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1. 发明申请

US20170096963A1 SANDWICH STRUCTURE HAVING HINGE ASSEMBLIES FOR ACCOMMODATING DIFFERENTIAL IN-PLANE EXPANSION OF FACE SHEETS 审中-公开
公开(公告)号：US20170096963A1
公开(公告)日：2017-04-06
申请号：US15382603
申请日：2016-12-17
申请人： The Boeing Company
发明人： Robert E. Grip , John J. Brown
IPC分类号： F02K1/80 , B64D29/00 , F02K1/82 , B64C1/12
CPC分类号： F02K1/80 , B64C1/12 , B64D27/26 , B64D29/00 , B64D29/06 , F01D25/26 , F01D25/30 , F02K1/82 , F02K1/822 , F04D29/441 , F05D2220/323 , F05D2250/40 , F05D2260/50 , Y02T50/672 , Y10T29/49229 , Y10T428/249923
摘要： A sandwich structure includes a first skin and a second skin spaced apart from each other and interconnected by a hinge assembly including a first hinge member and a second hinge member. The first hinge member proximal end is coupled to the first skin. The second hinge member proximal end is coupled to the second skin. The first hinge member distal end is coupled to the second member distal end at a member joint. The hinge assembly: prevents movement of the first skin relative to the second skin in an in-plane longitudinal direction of the first skin, allows movement of the first skin relative to the second skin in an in-plane transverse direction of the first skin, and allows movement of the first skin relative to the second skin in an out-of-plane direction that is normal to the in-plane longitudinal direction and the in-plane transverse direction.

2. 发明授权

US08757969B2 Turbine exhaust plenum 有权
标题翻译：涡轮排风室
公开(公告)号：US08757969B2
公开(公告)日：2014-06-24
申请号：US12883158
申请日：2010-09-15
申请人： Rohit Pruthi , Deepesh D. Nanda
发明人： Rohit Pruthi , Deepesh D. Nanda
IPC分类号： F01D25/24 , F01D25/30
CPC分类号： F01D25/30 , F01D9/065 , F05D2250/20 , F05D2250/40 , F05D2250/70
摘要： In accordance with one embodiment, a system includes a turbine engine including an axial-radial diffuser section disposed about a first longitudinal axis downstream in an exhaust flow path from a turbine section. The system also includes an exhaust plenum including a first plenum portion disposed about the axial-radial diffuser section, wherein the first plenum portion includes a curved wall portion that diverges away from a circumference of the axial-radial diffuser section. The exhaust plenum also includes a second plenum portion extending away from the first plenum portion downstream along a second longitudinal axis of the exhaust plenum approximately crosswise to the first longitudinal axis.
摘要翻译：根据一个实施例，系统包括涡轮发动机，该涡轮发动机包括轴向 - 径向扩散器部分，该轴向 - 径向扩散器部分围绕涡轮部分的排气流动路径中的第一纵向轴线设置在下游。该系统还包括排气室，其包括围绕轴向 - 径向扩散器部分设置的第一增压室部分，其中第一增压室部分包括远离轴向 - 径向扩散器部分的圆周分开的弯曲壁部分。排气室还包括第二增压室部分，该第二增压室部分沿排气室的第二纵向轴线远离第一集气室部分向下延伸，大致与第一纵向轴线交叉。

3. 发明申请

US20090290983A1 TURBINE BLADE ASSEMBLY AND STEAM TURBINE 有权
标题翻译：涡轮叶片组件和蒸汽涡轮机
公开(公告)号：US20090290983A1
公开(公告)日：2009-11-26
申请号：US12470264
申请日：2009-05-21
申请人： Osamu TANAKA
发明人： Osamu TANAKA
IPC分类号： F01D5/22 , F01D5/32
CPC分类号： F01D5/326 , F01D5/225 , F05D2220/31 , F05D2250/40 , F05D2260/50
摘要： A turbine blade 10a which is a stop blade is provided with a cutout portion 50 which is formed in one circumferential side surface 22a of a shank portion 22 at the center in the axial direction of a turbine rotor 100, a cutout portion 60 which is formed in one circumferential side surface 22a of the shank portion 22 from one end portion 22b to the cutout portion 50 in the axial direction of the turbine rotor 100, and a through passage 70 which is formed to pass from the cutout portion 50 to an effective blade part and in which a moving member 170, which moves a stopper member 160 to the effective blade part in the cutout portion 50, is inserted.
摘要翻译：作为止动叶片的涡轮叶片10a设置有切口部分50，该切口部分形成在涡轮转子100的轴向中心处的柄部分22的一个周向侧表面22a中，形成有切口部分60 在轴部22的一个圆周侧表面22a中，从涡轮转子100的轴向的一个端部22b到切口部50，以及形成为从切口部50通过有效刀片的贯通通道70 将止动构件160移动到切口部50中的有效叶片部的移动构件170插入其中。

4. 发明申请

US20080131276A1 Thermally decoupled mixer 有权
标题翻译：热解耦混频器
公开(公告)号：US20080131276A1
公开(公告)日：2008-06-05
申请号：US11606833
申请日：2006-11-30
申请人： Adeyemi E. Alade , Paul W. Palmer
发明人： Adeyemi E. Alade , Paul W. Palmer
IPC分类号： F01D1/02
CPC分类号： F02K1/48 , F02K1/38 , F05B2260/301 , F05D2250/40
摘要： The present invention provides a mixer assembly including a mixer and a plurality of scoops attached around a circumference of the mixer element via a combination of sliding brackets and fixed brackets. The sliding brackets provide attachment and allow relative movement between the plurality of scoops and the mixer element while the fixed brackets provide only attachment between the mixer element and the plurality of scoops. The first sliding bracket includes a first flange that is fixedly mounted to the mixer element and a second flange that is biased against a surface of the scoop. A second sliding bracket is fixedly mounted to the mixer element and adjustably mounted to the scoop. The second sliding bracket includes an attachment hole and the scoop includes an adjustment slot. A fastener assembly including a spacer is received within the adjustment hole and the adjustment slot to allow relative movement between the mixer element and the scoop.
摘要翻译：本发明提供了一种混合器组件，其包括混合器和通过滑动支架和固定支架的组合在混合器元件的圆周周围附接的多个铲斗。滑动支架提供附接并且允许多个铲斗和混合器元件之间的相对移动，而固定支架仅提供混合器元件和多个勺子之间的附接。第一滑动支架包括固定地安装到混合器元件的第一凸缘和抵靠勺表面偏压的第二凸缘。第二滑动支架固定地安装到混合器元件上并可调节地安装到勺子上。第二滑动支架包括附接孔，勺包括调节槽。包括间隔件的紧固件组件被容纳在调节孔和调节槽内，以允许混合器元件和铲斗之间的相对移动。

5. 发明申请

US20080063513A1 Turbine blade tip gap reduction system for a turbine engine 审中-公开
标题翻译：涡轮发动机的涡轮叶片尖端间隙减小系统
公开(公告)号：US20080063513A1
公开(公告)日：2008-03-13
申请号：US11518018
申请日：2006-09-08
申请人： Gennadiy Afanasiev
发明人： Gennadiy Afanasiev
IPC分类号： F01D25/26
CPC分类号： F01D11/22 , F05D2240/11 , F05D2250/40
摘要： A turbine blade gap control system configured to move a vane carrier and attached ring segments of a turbine engine axially relative to a turbine blade assembly to reduce the gaps between the tips of the turbine blades and the ring segments to increase the efficiency of the turbine engine once operating in a steady state condition. The turbine blade assembly may be formed from a plurality rows of turbine blades extending radially from a rotor, wherein each row may be formed from a plurality of turbine blades and wherein the turbine blades may have tips positioned at an acute angle relative to a rotational axis of the turbine blade assembly. A vane carrier may be positioned concentric with the rotor and positioned radially outward from the turbine blades, and a plurality of ring segments may be attached to the vane carrier.
摘要翻译：一种涡轮机叶片间隙控制系统，被配置为相对于涡轮机叶片组件轴向地移动涡轮机的叶片载体和附接的环段，以减小涡轮叶片和环段之间的间隙，以提高涡轮发动机的效率一旦在稳态条件下工作。涡轮叶片组件可以由从转子径向延伸的多排涡轮机叶片形成，其中每排可以由多个涡轮叶片形成，并且其中涡轮机叶片可具有相对于旋转轴线成锐角的尖端的涡轮叶片组件。叶片载体可以与转子同轴地定位并且从涡轮叶片径向向外定位，并且多个环形段可以附接到叶片载体。

6. 发明授权

US09695822B2 Adjustable core turbocharger 有权
公开(公告)号：US09695822B2
公开(公告)日：2017-07-04
申请号：US14489300
申请日：2014-09-17
申请人： Ford Global Technologies, LLC
发明人： James Douglas Ervin , August Thomas Vaught
IPC分类号： F01D7/00 , F04C28/18 , F01D11/08 , F04D15/00 , F04D27/00 , F01D11/22 , F04D25/04 , F04D25/02 , F01D17/14 , F01D25/24 , F02B37/02 , F02B37/22 , F02B39/14 , F02B47/08 , F04C18/02
CPC分类号： F04C28/185 , F01D11/08 , F01D11/22 , F01D17/141 , F01D17/143 , F01D25/24 , F02B37/025 , F02B37/22 , F02B39/14 , F02B47/08 , F04C18/02 , F04D15/0033 , F04D25/024 , F04D25/045 , F04D27/002 , F04D27/0246 , F05D2220/40 , F05D2250/40 , Y02T10/144
摘要： A turbocharger is provided herein. The turbocharger includes a housing and an adjustable core at least partially circumferentially surrounded by the housing, the adjustable core having a turbine rotor coupled to a compressor rotor via a shaft. The turbocharger further includes an adjustment mechanism coupled to the adjustable core configured to adjust an axial position of the housing relative to the adjustable core in response to adjustment commands.

7. 发明授权

US09555871B2 Two-surface sandwich structure for accommodating in-plane expansion of one of the surfaces relative to the opposing surface 有权
标题翻译：用于容纳相对于相对表面的一个表面的平面内膨胀的双表面夹层结构
公开(公告)号：US09555871B2
公开(公告)日：2017-01-31
申请号：US13412593
申请日：2012-03-05
申请人： Robert E. Grip , John J. Brown
发明人： Robert E. Grip , John J. Brown
IPC分类号： F02K1/82 , F02K1/80 , B64C1/12 , B64D29/06 , B64D27/26 , B64D29/00 , F01D25/26 , F01D25/30 , F04D29/44
CPC分类号： F02K1/80 , B64C1/12 , B64D27/26 , B64D29/00 , B64D29/06 , F01D25/26 , F01D25/30 , F02K1/82 , F02K1/822 , F04D29/441 , F05D2220/323 , F05D2250/40 , F05D2260/50 , Y02T50/672 , Y10T29/49229 , Y10T428/249923
摘要： A sandwich structure includes a first skin, a second skin, a first hinge member, and a second hinge member. The first hinge member may be movably coupled to the first skin and a first skin joint. The second hinge member may be movably coupled to the second skin and second skin joint. The first hinge member and the second member may be movably coupled to one another and a member joint located between the first and second skin joint.
摘要翻译：夹层结构包括第一皮肤，第二皮肤，第一铰链构件和第二铰链构件。第一铰链构件可以可移动地联接到第一皮肤和第一皮肤接头。第二铰链构件可以可移动地联接到第二皮肤和第二皮肤接头。第一铰链构件和第二构件可以可移动地彼此联接和位于第一和第二皮肤接头之间的构件接头。

8. 发明申请

US20130164114A1 ADJUSTABLE CORE TURBOCHARGER 有权
公开(公告)号：US20130164114A1
公开(公告)日：2013-06-27
申请号：US13333189
申请日：2011-12-21
申请人： James Douglas Ervin , August Thomas Vaught
发明人： James Douglas Ervin , August Thomas Vaught
IPC分类号： F04D29/46 , F02C6/12 , F01D17/00
CPC分类号： F04C28/185 , F01D11/08 , F01D11/22 , F01D17/141 , F01D17/143 , F01D25/24 , F02B37/025 , F02B37/22 , F02B39/14 , F02B47/08 , F04C18/02 , F04D15/0033 , F04D25/024 , F04D25/045 , F04D27/002 , F04D27/0246 , F05D2220/40 , F05D2250/40 , Y02T10/144
摘要： A turbocharger is provided herein. The turbocharger includes a housing and an adjustable core at least partially circumferentially surrounded by the housing, the adjustable core having a turbine rotor coupled to a compressor rotor via a shaft. The turbocharger further includes an adjustment mechanism coupled to the adjustable core configured to adjust an axial position of the housing relative to the adjustable core in response to adjustment commands.

9. 发明授权

US08393435B2 Trailing edge for an aircraft engine, of the type with moving chevrons 失效
标题翻译：飞机发动机的后缘，具有移动的人字形的类型
公开(公告)号：US08393435B2
公开(公告)日：2013-03-12
申请号：US12918329
申请日：2009-02-26
申请人： Philipe Guerin
发明人： Philipe Guerin
IPC分类号： F02K1/08
CPC分类号： F02K1/46 , F05D2250/11 , F05D2250/40 , F05D2250/42 , F05D2260/96 , Y02T50/671
摘要： This trailing edge is of the type with moving chevrons (9a, 9b, 9c). It comprises actuating means able to cause these chevrons (9a, 9b, 9c) to move from a passive position in which they are directed substantially in the direction of the airflow leaving the said engine, into an active position in which at least part of each chevron is inclined with respect to this direction. This trailing edge is notable in that the said active position is derived from the said passive position by pivoting, possibly combined with a translational movement, of at least part of each chevron about an axis (Aa, Ab, Ac) substantially parallel to the said direction.
摘要翻译：该后缘是具有移动的人字形（9a，9b，9c）的类型。它包括致动装置，其能够使这些人字形（9a，9b，9c）从被动地位于基本上沿离开所述发动机的气流的方向的被动位置进入活动位置，其中每个人字形相对于这个方向倾斜。该后缘是值得注意的，因为所述主动位置是通过绕基本上平行于所述主动位置的轴线（Aa，Ab，Ac）绕轴线（Aa，Ab，Ac）的枢轴转动（可能与平移运动相结合）而衍生的，方向。

10. 发明授权

US08132755B2 Engine exhaust system with directional nozzle 有权
标题翻译：发动机排气系统带定向喷嘴
公开(公告)号：US08132755B2
公开(公告)日：2012-03-13
申请号：US12303970
申请日：2007-06-11
申请人： Charles Hollimon , John Barber , John Herman Sherrer , Robert Laramee
发明人： Charles Hollimon , John Barber , John Herman Sherrer , Robert Laramee
IPC分类号： B64C15/12
CPC分类号： F02K1/004 , B64D33/04 , F02C7/20 , F02K1/36 , F02K1/52 , F02K1/805 , F05D2220/329 , F05D2230/642 , F05D2250/40 , F05D2260/54
摘要： An exhaust system for an aircraft has a primary exhaust duct for communicating exhaust gas from an engine exhaust exit and is configured for movement with the engine. A secondary exhaust duct is in fluid communication with the primary exhaust duct and is movably mounted to the airframe. The secondary duct has a portion selectively rotatable relative to the remainder of the secondary duct for directing the exhaust gas vector. The system has means for maintaining a generally consistent relative alignment between the primary duct and the secondary duct.
摘要翻译：用于飞行器的排气系统具有用于将来自发动机排气出口的废气连通并且被构造成与发动机一起运动的主排气管道。二次排气管道与主排气管道流体连通并且可移动地安装到机身。次级管道具有相对于辅助管道的其余部分选择性地可旋转的部分，用于引导废气向量。该系统具有用于维持主管道和次管道之间的大致一致的相对对准的装置。

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