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1. 发明申请

US20080041062A1 TURBOMACHINE NOZZLE COVER PROVIDED WITH TRIANGULAR PATTERNS HAVING A POINT OF INFLEXION FOR REDUCING JET NOISE 有权
标题翻译：涡轮喷嘴盖提供三角形图案，具有一定程度的减少噪音的噪音
公开(公告)号：US20080041062A1
公开(公告)日：2008-02-21
申请号：US11759678
申请日：2007-06-07
申请人： Dax Au , Pascal Moise Michel Bigot , Pierre Briend , Pierre Philippe Marie Loheac
发明人： Dax Au , Pascal Moise Michel Bigot , Pierre Briend , Pierre Philippe Marie Loheac
IPC分类号： F02K1/00
CPC分类号： F02K1/48 , F02K1/386 , F05D2250/11 , F05D2250/184
摘要： The invention relates to an annular cover for a turbomachine nozzle, the cover having a plurality of patterns extending a trailing edge of said cover and spaced apart circumferentially from one another, each pattern having an outline that is substantially triangular in shape, with a base formed by a portion of the trailing edge of the cover and a vertex spaced downstream from the base and connected thereto by two sides. For each pattern, the vertex presents an outline that is substantially curved; each side is connected to the trailing edge of the cover following an outline that is substantially curved having a radius of curvature that is greater than the radius of curvature of the outline of the vertex; and the outline of each of the sides includes at least one point of inflexion having a tangent that is substantially parallel to the base.
摘要翻译：本发明涉及一种用于涡轮机喷嘴的环形盖，所述盖具有延伸所述盖的后缘并且彼此周向间隔开的多个图案，每个图案具有基本上三角形的轮廓，其形成通过盖的后缘的一部分和与基座间隔开并与两侧相连的顶点。对于每个图案，顶点呈现大致弯曲的轮廓; 每一侧通过基本上弯曲的轮廓连接到盖的后缘，该轮廓的曲率半径大于顶点轮廓的曲率半径; 并且每个侧面的轮廓包括具有基本上平行于基部的切线的拐点的至少一个点。

2. 发明授权

US07854123B2 Turbomachine nozzle cover provided with triangular patterns having pairs of vertices for reducing jet noise 有权
标题翻译：涡轮机喷嘴盖提供三角形图案，具有一对顶点以减少喷气噪声
公开(公告)号：US07854123B2
公开(公告)日：2010-12-21
申请号：US11759719
申请日：2007-06-07
申请人： Dax Au , Pascal Moise Michel Bigot , Pierre Briend , Pierre Philippe Marie Loheac
发明人： Dax Au , Pascal Moise Michel Bigot , Pierre Briend , Pierre Philippe Marie Loheac
IPC分类号： F02K1/00
CPC分类号： F02K1/386 , F05D2250/70 , F05D2260/96
摘要： The pattern relates to a cover for a turbomachine nozzle, the cover having a plurality of patterns each with an outline of triangular shape having a base and two vertices that are spaced downstream and interconnected by a side. For each pattern, the vertices present respective curved outlines and they are interconnected by a curved portion presenting a radius of curvature greater than the radii of curvature of the outlines of said vertices, each side being connected to the trailing edge of the cover via a curved outline presenting a radius of curvature greater than the radii of curvature of the outlines of the vertices and greater than the radius of curvature of the outline of the curved portion, and the vertices and the curved portion are inclined radially towards the inside of the cover, with the curved portion being radially offset outwards relative to the vertices.
摘要翻译：该图案涉及一种用于涡轮机喷嘴的盖，所述盖具有多个图案，每个图案具有三角形轮廓，其具有底部，并且两个顶点间隔下游并由侧面互连。对于每个图案，顶点呈现相应的弯曲轮廓，并且它们通过弯曲部分相互连接，弯曲部分具有大于所述顶点轮廓的曲率半径的曲率半径，每个侧面经由弯曲的轮廓呈现大于顶点轮廓的曲率半径的曲率半径，并且大于曲面部分的轮廓的曲率半径，并且顶点和弯曲部分朝向盖的内侧径向倾斜，其中弯曲部分相对于顶点径向向外偏移。

3. 发明授权

US07581384B2 Turbomachine nozzle cover provided with triangular patterns having a point of inflexion for reducing jet noise 有权
标题翻译：涡轮机喷嘴盖提供三角形图案，具有拐点以减少喷气噪声
公开(公告)号：US07581384B2
公开(公告)日：2009-09-01
申请号：US11759678
申请日：2007-06-07
申请人： Dax Au , Pascal Moise Michel Bigot , Pierre Briend , Pierre Philippe Marie Loheac
发明人： Dax Au , Pascal Moise Michel Bigot , Pierre Briend , Pierre Philippe Marie Loheac
IPC分类号： F02K1/46
CPC分类号： F02K1/48 , F02K1/386 , F05D2250/11 , F05D2250/184
摘要： The invention relates to an annular cover for a turbomachine nozzle, the cover having a plurality of patterns extending a trailing edge of said cover and spaced apart circumferentially from one another, each pattern having an outline that is substantially triangular in shape, with a base formed by a portion of the trailing edge of the cover and a vertex spaced downstream from the base and connected thereto by two sides. For each pattern, the vertex presents an outline that is substantially curved; each side is connected to the trailing edge of the cover following an outline that is substantially curved having a radius of curvature that is greater than the radius of curvature of the outline of the vertex; and the outline of each of the sides includes at least one point of inflexion having a tangent that is substantially parallel to the base.
摘要翻译：本发明涉及一种用于涡轮机喷嘴的环形盖，所述盖具有延伸所述盖的后缘并且彼此周向间隔开的多个图案，每个图案具有基本上三角形的轮廓，其中形成有底部通过盖的后缘的一部分和与基座间隔开并与两侧相连的顶点。对于每个图案，顶点呈现大致弯曲的轮廓; 每一侧通过基本上弯曲的轮廓连接到盖的后缘，该轮廓的曲率半径大于顶点轮廓的曲率半径; 并且每个侧面的轮廓包括具有基本上平行于基部的切线的拐点的至少一个点。

4. 发明申请

US20130032663A1 DEVICE FOR REDUCING NOISE FROM JET-PYLON INTERACTIONS ON JET ENGINES 有权
标题翻译：用于减少喷气发动机上的喷射相互作用的噪声的装置
公开(公告)号：US20130032663A1
公开(公告)日：2013-02-07
申请号：US13581050
申请日：2011-02-25
申请人： Alain Dravet , Jacques Michel Albert Julliard , Pierre Philippe Marie Loheac
发明人： Alain Dravet , Jacques Michel Albert Julliard , Pierre Philippe Marie Loheac
IPC分类号： B64D27/26
CPC分类号： B64C21/02 , B64C7/02 , B64D27/18 , B64D33/06 , Y02T50/166
摘要： An aircraft pylon for mounting a dual-flow or triple-flow jet engine, the pylon including an upper surface for connection to the aircraft, two side flanks, and a flange on the lower portion of the pylon. The pylon further includes at least one portion that extends downstream from the cold flow nozzle of the jet engine and lies in the cold flow and, on the portion thereof extending into the cold flow beyond the nozzle, at least one opening, positioned on one of the flanks of the pylon, by which an air stream is injected into or drawn from the gas flow that flows along the flanks of the pylon.
摘要翻译：一种用于安装双流或三流喷气发动机的飞机塔架，该塔架包括用于连接飞行器的上表面，两个侧翼和在塔架下部的凸缘。塔架还包括至少一部分，其从喷气发动机的冷流喷嘴的下游延伸并且位于冷流中，并且在其延伸到超过喷嘴的冷流中的部分上，至少一个开口位于塔的侧面，通过该侧翼将空气流注入或沿着沿着塔的侧面流动的气流引导。

5. 发明申请

US20080105487A1 CURVED LOBE MIXER FOR A CONVERGING-STREAM NOZZLE FOR A TURBOMACHINE 审中-公开
标题翻译：用于涡轮发动机的弯道喷嘴的弯曲液压混合机
公开(公告)号：US20080105487A1
公开(公告)日：2008-05-08
申请号：US11764454
申请日：2007-06-18
申请人： Pierre Philippe Marie Loheac , Alexandre Alfred Gaston Vuillemin
发明人： Pierre Philippe Marie Loheac , Alexandre Alfred Gaston Vuillemin
IPC分类号： F02K1/46 , F01N1/14 , F02K1/00
CPC分类号： F02K1/48 , F02K1/386
摘要： The invention relates to a mixer for a bypass turbomachine, the mixer comprising a cylindrical member having a sinusoidal portion at its downstream end defining inner lobes and outer lobes distributed circumferentially, each outer lobe comprising a pair of radial walls interconnected by an outer curvilinear dome, each inner lobe comprising a pair of radial walls interconnected by an inner curvilinear dome, the walls of the outer lobes radially extending the walls of the inner lobes, the radial walls of the outer lobes and of the inner lobes presenting an outline that is substantially curved with at least one point of inflection.
摘要翻译：本发明涉及一种用于旁路涡轮机的混合器，该混合器包括圆柱形构件，其圆柱形构件在其下游端具有限定内凸角的正弦部分和沿周向分布的外凸角，每个外凸耳包括通过外曲面圆顶互连的一对径向壁，每个内凸耳包括一对径向壁，其通过内部曲线的圆顶相互连接，所述外部凸角的壁径向延伸所述内部凸角的壁，所述外部凸角和所述内部凸角的径向壁呈现出基本上弯曲的轮廓至少有一个拐点。

6. 发明申请

US20070176052A1 AIR INLET FOR A TURBOFAN ENGINE 有权
标题翻译：涡轮发动机的空气入口
公开(公告)号：US20070176052A1
公开(公告)日：2007-08-02
申请号：US11627638
申请日：2007-01-26
申请人： Philippe Gerard CHANEZ , Pierre Philippe Marie Loheac
发明人： Philippe Gerard CHANEZ , Pierre Philippe Marie Loheac
IPC分类号： B64D33/02
CPC分类号： F02C7/045 , B64D33/02 , B64D2033/0286 , F02K3/06
摘要： The present invention relates to an air inlet for a nacelle of a jet engine with a front fan, comprising an upper part (115S), a lower part (115I), an inner lateral part (115int) and an outer lateral part (ext), defining a leading edge (115) between an external wall (111) of the nacelle and an internal wall (113) forming the air supply channel of the jet engine. According to the invention, the air inlet is characterized in that the leading edge of the outer lateral part (115ext) is to the rear with respect to the leading edge of the inner lateral part (115int).Preferably, the leading edge of the upper part (115S) is likewise to the rear with respect to the leading edge of the lower part (115I).
摘要翻译：本发明涉及一种具有前风扇的喷气发动机的机舱的空气入口，包括上部（115S），下部（115I），内侧横向部分（115int）和外侧部分（ext），限定在所述机舱的外壁（111）和形成所述喷气发动机的空气供应通道的内壁（113）之间的前缘（115）。根据本发明，进气口的特征在于，外侧部分（115 ext）的前缘相对于内侧部分（115 int）的前缘位于后方。优选地，上部（115S）的前缘相对于下部（115I）的前缘同样地向后。

7. 发明授权

US07735776B2 Air inlet for a turbofan engine 有权
标题翻译：涡扇发动机的进气口
公开(公告)号：US07735776B2
公开(公告)日：2010-06-15
申请号：US11627638
申请日：2007-01-26
申请人： Philippe Gerard Chanez , Pierre Philippe Marie Loheac
发明人： Philippe Gerard Chanez , Pierre Philippe Marie Loheac
IPC分类号： B64D33/02
CPC分类号： F02C7/045 , B64D33/02 , B64D2033/0286 , F02K3/06
摘要： The present invention relates to an air inlet for a nacelle of a jet engine with a front fan, comprising an upper part (115S), a lower part (115I), an inner lateral part (115int) and an outer lateral part (ext), defining a leading edge (115) between an external wall (111) of the nacelle and an internal wall (113) forming the air supply channel of the jet engine. According to the invention, the air inlet is characterized in that the leading edge of the outer lateral part (115ext) is to the rear with respect to the leading edge of the inner lateral part (115int).Preferably, the leading edge of the upper part (115S) is likewise to the rear with respect to the leading edge of the lower part (115I).
摘要翻译：本发明涉及一种具有前风扇的喷气发动机机舱的空气入口，包括上部分（115S），下部分（115I），内侧部分（115int）和外侧部分（ext），在所述机舱的外壁（111）和形成所述喷气发动机的空气供应通道的内壁（113）之间限定前缘（115）。根据本发明，进气口的特征在于，外侧部分（115ext）的前缘相对于内侧部分（115int）的前缘位于后方。优选地，上部（115S）的前缘相对于下部（115I）的前缘同样向后。

8. 发明授权

US08991749B2 Device for reducing noise from jet-pylon interactions on jet engines 有权
标题翻译：用于减少喷气发动机上喷气塔相互作用的噪音的装置
公开(公告)号：US08991749B2
公开(公告)日：2015-03-31
申请号：US13581050
申请日：2011-02-25
申请人： Alain Dravet , Jacques Michel Albert Julliard , Pierre Philippe Marie Loheac
发明人： Alain Dravet , Jacques Michel Albert Julliard , Pierre Philippe Marie Loheac
IPC分类号： B64B1/24 , B64C21/02 , B64C7/02 , B64D27/18 , F02K1/34
CPC分类号： B64C21/02 , B64C7/02 , B64D27/18 , B64D33/06 , Y02T50/166
摘要： An aircraft pylon for mounting a dual-flow or triple-flow jet engine, the pylon including an upper surface for connection to the aircraft, two side flanks, and a flange on the lower portion of the pylon. The pylon further includes at least one portion that extends downstream from the cold flow nozzle of the jet engine and lies in the cold flow and, on the portion thereof extending into the cold flow beyond the nozzle, at least one opening, positioned on one of the flanks of the pylon, by which an air stream is injected into or drawn from the gas flow that flows along the flanks of the pylon.
摘要翻译：一种用于安装双流或三流喷气发动机的飞机塔架，该塔架包括用于连接飞行器的上表面，两个侧翼和在塔架下部的凸缘。塔架还包括至少一部分，其从喷气发动机的冷流喷嘴的下游延伸并且位于冷流中，并且在其延伸到超过喷嘴的冷流中的部分上，至少一个开口位于塔的侧面，通过该侧翼将空气流注入或沿着沿着塔的侧面流动的气流引导。

9. 发明申请

US20090084111A1 TURBOMACHINE NOZZLE COWL HAVING JET NOISE REDUCTION PATTERNS 审中-公开
标题翻译：涡轮喷嘴具有喷射噪声减少模式
公开(公告)号：US20090084111A1
公开(公告)日：2009-04-02
申请号：US12210533
申请日：2008-09-15
申请人： Sebastien Jean-Paul AEBERLI , Pierre Philippe Marie Loheac , Stephane Jacques Francois Thomas , Alexandre Alfred Gaston Vuillemin , Kamel Zeggai
发明人： Sebastien Jean-Paul AEBERLI , Pierre Philippe Marie Loheac , Stephane Jacques Francois Thomas , Alexandre Alfred Gaston Vuillemin , Kamel Zeggai
IPC分类号： F02K1/44 , F01N1/08 , F01N1/14
CPC分类号： F02K1/386 , F02K1/48 , F02K3/06 , F05D2250/16
摘要： The invention relates to a cowl for a turbomachine nozzle, the cowl including a plurality of repetitive patterns disposed to extend a trailing edge of said cowl and spaced circumferentially apart from one another. Each pattern is in the form of a quadrilateral having a base that is formed by a portion of the trailing edge of the cowl and two vertices that are spaced downstream from the base and that are connected thereto via two sides, each side having the shape of a parabola. Each pattern is asymmetrical relative to a midplane of the pattern containing a longitudinal axis of said cowl, and it comprises a first portion inclined radially towards the inside of the cowl, and a second portion inclined radially towards the outside of the cowl.
摘要翻译：本发明涉及一种用于涡轮机喷嘴的整流罩，整流罩包括多个重复图案，其设置成延伸所述整流罩的后缘并且彼此周向地间隔开。每个图案是四边形的形式，其具有由整流罩的后缘的一部分形成的基部和两个顶点，该顶点与底座间隔开并且经由两侧与其连接，每个侧面的形状为抛物线每个图案相对于包含所述整流罩的纵向轴线的图案的中平面是不对称的，并且其包括朝向罩的内部径向倾斜的第一部分和朝向罩的外部径向倾斜的第二部分。

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