust reverser which controls the variable exhaust area 失效
标题翻译：旁路喷气发动机具有汇流喷嘴，控制旁路气流的旋转构件和控制可变排气区域的推力反向器
公开(公告)号：US5956939A
公开(公告)日：1999-09-28
申请号：US958345
申请日：1997-10-27
申请人： Etienne Fage
发明人： Etienne Fage
IPC分类号： F02K1/06 , F02K1/16 , F02K1/38 , F02K1/54 , F02K1/60 , F02K3/02 , F02K1/10 , F02K1/56
CPC分类号： F02K1/06 , F02K1/16 , F02K1/386 , F02K1/54 , F02K1/60 , F02K3/02 , Y02T50/672
摘要： A bypass jet engine which includes a confluent nozzle (8) and a thrust reverser (7), controlled means (14) arranged at the periphery of the confluent nozzle (8) adjacent to the mouth of an annular bypass duct (4) and inside this nozzle to vary the confluence cross section. The bypass jet engine also includes means of shifting the pivot pins (20) of the reverser doors (7) in order to reduce the cross section of the outlet orifice of the nozzle when the controlled means (14) of varying the confluence cross section increase the confluence cross section and, conversely, to increase the cross section of the outlet orifice of the nozzle when the controlled means (14) reduce the confluence cross section.
摘要翻译：一种旁路喷气发动机，其包括汇合喷嘴（8）和推力反向器（7），控制装置（14）布置在与环形旁通管道（4）的口部相邻的汇合喷嘴（8）的周边，并且内部这个喷嘴改变汇合截面。旁路喷气发动机还包括移动反向门（7）的枢轴销（20）的装置，以便当改变汇流横截面的受控装置（14）增加时，减小喷嘴的出口孔的横截面汇合横截面，相反地，当受控装置（14）减小汇合横截面时，增加喷嘴的出口孔的横截面。

8. 发明授权

US5211008A Gas ejection nozzle for a jet engine and a jet engine fitted with this nozzle, in particular an engine of the separate flow type 失效
标题翻译：用于喷气发动机的气体喷射喷嘴和用该喷嘴，特别是单独流动型发动机的喷气发动机
公开(公告)号：US5211008A
公开(公告)日：1993-05-18
申请号：US798807
申请日：1991-11-27
申请人： Etienne Fage
发明人： Etienne Fage
IPC分类号： F02K1/09 , F02K1/74
CPC分类号： F02K1/09 , F02K1/74
摘要： The invention relates to an ejection nozzle with a variable outlet section for a jet engine. An axially moving annular skirt (4) is disposed about the fixed nozzle wall (2) so that it can be displaced axially between an upstream position in which the skirt is disposed retracted about the fixed wall (2) and a downstream position in which it projects to the rear of the outlet section of this wall. A semiflexible crown (8) is provided to ensure the connection between the moving skirt (4) and the fixed wall (2), this crown bearing elastically about the wall (2). The invention makes it possible in particular to increase the outlet section of a central hot gas nozzle so as to ensure a reduction of the hot jet thrust when the thrust reversers are applied on the cold jet. It also makes it possible in certain flight conditions, especially during take-off in hot weather, to reduce the temperature of the hot outlet gases and thus to increase the speed of the gas generator and increase the direct jet thrust.
摘要翻译：本发明涉及具有用于喷气发动机的可变出口部分的喷嘴。轴向移动的环形裙部（4）围绕固定喷嘴壁（2）设置，使得其可以在裙部围绕固定壁（2）缩回的上游位置和下游位置之间沿轴向移动投射到这堵墙出口部分的后部。提供半柔性冠（8）以确保移动裙部（4）和固定壁（2）之间的连接，该冠部轴承围绕壁（2）弹性地弹性。本发明特别地可以增加中央热气喷嘴的出口部分，以确保当将推力反向器应用于冷喷射时减少热喷射推力。这也可以在某些飞行条件下，特别是在炎热的天气下起飞时，可以降低热出口气体的温度，从而提高气体发生器的速度并增加直接喷射推力。

9. 发明授权

US4860956A Thrust reverser for aircraft jet engine and aircraft engine equipped with said thrust reverser 失效
标题翻译：用于具有所述推力反向器的飞机喷气发动机和飞机发动机的推力反向器
公开(公告)号：US4860956A
公开(公告)日：1989-08-29
申请号：US84910
申请日：1987-08-13
申请人： Etienne Fage
发明人： Etienne Fage
IPC分类号： F02K1/60
CPC分类号： F02K1/60
摘要： This invention relates to a thrust reverser for aircraft jet engine having at least one door mounted to the downstream end of the jet generator to pivot about an axis which is transverse and at least substantially diametral to said jet, the door being able to pivot between a retracted position and an extended position. According to the invention, an at least partially supple seal is provided between the opposite parts of the inner and outer surfaces, respectively, of the door and of the jet generator, the transverse section of the seal being continually adapted to the space between the door and the jet generator in retracted position of the door.
摘要翻译：本发明涉及一种用于飞行器喷气发动机的推力反向器，其具有至少一个门，其安装到喷射发生器的下游端，以围绕横向并且至少基本上直径于所述射流的轴线枢转，门能够在缩回位置和延伸位置。根据本发明，分别在门和喷气发生器的内表面和外表面的相对部分之间提供至少部分柔软的密封，密封件的横向部分连续地适应于门之间的空间并且喷射发生器处于门的缩回位置。

10. 发明授权

US5097661A Jet engine having a planar exit opening 失效
标题翻译：喷气式发动机有平面出口打开
公开(公告)号：US5097661A
公开(公告)日：1992-03-24
申请号：US331128
申请日：1989-03-31
申请人： Jean-Pierre Lair , Etienne Fage , Thomas E. Finch
发明人： Jean-Pierre Lair , Etienne Fage , Thomas E. Finch
IPC分类号： F02K1/60
CPC分类号： F02K1/60
摘要： To eliminate the fish-mouth geometry at the downstream portion of a thrust reverser fitted jet engine which results from the formation of substantially arcuate notches when the thrust reverser doors are stowed, moveable flaps are positioned in close proximity to the doors such that when the doors are in their stowed position, the flaps would fill, at least partially, the arcuate notches to effect a substantially planar exit opening, thereby substantially eliminating the fish-mouth geometry. Moreover, the flaps can be used to effect a uniform thickness for the exit opening of the jet engine by each having a shape corresponding to that of the corresponding arcuate notch; and the principal outer surfaces and inner surfaces of the flaps provide continuity with the outer surfaces and the inner surfaces, respectively, of the doors, with the ends of the flaps have trailing edge which have thicknesses similar to those of the trailing edges of the doors. Thus, when the doors are in their stowed position, the respective trailing edges of the doors and the flaps form a minimum base surface, at the exit opening of the jet engine, in the shape of a ring having a uniform minimum thickness.
摘要翻译：为了消除在推力反向器装配的喷气发动机的下游部分处的鱼嘴几何形状，其在推力反向器门被收起时形成基本上弧形的凹口，可移动的襟翼位于门附近，使得当门处于其收起位置，翼片将至少部分地填充弧形凹口以实现基本上平面的出口，从而基本上消除鱼嘴几何形状。此外，翼片可以用于对喷气发动机的出口形成均匀的厚度，每个具有对应于相应弓形凹口的形状; 并且翼片的主要外表面和内表面分别提供与门的外表面和内表面的连续性，其中翼片的端部具有后缘，其厚度类似于门的后缘的厚度。因此，当门处于其收起位置时，门和翼片的相应后缘在喷气发动机的出口处形成具有均匀最小厚度的环形的最小基面。

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