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1. 发明授权

US10001028B2 Dual spring bearing support housing 有权
公开(公告)号：US10001028B2
公开(公告)日：2018-06-19
申请号：US13453837
申请日：2012-04-23
申请人： Ravindra Shankar Ganiger , Stephanie Frances Drummond , Daryl Scott Schneider
发明人： Ravindra Shankar Ganiger , Stephanie Frances Drummond , Daryl Scott Schneider
IPC分类号： F01D25/16 , F02C7/06 , F16C27/04 , F16C19/54 , F16C35/04
CPC分类号： F01D25/16 , F01D25/164 , F02C7/06 , F05D2230/64 , F05D2250/312 , F05D2250/36 , F05D2250/37 , F16C19/54 , F16C27/04 , F16C35/042 , F16C2360/23
摘要： A bearing support housing for a gas turbine engine includes: an annular mounting flange; a first bearing cage including: an annular first bearing support ring; and an annular array of axially-extending first spring arms interconnecting the first bearing support ring and the mounting flange; and a second bearing cage including: an annular second bearing support ring; and an annular array of axially-extending second spring arms interconnecting the second bearing support ring and the mounting flange, the second spring arms defining spaces therebetween. The first spring arms are received between the second spring arms, and the bearing cages are sized so as to permit independent flexing motion of the first and second spring arms.

2. 发明申请

US20170284213A1 SEAL SEGMENT ASSEMBLY INCLUDING MATING CONNECTION FOR A TURBOMACHINE 审中-公开
公开(公告)号：US20170284213A1
公开(公告)日：2017-10-05
申请号：US15479442
申请日：2017-04-05
申请人： MTU Aero Engines AG
发明人： Christian Liebl , Steffen Schlothauer , Andreas Jakimov , Alexander Ladewig , Karl Blumenschein , Juergen Kraus
IPC分类号： F01D11/00 , F01D9/04 , F01D5/02
CPC分类号： F01D11/001 , B22F5/009 , B22F2998/10 , B22F2999/00 , B33Y10/00 , B33Y80/00 , F01D5/02 , F01D9/041 , F01D11/127 , F05D2220/323 , F05D2230/22 , F05D2230/234 , F05D2230/31 , F05D2240/11 , F05D2250/283 , F05D2250/37 , F05D2250/75 , F05D2260/36 , Y02P10/295 , B22F5/106 , B22F3/1055 , B22F2207/20 , B22F7/062
摘要： A seal segment assembly for a turbomachine, in particular a gas turbine, including a first seal carrier and a second seal carrier, that are adjacently disposed in the circumferential direction, the first seal carrier having a first carrier base and at least one first sealing member that is joined to the first carrier base, and the second seal carrier having a second carrier base and at least one second sealing member that is joined to the second carrier base, the first sealing member and the second sealing member being formed by a plurality of cavities, that are adjacently disposed in the circumferential direction and in the axial direction, in particular evenly spaced, the cavities extending in the radial direction from the particular carrier base. The first carrier base and the second carrier base are intercouplable or are intercoupled in the circumferential direction by a mating connection assembly.

3. 发明授权

US09771813B2 Converging flow joint insert system at an intersection between adjacent transitions extending between a combustor and a turbine assembly in a gas turbine engine 有权
公开(公告)号：US09771813B2
公开(公告)日：2017-09-26
申请号：US15318781
申请日：2014-06-26
申请人： Siemens Energy, Inc.
发明人： Robert T. Brooks
IPC分类号： F01D9/02 , F02C3/14 , F23R3/60 , F23R3/42
CPC分类号： F01D9/023 , F02C3/14 , F05D2250/25 , F05D2250/37 , F05D2250/38 , F05D2260/941 , F23R3/002 , F23R3/425 , F23R3/60 , F23R2900/00019
摘要： A transition duct system (100) for routing a gas flow from a combustor (102) to the first stage (104) of a turbine section (106) in a combustion turbine engine (108), wherein the transition duct system (100) includes one or more converging flow joint inserts (120) forming a trailing edge (122) at an intersection (124) between adjacent transition ducts (126, 128) is disclosed. The transition duct system (100) may include a transition duct (126, 128) having an internal passage (130) extending between an inlet (132, 184) to an outlet (134, 186) and may expel gases into the first stage turbine (104) with a tangential component. The converging flow joint insert (120) may be contained within a converging flow joint insert receiver (136) and disconnected from the transition duct bodies (126, 128) by which the converging flow joint insert (120) is positioned. Being disconnected eliminates stress formation within the converging flow joint insert (120), thereby enhancing the life of the insert. The converging flow joint insert (120) may be removable such that the insert (120) can be replaced once worn beyond design limits.

4. 发明申请

US20160146156A1 CASCADE SYSTEM AND APPARATUS 审中-公开
标题翻译： CASCADE系统和设备
公开(公告)号：US20160146156A1
公开(公告)日：2016-05-26
申请号：US14954570
申请日：2015-11-30
申请人： Rohr, Inc.
发明人： Sara C. Crawford
IPC分类号： F02K1/72
CPC分类号： F02K1/72 , F02K1/64 , F02K1/70 , F05D2250/37
摘要： A thrust reverser system may comprise a cascade radially positioned about a centerline of an engine or a nacelle centerline. Various cascade features may be positioned at a constant radius from the centerline while other features vary according to station and/or circumferential position.
摘要翻译：推力反向器系统可以包括围绕发动机或机舱中心线的中心线径向定位的级联。各种级联特征可以从中心线定位在恒定的半径处，而其它特征根据站和/或周向位置而变化。

5. 发明申请

US20130280063A1 DUAL SPRING BEARING SUPPORT HOUSING 有权
标题翻译：双弹簧轴承支架
公开(公告)号：US20130280063A1
公开(公告)日：2013-10-24
申请号：US13453837
申请日：2012-04-23
申请人： Ravindra Shankar Ganiger , Stephanie Frances Drummond , Daryl Scott Schneider
发明人： Ravindra Shankar Ganiger , Stephanie Frances Drummond , Daryl Scott Schneider
IPC分类号： F04D29/04
CPC分类号： F01D25/16 , F01D25/164 , F02C7/06 , F05D2230/64 , F05D2250/312 , F05D2250/36 , F05D2250/37 , F16C19/54 , F16C27/04 , F16C35/042 , F16C2360/23
摘要： A bearing support housing for a gas turbine engine includes: an annular mounting flange; a first bearing cage including: an annular first bearing support ring; and an annular array of axially-extending first spring arms interconnecting the first bearing support ring and the mounting flange; and a second bearing cage including: an annular second bearing support ring; and an annular array of axially-extending second spring arms interconnecting the second bearing support ring and the mounting flange, the second spring arms defining spaces therebetween. The first spring arms are received between the second spring arms, and the bearing cages are sized so as to permit independent flexing motion of the first and second spring arms.
摘要翻译：用于燃气涡轮发动机的轴承支撑壳体包括：环形安装凸缘; 第一轴承保持架，包括：环形第一轴承支撑环; 以及将所述第一轴承支撑环和所述安装凸缘互连的轴向延伸的第一弹簧臂的环形阵列; 以及第二轴承保持架，其包括：环形的第二轴承支撑环; 以及将所述第二轴承支撑环和所述安装凸缘互连的轴向延伸的第二弹簧臂的环形阵列，所述第二弹簧臂在其间限定空间。第一弹簧臂被容纳在第二弹簧臂之间，并且轴承保持架的尺寸设计成允许第一和第二弹簧臂的独立的弯曲运动。

6. 发明授权

US09933012B1 Bearing centering spring with integral outer rings 有权
公开(公告)号：US09933012B1
公开(公告)日：2018-04-03
申请号：US14616990
申请日：2015-02-09
申请人： United Technologies Corporation
发明人： Joseph Grillo , Kevin Duffy , Ronnie K. Kovacik
IPC分类号： F16C27/00 , F16C27/04
CPC分类号： F16C33/605 , F01D25/162 , F01D25/164 , F02C7/06 , F05D2230/64 , F05D2240/50 , F05D2250/31 , F05D2250/36 , F05D2250/37 , F16C19/28 , F16C19/54 , F16C27/04 , F16C27/045 , F16C33/581 , F16C2226/50 , F16C2240/40 , F16C2360/23
摘要： A bearing centering spring includes a cylindrical body with outer rings at each end, wherein each outer ring has outer raceways on the inner surface of the body. There is also a retaining feature on an end of the body and ports through the body that are positioned between the outer rings.

7. 发明申请

US20160265431A1 NOZZLE, COMBUSTION APPARATUS, AND GAS TURBINE 审中-公开
标题翻译：喷嘴，燃烧装置和气体涡轮
公开(公告)号：US20160265431A1
公开(公告)日：2016-09-15
申请号：US15031051
申请日：2014-11-26
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： Issei TAMURA , Shinji AKAMATSU , Keijiro SAITO , Kotaro MIYAUCHI , Tomo KAWAKAMI
IPC分类号： F02C3/30 , F23R3/28 , F23L7/00
CPC分类号： F02C3/30 , F05D2220/32 , F05D2250/37 , F05D2250/73 , F23L7/002 , F23R3/28 , F23R3/343 , F23R2900/00013
摘要： A combustion apparatus includes a nozzle in which a fuel injection port for injecting a fuel is formed on the center of a tip. A plurality of water injection ports are formed with intervals therebetween in a circumferential direction around the fuel injection port of the tip of the nozzle, and the water injection ports are non-uniformly formed in the circumferential direction.
摘要翻译：燃烧装置包括喷嘴，其中在喷嘴的中心形成有用于喷射燃料的燃料喷射口。在喷嘴端部的燃料喷射口周围的周向上形成有多个注水口，并且水喷射口在圆周方向上不均匀地形成。

8. 发明申请

US20150361899A1 Fire Shield for a Gas Turbine Engine 审中-公开
标题翻译：燃气轮机发动机防火罩
公开(公告)号：US20150361899A1
公开(公告)日：2015-12-17
申请号：US14760612
申请日：2013-01-15
申请人： United Technologies Corporation
发明人： Chung Wong , Jack V. Vitale , Omar I. Osorio , Daih-Yeou Chen
IPC分类号： F02C7/25 , F02C7/22
CPC分类号： F02C7/25 , F01D25/145 , F02C7/22 , F05D2220/50 , F05D2230/54 , F05D2240/15 , F05D2250/231 , F05D2250/37 , F05D2300/603 , Y02T50/672 , Y02T50/675 , Y10T29/49828
摘要： A gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes an engine case, a multiple of fuel injectors mounted to the engine case, and a fire shield mounted to the engine case to surround at least one, but less than all, of the multiple of fuel injectors. In a further embodiment of the foregoing embodiment, the fire shield includes a sheet metal alloy layer. In the alternative or additionally thereto, in the foregoing embodiment the fire shield includes a composite cloth on an interior of the sheet metal alloy layer with respect to the engine case.
摘要翻译：根据本公开的一个公开的非限制性实施例的燃气涡轮发动机包括发动机壳体，安装到发动机壳体上的多个燃料喷射器，以及安装到发动机壳体上的防火罩，以围绕至少一个但小于所有的燃料喷射器的数量。在上述实施例的另一实施例中，防火罩包括金属板合金层。在替代或附加地，在前述实施例中，防火罩包括相对于发动机壳体在金属板合金层内部的复合布。

9. 发明授权

US08888441B2 Segmented seal assembly 有权
标题翻译：分段密封组件
公开(公告)号：US08888441B2
公开(公告)日：2014-11-18
申请号：US13197532
申请日：2011-08-03
申请人： Daniel Edward Jordy , William Edward Adis , Bernard Arthur Couture, Jr. , Dexter Andrew Young
发明人： Daniel Edward Jordy , William Edward Adis , Bernard Arthur Couture, Jr. , Dexter Andrew Young
IPC分类号： F01D11/12 , F01D11/02 , F16J15/44
CPC分类号： F01D11/02 , F01D11/025 , F05D2220/31 , F05D2230/642 , F05D2250/37 , F05D2260/36 , F16J15/442
摘要： Systems and devices for sealing portions of a rotary machine are disclosed. In one embodiment, a seal assembly element includes: a head flange; an axial neck connected to the head flange, wherein the axial neck includes a mating flange extending circumferentially from a distal end of the seal assembly element, the mating flange configured to form a multidirectional seal with a recessed portion of a complementary seal assembly element; and a set of axial seal teeth connected to the axial neck.
摘要翻译：公开了用于密封旋转机器的部分的系统和装置。在一个实施例中，密封组件元件包括：头部凸缘; 连接到头部凸缘的轴向颈部，其中所述轴向颈部包括从所述密封组件元件的远端周向延伸的配合凸缘，所述配合凸缘被配置成与互补密封组件元件的凹部形成多向密封; 以及一组轴向密封齿连接到轴向颈部。

10. 发明授权

US08534673B2 Inter stage seal housing having a replaceable wear strip 有权
标题翻译：跨级密封外壳具有可更换的耐磨条
公开(公告)号：US08534673B2
公开(公告)日：2013-09-17
申请号：US12860359
申请日：2010-08-20
申请人： Santo F. Scimeca , Chad Garner
发明人： Santo F. Scimeca , Chad Garner
IPC分类号： F16J15/447
CPC分类号： F01D11/12 , F01D11/001 , F01D11/122 , F05D2230/72 , F05D2240/40 , F05D2240/55 , F05D2250/37
摘要： An inter stage seal housing for a turbine engine having upper and lower half inter stage seal housings in which a contact sealing surface of the seal housing is restored after an interval of engine operation. The contact sealing surface is restored by fitting a replaceable wear strip on the downstream sealing surface of the seal housing. In order to fit the replaceable wear strip, a circumferential groove is machined along an outer peripheral edge of the seal housing. The groove is machined to include axial location and radial retention such that the wear strips can be slid into the upper half and lower half inter stage seal housing circumferentially from the horizontal joint. The groove includes through holes and the wear strips include corresponding threaded holes such that the wear strips can be fastened in the groove by fasteners and fastener retention hardware.
摘要翻译：一种用于涡轮发动机的级间密封壳体，其具有上下半层间密封壳体，其中密封壳体的接触密封表面在发动机操作间隔之后恢复。通过在密封壳体的下游密封表面上安装可更换的耐磨条来恢复接触密封表面。为了安装可更换的耐磨条，沿着密封壳体的外周缘加工圆周槽。凹槽被加工成包括轴向位置和径向保持，使得磨损条可以从水平接头周向滑入上半部和下半部分间隔间密封壳体。凹槽包括通孔，并且耐磨条包括相应的螺纹孔，使得耐磨条可以通过紧固件和紧固件保持硬件紧固在凹槽中。

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