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公开(公告)号：US20170275010A1
公开(公告)日：2017-09-28
申请号：US15622325
申请日：2017-06-14
申请人： ROHR, INC.
发明人： MICHAEL SEAN PRETTY , JOHN MOULE , JOSEPH C. ZECCA
摘要： A nacelle may include a pylon and a thrust reverser having an inner fixed structure. A locking mechanism may automatically engage and prevent relative movement between thrust reverser halves. A bumper may be coupled to the inner fixed structure. The locking mechanism may limit deflections between the thrust reverser and the pylon in response to a burst duct. A locking mechanism in the inner fixed structure may include a pressure relief door and an arrestor which hooks onto a retaining bar in a pylon bracket. The locking mechanism may allow the thrust reverser halves to be opened for access to the engine.
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公开(公告)号：US09764818B2
公开(公告)日：2017-09-19
申请号：US15040663
申请日：2016-02-10
申请人： Rohr, Inc.
IPC分类号： B64C1/40 , G10K11/168 , B64D29/00 , G10K11/172 , B64C1/00 , G10K11/16
CPC分类号： B64C1/40 , B64C1/066 , B64D29/00 , G10K11/168 , G10K11/172
摘要： A structural panel may be configured for attenuating noise. This panel includes a first skin, a second skin and a core forming a plurality of cavities vertically between the first skin and the second skin. The core may include a wall connected to and extending vertically between the first skin and the second skin. The wall may be laterally between and fluidly separate at least a first of the cavities from a second of the cavities. The wall may include a vertical stiffener. One or more perforations in the first skin may be fluidly coupled with the first of the cavities.
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公开(公告)号：US09719421B2
公开(公告)日：2017-08-01
申请号：US14122943
申请日：2012-05-31
申请人： Predrag Todorovic
发明人： Predrag Todorovic
CPC分类号： F02C7/042 , B64D29/00 , B64D29/06 , B64D33/02 , B64D2033/0286 , Y02T50/671
摘要： An aircraft gas-turbine engine has an engine cowling-nacelle which surrounds a core engine in a tubular way, characterized in that at least one inflow-side part of the engine cowling-nacelle is telescopically movable against the flow direction.
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公开(公告)号：US20170175766A1
公开(公告)日：2017-06-22
申请号：US14974195
申请日：2015-12-18
摘要： A gas turbine engine comprises a nacelle that encloses a fan rotor carrying a plurality of fan blades. The nacelle is formed with droop such that one portion extends axially further from the fan blades than does another portion. The nacelle is rotatable such that a circumferential location of the one portion and the other portion may be varied dependent on flight conditions. A method of operating a gas turbine engine is also disclosed.
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公开(公告)号：US09670876B2
公开(公告)日：2017-06-06
申请号：US14184335
申请日：2014-02-19
CPC分类号： F02K1/763 , B23P19/04 , B64D29/00 , B64D33/04 , F02K1/60 , F02K1/605 , F02K1/62 , F02K1/64 , F02K1/72 , F05D2260/50 , Y10T29/49229
摘要： A pivot thrust reverser includes a first tandem pivot door subassembly comprising an inner panel and an outer panel. The inner panel and outer panel are connected by a first sliding rail. A second tandem pivot door subassembly is included comprising an inner panel and an outer panel. The inner panel and outer panel are connected by a second sliding rail.
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公开(公告)号：US09670798B2
公开(公告)日：2017-06-06
申请号：US13870369
申请日：2013-04-25
申请人： AIRCELLE
摘要： A turbojet engine nacelle includes a rear section having an internal structure. The internal structure surrounds a rear part of an engine compartment and delimits, with an ejection jet pipe, an outlet cross section for the ventilation of the engine compartment. The engine nacelle includes a moving element associated with a corresponding controller. The moving element is able to move between a withdrawn position in which the outlet cross section for ventilation is at a maximum and an engaged position in which the moving element partially reduces the outlet cross section for ventilation by comparison with the retracted position. The controller is capable of moving the moving element between the retracted and engaged positions.
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公开(公告)号：US20170096230A1
公开(公告)日：2017-04-06
申请号：US15280300
申请日：2016-09-29
发明人： Thierry Surply , Alain Porte
CPC分类号： B64D29/00 , B64D15/04 , B64D33/02 , B64D2033/0206 , B64D2033/0233 , F02C7/045 , F02C7/047 , Y02T50/672
摘要： An acoustic structure for an aircraft nacelle which comprises an acoustically resistive substructure, at least one layer of cells and a reflective layer. The acoustic structure comprises at least one single-piece substructure which divides up the layer of cells and which incorporates elongated elements of a de-icing system.
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公开(公告)号：US20170030397A1
公开(公告)日：2017-02-02
申请号：US15295041
申请日：2016-10-17
申请人： NMC GROUP, INC.
CPC分类号： F16B37/145 , B64C1/403 , B64D29/00 , F16B5/0692 , F16B37/048 , F16B37/14 , Y02T50/46
摘要： A fastener assembly for affixing insulation blankets to a substrate is provided. The fastener assembly includes an attachment member having a construction for affixing to a substrate as well as a first fastener member preferably in the form of a male threaded stud. The fastener assembly further includes a cap fastener. The cap fastener includes a cap member and a second fastener member preferably in the form of a female threaded extension for threadably affixing to the first fastener member. The cap member has an exterior side and an interior side. The cap member's exterior side preferably has a shape for rotation by a tool. Meanwhile, the cap member's interior side has a circular recess concentric with the cap fastener's female threaded extension. When assembled, the circular recess forms a circular insulating cavity between the cap member and an insulation blanket.
摘要翻译： 提供了一种用于将绝缘毯固定到基底的紧固件组件。 紧固件组件包括具有用于固定到基底的构造的附接构件以及优选为阳螺纹的形式的第一紧固构件。 紧固件组件还包括盖紧固件。 盖紧固件包括盖构件和优选为内螺纹延伸部形式的第二紧固构件，用于螺纹地固定到第一紧固构件。 盖构件具有外侧和内侧。 盖构件的外侧优选具有用于通过工具旋转的形状。 同时，盖构件的内侧具有与盖紧固件的内螺纹延伸部同心的圆形凹槽。 当组装时，圆形凹槽在盖构件和绝缘层之间形成圆形绝缘腔。
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69.发明授权Methods and apparatus for supporting engines and nacelles relative to aircraft wings 有权相对于飞机机翼来支持发动机和发动机舱的方法和装置公开(公告)号：US09505499B2
公开(公告)日：2016-11-29
申请号：US14928953
申请日：2015-10-30
申请人： The Boeing Company
发明人： Jack W. Mauldin , David W. Kwok , John A. Weidler , Antonio B. Gonzales , Edward L. Lawson , Andrew C. Kulak
摘要： Methods and apparatus for supporting engines and nacelles relative to aircraft wings are disclosed. An example apparatus includes a nacelle; a first support structure coupled between a wing and a first side of the nacelle along a thrust axis of an engine; a second support structure coupled between the wing and a second side of the nacelle along the thrust axis, the first support structure spaced apart from the second support structure on the wing, a longitudinal plane to extend through the first support structure, the second support structure, and the thrust axis, the first support structure to be rigidly fixed relative to the wing to substantially prevent movement of the engine by the first support structure, the second support structure to be rigidly fixed relative to the wing to substantially prevent movement of the engine by the second support structure, the first and second support structures to be coupled to opposite sides of the engine to enable thrust loads to be reacted through the first and second support structures to the wing.
摘要翻译： 公开了相对于飞机机翼来支撑发动机和机舱的方法和装置。 示例性装置包括机舱; 第一支撑结构，沿着发动机的推力轴联接在所述机舱和所述机舱的第一侧之间; 第二支撑结构，其沿所述推力轴线联接在所述机翼和所述机舱的第二侧之间，所述第一支撑结构与所述机翼上的所述第二支撑结构间隔开，纵向平面延伸穿过所述第一支撑结构，所述第二支撑结构 和所述推力轴线，所述第一支撑结构相对于所述机翼刚性地固定，以基本上防止所述第一支撑结构发动机的运动，所述第二支撑结构相对于所述机翼刚性地固定，以基本上防止所述发动机的运动 通过第二支撑结构，第一和第二支撑结构将联接到发动机的相对侧，以使得推力载荷能够通过第一和第二支撑结构反作用于机翼。
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公开(公告)号：US20160304184A1
公开(公告)日：2016-10-20
申请号：US15100619
申请日：2014-11-25
申请人： SNECMA
CPC分类号： B64C1/1453 , B64D29/00 , F01D25/24 , F01D25/28 , F01D25/32 , F05D2260/602
摘要： A propulsion assembly includes an engine surrounded by a nacelle, a means for draining the fluids from the engine and a means for guiding said fluids to a retention box. The retention box is arranged outside the engine and has a cavity for storing drained fluids. The retention box is fixed to a cowling of the nacelle and supported thereby.
摘要翻译： 推进组件包括由机舱包围的发动机，用于从发动机排出流体的装置和用于将所述流体引导到保持箱的装置。 保持箱布置在发动机外部，并具有用于储存排出的流体的空腔。 保持箱固定在机舱的整流罩上并由此支撑。
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