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公开(公告)号：US20150344140A1
公开(公告)日：2015-12-03
申请号：US14501830
申请日：2014-09-30
Applicant: Airbus Operations (SAS)
Inventor： Francois Peyruseigt , Thierry Gaches , Mathieu Kaleta , Nicolas Voyer
IPC: B64D27/26
Abstract: An aerodynamic fairing whose floor has absolutely no contact with respect to the lateral panels over the entire length of the fairing along the longitudinal axis. A free space e is provided between the floor and the lower edge of each panel. There is a longitudinal mechanical gap between the floor and each of the lateral panels. The absence of any rigid mechanical connection between the floor and the lateral panels allows the transfer of the thermomechanical stresses from the floor to the lateral panels and therefore preventing the deformation of the fairing.
Abstract translation: 一种空气动力学整流罩，其地板在纵向轴线上在整流罩的整个长度上绝对不与侧板接触。 在地板和每个面板的下边缘之间设置一个自由空间e。 在地板和每个侧板之间存在纵向机械间隙。 在地板和侧板之间没有任何刚性的机械连接允许将热机械应力从地板转移到侧板，从而防止整流罩的变形。
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2.发明授权公开(公告)号：US11486335B2
公开(公告)日：2022-11-01
申请号：US17516251
申请日：2021-11-01
Applicant: Airbus Operations SAS
Inventor： Fabien Menou , Laurent Cazeaux , Thierry Gaches
Abstract: A turbofan engine having a duct for a bypass flow and blades. Each blade is mobile between a stowed position and a deployed position. Each blade includes a rigid core a second, free end, and a sheath into which the core and the second end slide. Each sheath includes a first part which surrounds at least one part of the core and the second end, and an aileron which extends beyond the core facing the first part of the adjacent blade. The sheath is made of a flexible material such that the bypass flow causes the sheath to come into contact with the first part of the adjacent blade. A turbofan engine of this kind makes it possible to create blades whose production costs are low but whose aerodynamic behavior is effective.
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Patent Agency Ranking
公开(公告)号：US20150144732A1
公开(公告)日：2015-05-28
申请号：US14501910
申请日：2014-09-30
Applicant: Airbus Operations (SAS)
Inventor： Francois Peyruseigt , Thierry Gaches , Mathieu Kaleta , Nicolas Voyer , Delphine Chamaillard
Abstract: An aerodynamic fairing including at least one sub-assembly, each sub-assembly having a frame which is orientated transversely relative to the longitudinal axis of the fairing and a floor portion which is provided with an inner face, via which the floor portion is fixed to the frame. The fairing further comprises lateral panels which are fixed to the frame and which each extend substantially along the longitudinal axis of the fairing at one side and the other of a plane of symmetry of the fairing. The floor portions of the sub-assemblies are not mechanically connected to each other via rigid connections. The division of the floor into separate portions allows a reduction in the longitudinal thermomechanical stresses applied by the expansion of the floor under the action of the primary hot flow of the turbo reactor.
Abstract translation: 包括至少一个子组件的空气动力整流罩，每个子组件具有相对于整流罩的纵向轴线横向定向的框架和设置有内表面的底板部分，底板部分固定到 框架。 整流罩进一步包括侧板，其固定到框架上，并且每个侧板基本上沿着整流罩的纵向轴线在整流罩的一侧和对称平面的另一侧延伸。 子组件的地板部分不通过刚性连接机械连接。 将地板划分成分离的部分允许在涡轮反应器的主要热流的作用下由地板膨胀施加的纵向热机械应力的减小。
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公开(公告)号：US11047262B2
公开(公告)日：2021-06-29
申请号：US16424650
申请日：2019-05-29
Applicant: Airbus Operations SAS
Inventor： Thierry Gaches , Lionel Czapla , Bastian Sabathier
Abstract: A propulsion system for an aircraft. The propulsion system comprises a core, an internal fixed structure secured to the core and arranged around the core, and a nacelle surrounding the core and the internal fixed structure in which a secondary flow path is delimited between the internal fixed structure and the nacelle. The internal fixed structure has a slot which permits fluidic communication between a compartment on the inside of the internal fixed structure and the secondary flow path.
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公开(公告)号：US09469409B2
公开(公告)日：2016-10-18
申请号：US14501910
申请日：2014-09-30
Applicant: Airbus Operations (SAS)
Inventor： Francois Peyruseigt , Thierry Gaches , Mathieu Kaleta , Nicolas Voyer , Delphine Chamaillard
Abstract: An aerodynamic fairing including at least one sub-assembly, each sub-assembly having a frame which is orientated transversely relative to the longitudinal axis of the fairing and a floor portion which is provided with an inner face, via which the floor portion is fixed to the frame. The fairing further comprises lateral panels which are fixed to the frame and which each extend substantially along the longitudinal axis of the fairing at one side and the other of a plane of symmetry of the fairing. The floor portions of the sub-assemblies are not mechanically connected to each other via rigid connections. The division of the floor into separate portions allows a reduction in the longitudinal thermomechanical stresses applied by the expansion of the floor under the action of the primary hot flow of the turbo reactor.
Abstract translation: 包括至少一个子组件的空气动力整流罩，每个子组件具有相对于整流罩的纵向轴线横向定向的框架和设置有内表面的底板部分，底板部分固定到 框架。 整流罩进一步包括侧板，其固定到框架上，并且每个侧板基本上沿着整流罩的纵向轴线在整流罩的一侧和对称平面的另一侧延伸。 子组件的地板部分不通过刚性连接机械连接。 将地板划分成分离的部分允许在涡轮反应器的主要热流的作用下由地板膨胀施加的纵向热机械应力的减小。
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6.发明授权公开(公告)号：US11473528B2
公开(公告)日：2022-10-18
申请号：US17488725
申请日：2021-09-29
Applicant: Airbus Operations SAS
Inventor： Corentin Vilhes , Simon Vanderbauwede , Thierry Gaches , Laurent Cazeaux , Pascal Gardes , Guillaume Seguin
Abstract: A turbofan having a fixed structure, a fan, a fan casing surrounding the fan, an outer cowl disposed around the fan casing and mounted so as to be articulated on the fixed structure, and a deployment system that moves the outer cowl from a closed position to an open position. The deployment system has a guide rail fastened around the fan casing, a slider that is able to move along the guide rail and has a shoe. An activation system of the deployment system moves the slider and the shoe alternately in one direction or the other along the guide rail. One end of an arm of the deployment system is mounted to be articulated on the shoe and another end is mounted to be articulated on the outer cowl. Such a motorized deployment system makes it possible to save space and mass in the turbofan.
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公开(公告)号：US09688412B2
公开(公告)日：2017-06-27
申请号：US14501830
申请日：2014-09-30
Applicant: Airbus Operations (SAS)
Inventor： Francois Peyruseigt , Thierry Gaches , Mathieu Kaleta , Nicolas Voyer
Abstract: An aerodynamic fairing whose floor has absolutely no contact with respect to the lateral panels over the entire length of the fairing along the longitudinal axis. A free space e is provided between the floor and the lower edge of each panel. There is a longitudinal mechanical gap between the floor and each of the lateral panels. The absence of any rigid mechanical connection between the floor and the lateral panels allows the transfer of the thermomechanical stresses from the floor to the lateral panels and therefore preventing the deformation of the fairing.
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