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公开(公告)号：US10113506B2
公开(公告)日：2018-10-30
申请号：US14881886
申请日：2015-10-13
Applicant: AIRCELLE
Inventor： Hélène Malot , Jean-Pierre Guegou , Philippe Bienvenu , Philippe Prunin
Abstract: The present disclosure provides a nozzle for an aircraft turboprop engine with an unducted fan, including: an inner wall, an outer wall radially spaced apart from the inner wall and concentric with the inner wall, a junction area of the inner and outer walls including an opening contained in a plane transverse to a longitudinal axis of the nozzle. In particular, the junction area of the inner and outer walls includes two connecting plates and a member to secure the two connecting plates together, or in another form, the junction area includes a pad secured to the inner wall, and a pad secured to the outer wall, facing the pad of the inner wall of the nozzle.
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公开(公告)号：US09789556B2
公开(公告)日：2017-10-17
申请号：US14883994
申请日：2015-10-15
Applicant: AIRCELLE
Inventor： Philippe Bienvenu , Helene Malot , Francisco Caneque
IPC: B23K31/02 , B23K3/08 , B21D26/033 , B23K1/008 , F02K1/82 , F02K1/80 , B23K1/00 , B23K101/00
CPC classification number: B23K3/087 , B21D26/033 , B23K1/0014 , B23K1/0018 , B23K1/008 , B23K2101/001 , F02K1/80 , F02K1/827 , F05D2230/23 , F05D2230/237 , F05D2250/283 , F05D2300/502
Abstract: A method for assembling a set including an inner wall, a shrouded outer wall and an intermediate element, each presenting substantially circular sections, the shrouded outer wall presenting a shape substantially complementary to a shape of outer and inner surfaces of the intermediate element, and whose inner surface covers the outer surface of the intermediate element. In particular, the method includes a step of placing a brazing sheet, whose melting temperature is lower than melting temperatures of other elements of the set, over an assembly surface in contact with another assembly surface, and a step of heating, by a furnace, a set including the outer or inner walls and the intermediate element between which is interposed a brazing sheet so as to fix the outer or inner wall by brazing on the intermediate element.
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Patent Agency Ranking
公开(公告)号：US20160032863A1
公开(公告)日：2016-02-04
申请号：US14881886
申请日：2015-10-13
Applicant: AIRCELLE
Inventor： Hélène MALOT , Jean-Pierre Guegou , Philippe Bienvenu , Philippe Prunin
CPC classification number: F02K1/28 , F01D25/24 , F02C3/067 , F02K1/822 , F02K3/06 , F02K3/072 , Y02T50/671 , Y02T50/675
Abstract: The present disclosure provides a nozzle for an aircraft turboprop engine with an unducted fan, including: an inner wall, an outer wall radially spaced apart from the inner wall and concentric with the inner wall, a junction area of the inner and outer walls including an opening contained in a plane transverse to a longitudinal axis of the nozzle. In particular, the junction area of the inner and outer walls includes two connecting plates and a member to secure the two connecting plates together, or in another form, the junction area includes a pad secured to the inner wall, and a pad secured to the outer wall, facing the pad of the inner wall of the nozzle.
Abstract translation: 本公开提供了一种用于具有未引导风扇的飞机涡轮螺旋桨发动机的喷嘴，包括：内壁，与内壁径向间隔开并与内壁同心的外壁，内壁和外壁的接合面积包括 开口包含在横向于喷嘴的纵向轴线的平面中。 特别地，内壁和外壁的接合区域包括两个连接板和用于将两个连接板固定在一起的构件，或者以另一种形式，连接区域包括固定到内壁的垫，以及固定到 外壁，面向喷嘴内壁的垫。
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公开(公告)号：US09051899B2
公开(公告)日：2015-06-09
申请号：US14177494
申请日：2014-02-11
Applicant: AIRCELLE
Inventor： Helene Malot , Philippe Bienvenu
IPC: G10K11/172 , F02K1/82 , F02K1/04 , F02K1/44 , F02K1/80
CPC classification number: F02K1/827 , F02K1/04 , F02K1/44 , F02K1/80 , F05D2230/232 , F05D2250/283 , F05D2260/30 , Y02T50/671
Abstract: An exhaust cone for an aircraft turbojet engine includes a front part which has a front end and a rear end. The front end is equipped with a front connecting flange connecting to an outlet of a turbojet engine and the rear end is equipped with a rear connecting flange connecting to a rear part of the exhaust cone. In particular, the front part is further equipped with a sound attenuation structure including an outer skin, and the outer skin overlaps the front connecting flange and the rear connecting flange.
Abstract translation: 用于飞机涡轮喷气发动机的排气锥体包括具有前端和后端的前部。 前端配备有连接到涡轮喷气发动机的出口的前连接凸缘，并且后端配备有连接到排气锥的后部的后连接凸缘。 特别地，前部还配备有包括外皮的声音衰减结构，并且外表皮与前连接凸缘和后连接凸缘重叠。
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公开(公告)号：US20140299654A1
公开(公告)日：2014-10-09
申请号：US14274926
申请日：2014-05-12
Applicant: AIRCELLE , SNECMA PROPULSION SOLIDE
Inventor： Hélène MALOT , Philippe Bienvenu , Frédéric Guichard , Olivier Drevet
CPC classification number: B23K31/02 , B23K1/0014 , B23K3/087 , B23K37/00 , B23K2101/02
Abstract: A setup for assembling, by brazing, a composite panel including at least two parts separated by a filler material and joined together by brazing. The setup includes a furnace to achieve a brazing temperature for brazing the panel, and an assembly device which has a form having a shape similar to the final shape of the panel to be brazed. In particular, the assembly device further includes a pressing device to apply mechanical pressure to at least part of the surface of the panel in a direction allowing the panel to be permanently deformed into a shape which matches that of the form. The pressing device is moved under the action of a spring, and the forces applied by the spring being determined so that, at the brazing temperature, the spring applies the force necessary for deforming the panel against the form.
Abstract translation: 一种用于通过钎焊组装复合板的装置，所述复合板包括由填充材料分隔开并通过钎焊连接在一起的至少两个部分。 该装置包括实现钎焊板的钎焊温度的炉，以及具有与要钎焊的板的最终形状类似的形状的组装装置。 特别地，组装装置还包括一个加压装置，以在允许面板永久变形成与形状相匹配的形状的方向上对面板的至少部分表面施加机械压力。 挤压装置在弹簧的作用下移动，并且由弹簧施加的力被确定为使得在钎焊温度下弹簧施加使面板变形成形成所需的力。
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公开(公告)号：US09486870B2
公开(公告)日：2016-11-08
申请号：US14609726
申请日：2015-01-30
Applicant: AIRCELLE
Inventor： Philippe Bienvenu , Jean-Claude Rivoal , Flavien Poulet , Francisco Caneque
CPC classification number: B23K1/0018 , B23K1/0008 , B23K1/008 , B23K1/20 , B23K3/087 , F01D25/005
Abstract: A manufacturing method for a metal part uses a tooling assembly. The tooling assembly includes a counter-form and a deformable core which includes inner and outer skins, a honeycomb structure positioned between the inner and outer skins, and a brazing material interposed between the honeycomb structure and the inner and outer skins. In particular, the core is closed by a lid equipped with ducts through which a gas is introduced. The manufacturing method includes the following steps: positioning the tooling assembly in a vacuum furnace; introducing a pressurized gas directly inside an inner skin of the core of the tooling assembly; purging the pressurized gas from an inner portion of the inner skin of the tooling assembly; and dismounting the tooling assembly so as to extract a metal part manufactured.
Abstract translation: 金属部件的制造方法使用工具组件。 该工具组件包括一个对置形式和一个可变形的芯，其包括内表皮和外表皮，位于内表皮和外表皮之间的蜂窝结构以及置于蜂窝结构与内表皮和外表皮之间的钎焊材料。 特别地，芯体由装有管道的盖子封闭，导管通过导管引入气体。 该制造方法包括以下步骤：将加工组件定位在真空炉中; 将加压气体直接引入到工具组件的芯的内表皮内; 从加工组件的内表皮的内部清洗加压气体; 并拆卸模具组件以便提取制造的金属部件。
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公开(公告)号：US20140158458A1
公开(公告)日：2014-06-12
申请号：US14177494
申请日：2014-02-11
Applicant: AIRCELLE
Inventor： Helene Malot , Philippe Bienvenu
IPC: F02K1/82
CPC classification number: F02K1/827 , F02K1/04 , F02K1/44 , F02K1/80 , F05D2230/232 , F05D2250/283 , F05D2260/30 , Y02T50/671
Abstract: An exhaust cone for an aircraft turbojet engine includes a front part which has a front end and a rear end. The front end is equipped with a front connecting flange connecting to an outlet of a turbojet engine and the rear end is equipped with a rear connecting flange connecting to a rear part of the exhaust cone. In particular, the front part is further equipped with a sound attenuation structure including an outer skin, and the outer skin overlaps the front connecting flange and the rear connecting flange.
Abstract translation: 用于飞机涡轮喷气发动机的排气锥体包括具有前端和后端的前部。 前端配备有连接到涡轮喷气发动机的出口的前连接凸缘，并且后端配备有连接到排气锥的后部的后连接凸缘。 特别地，前部还配备有包括外皮的声音衰减结构，并且外表皮与前连接凸缘和后连接凸缘重叠。
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