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1. 发明授权

US09976744B2 Reheat burner arrangement having an increasing flow path cross-section 有权
公开(公告)号：US09976744B2
公开(公告)日：2018-05-22
申请号：US14063065
申请日：2013-10-25
申请人： Ansaldo Energia Switzerland AG
发明人： John Philip Wood , Andrea Ciani , Andre Theuer , Douglas Anthony Pennell , Ewald Freitag
IPC分类号： F23R3/20 , F23R3/16 , F02C6/00 , F23R3/34 , F23R3/12 , F02C6/02 , F23R3/18
CPC分类号： F23R3/20 , F02C6/003 , F02C6/02 , F05D2250/12 , F05D2250/13 , F23R3/12 , F23R3/16 , F23R3/18 , F23R3/34 , F23R3/346 , F23R2900/03341
摘要： A reheat burner arrangement including a center body, an annular duct with a cross-section area, an intermediate fuel injection plane located along the center body and being actively connected to the cross section area of the annular duct, wherein the center body is located upstream of a combustion chamber, wherein the structure of the reheat burner arrangement is defined by various parameters and the structure of the reheat burner arrangement is defined by various dependencies.

2. 发明申请

US20180066527A1 TURBINE COMPONENT THERMAL BARRIER COATING WITH VERTICALLY ALIGNED, ENGINEERED SURFACE AND MULTIFURCATED GROOVE FEATURES 审中-公开
公开(公告)号：US20180066527A1
公开(公告)日：2018-03-08
申请号：US15547709
申请日：2015-12-08
申请人： Siemens Aktiengesellschaft
发明人： Kai Kadau , Jose Antonio Pascual-Gutierrez , Atin Sharma
IPC分类号： F01D5/28 , F01D11/12 , F01D5/18 , C23C28/00 , C23C4/18 , C23C4/073 , C23C4/02
CPC分类号： F01D5/288 , C23C4/02 , C23C4/073 , C23C4/18 , C23C28/3215 , C23C28/3455 , F01D5/186 , F01D11/122 , F05D2230/30 , F05D2230/31 , F05D2230/90 , F05D2240/11 , F05D2250/11 , F05D2250/12 , F05D2250/132 , F05D2250/294 , F05D2260/22141
摘要： Turbine engine (80) components, such as blades (92), vanes (104, 106), ring segment 110 abradable surfaces 120, or transitions (85), have vertically aligned engineered surface features (ESFs) (632, 634) and furcated engineered groove features (EGFs) (642, 652). A planform pattern of EGFs (642, 652) is cut into the outer surface of the component's thermal barrier coating (TBC). The EGF pattern includes a planform pattern of overlying vertices (644) respectively in vertical alignment with an underlying corresponding ESF (632, 634). At least three respective groove segments (642, 652, 642) within the EGF pattern (640) converge at each respective vertex (644) in a multifurcated pattern, so that crack-inducing stresses are attenuated in cascading fashion, as the stress (σA) is furcated (σB, σC) at each successive vertex juncture.

3. 发明申请

US20170234141A1 AIRFOIL HAVING CROSSOVER HOLES 审中-公开
公开(公告)号：US20170234141A1
公开(公告)日：2017-08-17
申请号：US15044775
申请日：2016-02-16
申请人： General Electric Company
发明人： Ronald Scott Bunker , Robert David Briggs
IPC分类号： F01D5/18 , F01D5/14
CPC分类号： F01D5/187 , F05D2240/303 , F05D2250/12 , F05D2250/14 , F05D2260/201 , F05D2260/202 , Y02T50/676
摘要： An airfoil for a turbine engine having first and second radially extending cooling chambers separated by a radially extending rib in which rows of crossover holes pass through the rib and fluidly coupling the first and second chambers.

4. 发明申请

US20170058700A1 EXHAUST MIXER WITH OUTER LOBE CONSTRAINT BAND 审中-公开
标题翻译：排气混合器与外部约束条带
公开(公告)号：US20170058700A1
公开(公告)日：2017-03-02
申请号：US15227599
申请日：2016-08-03
申请人： Rolls-Royce North American Technologies, Inc.
发明人： Tab M. Heffernan , Kenneth M. Pesyna
IPC分类号： F01D25/30 , F01D25/04 , F01D9/04
CPC分类号： F01D25/30 , F01D9/04 , F01D25/04 , F02K1/48 , F05D2220/32 , F05D2230/237 , F05D2230/642 , F05D2250/12 , F05D2250/141 , F05D2250/16 , F05D2260/941 , F05D2260/96
摘要： A gas turbine engine exhaust component is disclosed herein. The gas turbine engine exhaust component includes an annular mixer that extends around a central axis and is formed to include inner lobes that define radially-outwardly opening channels and outer lobes that define radially-inwardly opening channels. A constraint band is added to connect the outer lobes and reduce vibration, deflections, and stresses.
摘要翻译：本文公开了一种燃气涡轮发动机排气部件。燃气涡轮发动机排气部件包括围绕中心轴线延伸并且形成为包括限定径向向外的开口通道的内凸角和限定径向向内开口通道的外凸角的环形混合器。添加约束条带以连接外裂片并减少振动，偏转和应力。

5. 发明申请

US20170044905A1 Gas Turbine Blade 审中-公开
标题翻译：燃气轮机叶片
公开(公告)号：US20170044905A1
公开(公告)日：2017-02-16
申请号：US15235568
申请日：2016-08-12
申请人： Doosan Heavy Industries & Construction Co., Ltd.
发明人： Jong Hoon Park
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/288 , F05D2220/32 , F05D2230/90 , F05D2240/30 , F05D2240/81 , F05D2250/12 , F05D2250/22 , F05D2260/202
摘要： A gas turbine blade has a trench part of a film cooling unit for cooling a blade part that is formed at a tip of a film cooling hole part. As a result, cooling efficiency of the blade can be improved since the blade part is sufficiently cooled even during introduction of a large amount of cooling air, durability of the blade can be increased by inhibiting the blade from being damaged due to hot gas since the trench part is formed to have a minimum width, and efficiency of a gas turbine can be increased by an improvement in film efficiency.
摘要翻译：燃气轮机叶片具有用于冷却形成在薄膜冷却孔部分的尖端处的叶片部分的薄膜冷却单元的沟槽部分。结果，即使在大量冷却空气的引入期间叶片部分被充分冷却，也可以提高叶片的冷却效率，通过抑制由于热气体而导致的叶片的损坏，能够提高叶片的耐久性沟槽部形成为具有最小宽度，并且可以通过提高膜效率来提高燃气轮机的效率。

6. 发明申请

US20160312795A1 COMPOSITE FAN INLET BLADE CONTAINMENT 审中-公开
标题翻译：复合风扇进线刀片容纳
公开(公告)号：US20160312795A1
公开(公告)日：2016-10-27
申请号：US15105212
申请日：2014-11-24
申请人： GENERAL ELECTRIC COMPANY
发明人： David William CRALL
IPC分类号： F04D29/52 , B64D33/02 , B64D29/00 , F04D29/02 , F04D29/32
CPC分类号： F04D29/526 , B64D29/00 , B64D33/02 , F01D11/127 , F01D21/045 , F01D25/24 , F04D29/023 , F04D29/325 , F05D2250/12 , F05D2250/13 , F05D2250/132 , F05D2250/18 , F05D2300/603 , Y02T50/672
摘要： A ribbed composite shell includes an annular grid of relatively thick crack arresting ribs embedded in a relatively thin annular shell and relatively thin panels in thin annular shell between arresting ribs wherein each of panels are completely surrounded by a set of relatively thick adjoining ones of ribs. A shell forward flange may extend radially inwardly from thin annular shell. Arresting ribs may include radially stacked layers of strips between radially stacked annular layers of shell. Annular grid may include a rectangular grid pattern, a diamond grid pattern, or a hexagonal grid pattern. A nacelle inlet may have the ribbed composite shell within one or both of radially spaced apart composite inner and outer skins of an inner barrel. Nacelle inlet may be part of attached to a fan casing and axially disposed forward of fan blades circumscribed by the casing. The inlet may be on an engine nacelle.
摘要翻译：肋状复合壳体包括嵌入相对薄的环形壳体中的相对较厚的防裂肋的环形格栅，以及在阻挡肋之间的薄环形壳体中的相对薄的板，其中每个板被一组相对较厚的相邻的肋部包围。外壳向前法兰可从薄的环形外壳径向向内延伸。阻挡肋可以包括在径向层叠的壳的环形层之间的径向堆叠的条带。环形网格可以包括矩形网格图案，菱形网格图案或六边形网格图案。机舱入口可以在内筒的径向间隔开的复合内外表面的一个或两个内具有肋状复合壳。机舱入口可以是附接到风扇壳体并且轴向地设置在由壳体限定的风扇叶片的前面的一部分。入口可以在发动机机舱上。

7. 发明申请

US20160215643A1 SHIM SEAL ASSEMBLIES AND ASSEMBLY METHODS FOR STATIONARY COMPONENTS OF ROTARY MACHINES 审中-公开
标题翻译：旋转机械静态组件的SHIM密封组件和组装方法
公开(公告)号：US20160215643A1
公开(公告)日：2016-07-28
申请号：US15089706
申请日：2016-04-04
申请人： GENERAL ELECTRIC COMPANY
发明人： Neelesh Nandkumar Sarawate , Victor John Morgan , David Wayne Weber
IPC分类号： F01D11/00 , F16J15/12 , F16J15/08
CPC分类号： F01D11/005 , F05D2220/32 , F05D2240/11 , F05D2240/55 , F05D2250/12 , F05D2250/75 , F16J15/0812 , F16J15/0893 , F16J15/128
摘要： A seal assembly for a rotary machine is provided. The seal assembly includes a shim seal including multiple seal plates forming a box shaped shim seal. The box shaped seal includes a plurality of cuts at two opposing sides or corners for allowing high pressure fluid to occupy the cavity of the box-shaped shim seal. The seal may be inserted within one or more slots between adjacent stator components of the rotary machine.
摘要翻译：提供了一种用于旋转机器的密封组件。密封组件包括垫片密封件，该密封件包括形成盒形垫片密封件的多个密封板。箱形密封件包括在两个相对的侧面或拐角处的多个切口，用于允许高压流体占据箱形垫片密封件的空腔。密封件可以插入在旋转机器的相邻定子部件之间的一个或多个槽内。

8. 发明申请

US20160146041A1 BLADE OR VANE FOR A TURBOMACHINE AND AXIAL TURBOMACHINE 有权
标题翻译：涡轮机和轴流式涡轮机的叶片或叶片
公开(公告)号：US20160146041A1
公开(公告)日：2016-05-26
申请号：US14943686
申请日：2015-11-17
申请人： MTU Aero Engines AG
发明人： Andreas Hartung , Hermann Klingels , Patrick Wackers , Manfred Feldmann , Frank Stiehler , Markus Schlemmer
IPC分类号： F01D25/06 , F01D9/04 , F04D29/32
CPC分类号： F01D25/06 , F01D5/10 , F01D5/16 , F01D5/26 , F01D9/02 , F01D9/041 , F04D29/324 , F04D29/662 , F04D29/668 , F05D2220/32 , F05D2220/3212 , F05D2220/3215 , F05D2220/3217 , F05D2220/3219 , F05D2240/129 , F05D2240/30 , F05D2250/12 , F05D2250/121 , F05D2250/131 , F05D2250/141 , F05D2250/313 , F05D2260/96 , Y02T50/671
摘要： The present invention relates to a blade (100) or vane for a turbomachine, having at least one impulse element housing (1.1, 1.2) with a first impact cavity (10), in which an impulse element (11) is arranged with play of movement, wherein the impulse element housing has at least one second impact cavity (20), which is in alignment with the first impact cavity in a first matrix direction (A) and in which an impulse element (21) is arranged with play of movement, and has at least one third impact cavity (30), which is in alignment with the first impact cavity in a second matrix direction (B) crosswise to the first matrix direction and in which an impulse element (31) is arranged with play of movement.
摘要翻译：本发明涉及一种用于涡轮机的叶片（100）或叶片，其具有至少一个具有第一冲击腔（10）的脉冲元件壳体（1.1,1.2），其中脉冲元件（11）布置成运动，其中所述脉冲元件壳体具有至少一个第二冲击腔（20），所述第二冲击腔在第一矩阵方向（A）上与所述第一冲击腔对准，并且其中脉冲元件（21）布置成具有运动，并且具有至少一个第三冲击腔（30），其在与第一矩阵方向交叉的第二矩阵方向（B）上与第一冲击腔对准，其中脉冲元件（31）布置成与运动。

9. 发明申请

US20150369047A1 ROTOR AND GAS TURBINE ENGINE INCLUDING SAME 审中-公开
标题翻译：转子和气体涡轮发动机包括相同的
公开(公告)号：US20150369047A1
公开(公告)日：2015-12-24
申请号：US14742162
申请日：2015-06-17
申请人： United Technologies Corporation
发明人： Michael G. McCaffrey
IPC分类号： F01D5/08 , F01D5/12
CPC分类号： F01D5/082 , F01D5/12 , F04D29/321 , F04D29/584 , F05D2220/32 , F05D2250/12 , F05D2250/13 , F05D2250/71 , F05D2260/20 , F05D2260/2212 , Y02T50/671 , Y02T50/676
摘要： A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk. One or more cooling features may be incorporated radially inboard from the rotor disk rim that operate to induce vortices adjacent to the disk rim and/or disk web. The vortices increase the local velocity in the secondary cooling air flow path and therefore increase the heat transfer rate from the rotor to the secondary cooling air flow path.
摘要翻译：用于燃气涡轮发动机的转子包括从转子盘延伸的多个叶片。一个或多个冷却特征可以从转子盘边缘径向地插入内部，其操作以引起与盘缘和/或盘腹板相邻的涡流。涡流增加了二次冷却空气流动路径中的局部速度，因此增加了从转子到二次冷却空气流动路径的传热速率。

10. 发明授权

US09021813B2 Cable-actuated variable area fan nozzle with elastomeric seals 有权
标题翻译：带有弹性体密封件的电缆可变区域风扇喷嘴
公开(公告)号：US09021813B2
公开(公告)日：2015-05-05
申请号：US13225803
申请日：2011-09-06
申请人： Christopher Jasklowski , Michael L. Sangwin , David William Foutch , Mehmet Bahadir Alkislar , Matthew Anthony Dilligan
发明人： Christopher Jasklowski , Michael L. Sangwin , David William Foutch , Mehmet Bahadir Alkislar , Matthew Anthony Dilligan
IPC分类号： F02K1/12 , F02K1/11 , B25J5/00 , B62D57/024 , G05D1/00 , B64F5/00
CPC分类号： B25J5/007 , B62D57/024 , F02K1/12 , F02K1/1207 , F02K1/763 , F02K1/805 , F05D2250/12 , F05D2250/13 , F05D2270/051 , F05D2270/20 , F05D2270/58 , F05D2300/501 , G05D1/0033 , Y02T50/672
摘要： An apparatus installed on an aircraft, comprising: a sleeve or duct having a trailing lip area; a plurality of petals arranged side by side with gaps therebetween, one end of each petal being attached or pivotably coupled to the lip area; and a plurality of elastomeric seals configured and disposed to close the gaps between adjacent petals. Each elastomeric seal comprises a first portion that moves with a portion of a first petal that is in contact therewith, a second portion that moves with a portion of a second petal that is in contact there, and a third portion which is stretched as the first and second petals move further apart from each other. Petal deflection is actuated by a system comprising a flexible member, a motor, a shaft driven by the motor, and an arm projecting from the shaft. One end of the flexible member is attached to the arm, the flexible member being movable to deflect the petals inward in response to a shaft rotation.
摘要翻译：一种安装在飞机上的装置，包括：具有后缘区域的套筒或管道; 并排布置的多个花瓣，其间具有间隙，每个花瓣的一端附接或可枢转地联接到唇部区域; 以及多个弹性体密封件，其被配置和设置成封闭相邻花瓣之间的间隙。每个弹性密封件包括第一部分，其与与其接触的第一花瓣的一部分移动;第二部分，其与在其中接触的第二花瓣的一部分一起移动，第三部分被拉伸为第一部分并且第二个花瓣彼此进一步分开。花瓣偏转由包括柔性构件，马达，由马达驱动的轴和从轴突出的臂的系统致动。柔性构件的一端附接到臂，柔性构件可移动以响应于轴旋转向内偏转瓣。

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