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公开(公告)号：US09233757B2
公开(公告)日：2016-01-12
申请号：US13294090
申请日：2011-11-10
申请人： Norman John James , Alan Binks , Michael J Layland
发明人： Norman John James , Alan Binks , Michael J Layland
CPC分类号： B64D29/00 , B64D27/00 , B64D29/06 , B64D29/08 , Y10T137/0536
摘要： A nacelle is configured to be coupled to an underside of a wing so as to form a clearance space therebetween. The nacelle includes at least a first cowling which at least partially defines an inlet of the nacelle and which at least partially defines an outlet of the nacelle. The first cowling can include a unitary portion that extends continuously from the inlet to the outlet. The first cowling can also include a flattened surface.
摘要翻译： 机舱被配置为联接到翼的下侧，以便在它们之间形成间隙空间。 所述机舱至少包括第一整流罩，其至少部分地限定所述机舱的入口并且至少部分地限定所述机舱的出口。 第一个整流罩可以包括从入口到出口连续延伸的整体部分。 第一个整流罩也可以包括一个扁平的表面。
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公开(公告)号：US20130118599A1
公开(公告)日：2013-05-16
申请号：US13294090
申请日：2011-11-10
CPC分类号： B64D29/00 , B64D27/00 , B64D29/06 , B64D29/08 , Y10T137/0536
摘要： A nacelle is configured to be coupled to an underside of a wing so as to form a clearance space therebetween. The nacelle includes at least a first cowling which at least partially defines an inlet of the nacelle and which at least partially defines an outlet of the nacelle. The first cowling can include a unitary portion that extends continuously from the inlet to the outlet. The first cowling can also include a flattened surface.
摘要翻译： 机舱被配置为联接到翼的下侧，以便在它们之间形成间隙空间。 所述机舱至少包括第一整流罩，其至少部分地限定所述机舱的入口并且至少部分地限定所述机舱的出口。 第一个整流罩可以包括从入口到出口连续延伸的整体部分。 第一个整流罩也可以包括一个扁平的表面。
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公开(公告)号：US20100260602A1
公开(公告)日：2010-10-14
申请号：US12423550
申请日：2009-04-14
IPC分类号： F01D25/24
CPC分类号： B64D29/06 , B64D29/08 , B64D33/02 , B64D2033/0206 , Y02B10/30 , Y02E10/726 , Y10T137/0536
摘要： A nacelle inlet for an aircraft engine of a type having an engine fan case with a forward flange includes an acoustic inner barrel having a forward edge and an aft edge, an outer shell having a nose lip portion with a trailing inner edge, and an outer barrel portion having an aft portion. The nacelle inlet also includes an aft attachment flange configured to attach the inlet to the forward flange of the engine fan case, and an aft bulkhead having an aft end and connecting the outer barrel portion of the outer shell to the aft attachment flange. The forward edge of the acoustic inner barrel is connected to the trailing inner edge of the nose lip portion, and the aft portion of the inner barrel is attached to the aft attachment flange.
摘要翻译： 用于具有具有前凸缘的发动机风扇壳的类型的飞机发动机的机舱入口包括具有前边缘和后边缘的声学内筒，具有带有后缘内边缘的鼻唇部分的外壳 筒部具有后部。 机舱入口还包括后部附件凸缘，其构造成将入口附接到发动机风扇壳体的前凸缘，以及具有后端并且将外壳的外筒部分连接到后附件凸缘的后舱壁。 声学内筒的前缘连接到鼻唇部的后缘，并且内筒的后部附接到后附件凸缘。
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公开(公告)号：US08267642B2
公开(公告)日：2012-09-18
申请号：US13091615
申请日：2011-04-21
CPC分类号： B64D29/06 , B64D29/08 , B64D33/02 , B64D2033/0206 , Y02B10/30 , Y02E10/726 , Y10T137/0536
摘要： A nacelle inlet for an aircraft engine of a type having an engine fan case with a forward flange includes an acoustic inner barrel having a forward edge and an aft edge, an outer shell having a nose lip portion with a trailing inner edge, and an outer barrel portion having an aft portion. The nacelle inlet also includes an aft attachment flange configured to attach the inlet to the forward flange of the engine fan case, and an aft bulkhead having an aft end and connecting the outer barrel portion of the outer shell to the aft attachment flange. The forward edge of the acoustic inner barrel is connected to the trailing inner edge of the nose lip portion, and the aft portion of the inner barrel is attached to the aft attachment flange.
摘要翻译： 用于具有具有前凸缘的发动机风扇壳的类型的飞机发动机的机舱入口包括具有前边缘和后边缘的声学内筒，具有带有后缘内边缘的鼻唇部分的外壳 筒部具有后部。 机舱入口还包括后部附件凸缘，其构造成将入口附接到发动机风扇壳体的前凸缘，以及具有后端并且将外壳的外筒部分连接到后附件凸缘的后舱壁。 声学内筒的前缘连接到鼻唇部的后缘，并且内筒的后部附接到后附件凸缘。
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公开(公告)号：US20110197973A1
公开(公告)日：2011-08-18
申请号：US13091615
申请日：2011-04-21
IPC分类号： F02K99/00
CPC分类号： B64D29/06 , B64D29/08 , B64D33/02 , B64D2033/0206 , Y02B10/30 , Y02E10/726 , Y10T137/0536
摘要： A nacelle inlet for an aircraft engine of a type having an engine fan case with a forward flange includes an acoustic inner barrel having a forward edge and an aft edge, an outer shell having a nose lip portion with a trailing inner edge, and an outer barrel portion having an aft portion. The nacelle inlet also includes an aft attachment flange configured to attach the inlet to the forward flange of the engine fan case, and an aft bulkhead having an aft end and connecting the outer barrel portion of the outer shell to the aft attachment flange. The forward edge of the acoustic inner barrel is connected to the trailing inner edge of the nose lip portion, and the aft portion of the inner barrel is attached to the aft attachment flange.
摘要翻译： 用于具有具有前凸缘的发动机风扇壳的类型的飞机发动机的机舱入口包括具有前边缘和后边缘的声学内筒，具有带有后缘内边缘的鼻唇部分的外壳 筒部具有后部。 机舱入口还包括后部附件凸缘，其构造成将入口附接到发动机风扇壳体的前凸缘，以及具有后端并且将外壳的外筒部分连接到后附件凸缘的后舱壁。 声学内筒的前缘连接到鼻唇部的后缘，并且内筒的后部附接到后附件凸缘。
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公开(公告)号：US09403599B2
公开(公告)日：2016-08-02
申请号：US13595896
申请日：2012-08-27
CPC分类号： B64D29/06 , B64D29/08 , B64D33/02 , B64D2033/0206 , Y02B10/30 , Y02E10/726 , Y10T137/0536
摘要： A nacelle inlet for an aircraft engine of a type having an engine fan case with a forward flange includes an acoustic inner barrel having a forward edge and an aft edge, an outer shell having a nose lip portion with a trailing inner edge, and an outer barrel portion having an aft portion. The nacelle inlet also includes an aft attachment flange configured to attach the inlet to the forward flange of the engine fan case, and an aft bulkhead having an aft end and connecting the outer barrel portion of the outer shell to the aft attachment flange. The forward edge of the acoustic inner barrel is connected to the trailing inner edge of the nose lip portion, and the aft portion of the inner barrel is attached to the aft attachment flange.
摘要翻译： 用于具有具有前凸缘的发动机风扇壳的类型的飞机发动机的机舱入口包括具有前边缘和后边缘的声学内筒，具有带有后缘内边缘的鼻唇部分的外壳 筒部具有后部。 机舱入口还包括后部附件凸缘，其构造成将入口附接到发动机风扇壳体的前凸缘，以及具有后端并将外壳的外筒部分连接到后附件凸缘的后舱壁。 声学内筒的前缘连接到鼻唇部的后缘，并且内筒的后部附接到后附件凸缘。
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公开(公告)号：US08197191B2
公开(公告)日：2012-06-12
申请号：US12423550
申请日：2009-04-14
CPC分类号： B64D29/06 , B64D29/08 , B64D33/02 , B64D2033/0206 , Y02B10/30 , Y02E10/726 , Y10T137/0536
摘要： A nacelle inlet for an aircraft engine of a type having an engine fan case with a forward flange includes an acoustic inner barrel having a forward edge and an aft edge, an outer shell having a nose lip portion with a trailing inner edge, and an outer barrel portion having an aft portion. The nacelle inlet also includes an aft attachment flange configured to attach the inlet to the forward flange of the engine fan case, and an aft bulkhead having an aft end and connecting the outer barrel portion of the outer shell to the aft attachment flange. The forward edge of the acoustic inner barrel is connected to the trailing inner edge of the nose lip portion, and the aft portion of the inner barrel is attached to the aft attachment flange.
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8.发明授权公开(公告)号：US08402765B2
公开(公告)日：2013-03-26
申请号：US12485551
申请日：2009-06-16
CPC分类号： F02K1/763 , F02K1/09 , F02K1/30 , F02K1/70 , F02K1/72 , F02K3/06 , F05D2250/34 , Y10T74/18576 , Y10T74/18648
摘要： A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating nozzle segment having a forward edge and a first end. The nozzle segment is movably disposed behind the aft edge such that an upstream bypass flow exit is defined between the aft edge and the forward edge when the nozzle segment is in a deployed position. A deflector is disposed between the aft edge and the forward edge proximate to the first end. The deflector substantially prevents bypass flow from exiting the upstream bypass flow exit in a region that is proximate to the first end.
摘要翻译： 用于涡轮风扇发动机的可变区域风扇喷嘴组件包括具有后边缘的机舱和具有前边缘和第一端的平移喷嘴段。 喷嘴段可移动地设置在后边缘之后，使得当喷嘴段处于展开位置时，在后边缘和前边缘之间限定上游旁路流出口。 偏转器设置在靠近第一端的后边缘和前边缘之间。 偏转器基本上防止在接近第一端的区域中旁路流离开上游旁路流出口。
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公开(公告)号：US09371138B2
公开(公告)日：2016-06-21
申请号：US13491472
申请日：2012-06-07
申请人： Norman John James
发明人： Norman John James
IPC分类号： B64D29/02
CPC分类号： B64D29/02
摘要： A nacelle configured to be coupled to an underside of a wing so as to form a clearance space therebetween includes at least a lip defining an inlet and a first cowling disposed aft of the lip. The first cowling has an outer surface with at least one concave region that is depressed relative to another region of the outer surface. In some aspects, the depressed region can be disposed on an inboard side of the wing, for example, on an upper surface of the first cowling facing a wing. The nacelle can include a second cowling disposed between the lip and the first cowling and the first cowling can translate in a longitudinal direction relative to the second cowling.
摘要翻译： 构造成联接到机翼的下侧以便在其间形成间隙空间的机舱包括限定入口的至少一个唇缘和设置在唇部后面的第一整流罩。 第一整流罩具有外表面，其具有相对于外表面的另一区域凹陷的至少一个凹区域。 在一些方面，凹陷区域可以设置在机翼的内侧，例如在面向机翼的第一整流罩的上表面上。 机舱可以包括设置在唇缘和第一整流罩之间的第二整流罩，并且第一整流罩可以相对于第二整流罩在纵向方向上平移。
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公开(公告)号：US20130220435A1
公开(公告)日：2013-08-29
申请号：US13404982
申请日：2012-02-24
申请人： Norman John James
发明人： Norman John James
IPC分类号： F02K99/00
CPC分类号： B64D29/08 , B64D27/12 , B64D27/26 , B64D29/00 , B64D29/06 , B64D2027/262 , F02K1/30 , F02K1/32 , F23R3/60 , Y10T137/0536
摘要： A nacelle includes at least a first cowling which at least partially defines an inlet of the nacelle and which at least partially defines an outlet of the nacelle. The first cowling can include a unitary portion that extends continuously from the inlet to the outlet. The nacelle also includes a second cowling that at least partially defines the inlet and which translates relative to the first cowling. The nacelle can include a third cowling that at least partially defines the outlet and translates relative to the first cowling.
摘要翻译： 机舱至少包括第一整流罩，其至少部分地限定所述机舱的入口并且至少部分地限定所述机舱的出口。 第一个整流罩可以包括从入口到出口连续延伸的整体部分。 机舱还包括至少部分限定入口并相对于第一整流罩平移的第二整流罩。 机舱可以包括至少部分地限定出口并相对于第一整流罩平移的第三整流罩。
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