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1. 发明申请

US20180100406A1 MULTI-PLY SEAL 审中-公开
公开(公告)号：US20180100406A1
公开(公告)日：2018-04-12
申请号：US15291650
申请日：2016-10-12
申请人： United Technologies Corporation
发明人： Nathan K. Galle
IPC分类号： F01D11/08 , F01D9/02 , F04D29/54 , F04D29/16
CPC分类号： F01D11/08 , F01D9/02 , F01D11/005 , F01D25/246 , F04D29/164 , F04D29/542 , F05D2220/32 , F05D2240/11 , F05D2250/183 , F05D2250/75 , F05D2300/177 , F16J15/0887
摘要： A seal may comprise a first ply including an annular shape and a second ply including a discontinuous annular shape having an axial split. The second ply may be positioned adjacent to a surface of the first ply.

2. 发明授权

US09909431B2 Variable dual spring blade root support for gas turbines 有权
公开(公告)号：US09909431B2
公开(公告)日：2018-03-06
申请号：US14699269
申请日：2015-04-29
申请人： Siemens Energy, Inc.
发明人： Charalambos Polyzopoulos , Mohit Gupta , Robert Hudson , Erica Holden , David Myers
IPC分类号： F01D5/32 , F01D5/30
CPC分类号： F01D5/323 , F01D5/3007 , F05D2250/183 , F05D2250/184 , F05D2250/25
摘要： An adjustable blade root spring device for turbine blade fixation in turbomachinery. The device is designed to be placed in a space in a rotor disk cavity adjacent to a tip of a blade root, where the device applies a radial outward force on the turbine blade to fix the blade position in the rotor disk. The device includes a wave spring with integral end blocks which is compressed by a bolt and a coil spring. When the wave spring is compressed in length, it increases in height and makes contact with the rotor disk and the turbine blade. The force of the wave spring on the turbine blade can be adjusted via the bolt, and the coil spring provides an increased compliance range. The body of the device has an oblong cross-sectional shape, thereby preventing rotation of the device in the space between the blade and the disk.

3. 发明申请

US20180038594A1 COMBUSTOR COOLING PANEL, TRANSITION PIECE AND COMBUSTOR INCLUDING THE SAME, AND GAS TURBINE INCLUDING COMBUSTOR 审中-公开
公开(公告)号：US20180038594A1
公开(公告)日：2018-02-08
申请号：US15551138
申请日：2016-02-15
申请人： MITSUBISHI HITACHI POWER SYSTEMS, LTD.
发明人： Hiroki SHIBATA
IPC分类号： F23R3/06 , F23R3/28 , F01D25/12 , F01D9/02
CPC分类号： F23R3/06 , F01D9/023 , F01D25/12 , F02C7/18 , F05D2220/32 , F05D2240/35 , F05D2250/183 , F05D2250/312 , F05D2250/314 , F05D2260/202 , F23R3/002 , F23R3/28 , F23R3/42 , F23R3/46 , F23R2900/00018
摘要： A combustor cooling panel has a first channel and a second channel through which a cooling medium flows. Relative to an end zone in a longitudinal direction of the first channel, the second channel has: an overlapping zone that overlaps the end zone in an extension direction of the end zone by extending in the extension direction while being separated from the end zone in a circumferential direction intersecting the extension direction; and a non-overlapping zone that does not overlap the end zone in the extension direction. A bent portion that is bent toward the end zone in the circumferential direction is formed in the second channel.

4. 发明申请

US20180015536A1 FORMING COOLING PASSAGES IN COMBUSTION TURBINE SUPERALLOY CASTINGS 审中-公开
公开(公告)号：US20180015536A1
公开(公告)日：2018-01-18
申请号：US15548267
申请日：2016-02-17
申请人： Siemens Aktiengesellschaft
发明人： Gary B. Merrill , Jonathan E. Shipper, JR. , Cora Hitchman
IPC分类号： B22D25/02 , B22D29/00 , B22C9/24 , B22C7/02 , F01D9/02 , F01D25/12 , F01D5/18
CPC分类号： F01D5/284 , B22C7/02 , B22C9/24 , B22D25/02 , B22D29/001 , B28B11/048 , B28B19/0015 , C23C4/02 , C23C4/073 , C23C4/18 , C23C28/3215 , C23C28/3455 , F01D5/18 , F01D5/186 , F01D5/187 , F01D5/28 , F01D5/288 , F01D9/023 , F01D11/08 , F01D11/122 , F01D11/127 , F01D25/12 , F04D29/526 , F04D29/685 , F05D2220/32 , F05D2230/00 , F05D2230/211 , F05D2230/30 , F05D2230/31 , F05D2230/90 , F05D2240/11 , F05D2250/12 , F05D2250/15 , F05D2250/182 , F05D2250/183 , F05D2250/184 , F05D2250/185 , F05D2250/23 , F05D2250/282 , F05D2250/292 , F05D2250/294 , F05D2250/60 , F05D2250/75 , F05D2260/202 , F05D2260/22141 , F05D2300/175 , Y02T50/672 , Y02T50/673 , Y02T50/676 , Y02T50/6765
摘要： Cooling passages (99, 105) are formed in components for combustion turbine engines, such as blades (92), vanes (104, 106), ring segments (110) or castings in transitions (85), during investment casting, through use of ceramic shell inserts (130) within the casting mold (152). Ceramic posts (134) formed in the ceramic shell insert (130) have profiles conforming to corresponding profiles of partially completed cooling passages (156). Posts (134) are removed after superalloy component casting, forming the partially completed cooling passages, which are subsequently completed by removing remaining superalloy material along the cooling passage path.

5. 发明申请

US20170370241A1 TURBINE SHROUD WITH ABRADABLE LAYER HAVING DIMPLED FORWARD ZONE 审中-公开
公开(公告)号：US20170370241A1
公开(公告)日：2017-12-28
申请号：US15548440
申请日：2015-12-09
申请人： Siemens Aktiengesellschaft
发明人： Kok-Mun Tham , Ching-Pang Lee
IPC分类号： F01D11/12
CPC分类号： B22D25/02 , B22C7/02 , B22C9/24 , B22D29/001 , C23C4/02 , C23C4/073 , C23C4/18 , C23C28/3215 , C23C28/3455 , F01D5/18 , F01D5/186 , F01D5/187 , F01D5/28 , F01D5/284 , F01D5/288 , F01D9/023 , F01D11/08 , F01D11/122 , F01D11/127 , F01D25/12 , F04D29/526 , F04D29/685 , F05D2220/32 , F05D2230/00 , F05D2230/211 , F05D2230/30 , F05D2230/90 , F05D2240/11 , F05D2250/12 , F05D2250/15 , F05D2250/182 , F05D2250/183 , F05D2250/184 , F05D2250/185 , F05D2250/23 , F05D2250/282 , F05D2250/292 , F05D2250/294 , F05D2250/60 , F05D2250/75 , F05D2260/202 , F05D2260/22141 , F05D2300/175 , Y02T50/672 , Y02T50/673 , Y02T50/676 , Y02T50/6765
摘要： Turbine and compressor casing abradable components for turbine engines include abradable surfaces with a zonal system of forward (zone A) and rear or aft sections (zone B) surface features. The zone A surface profile comprises an array pattern of non-directional depression dimples, or upwardly projecting dimples, or both, in the abradable surface. The dimpled forward zone A surface features reduce surface solidity in a controlled manner, to help increase abradability during blade tip rubbing incidents, yet they provide sufficient material to resist incoming hot working fluid erosion of the abradable surface. In addition, the dimples provide generic forward section aerodynamic profiling to the abradable surface, compatible with different blade airfoil-camber profiles. The aft zone B surface features comprise an array pattern of ridges and grooves.

6. 发明申请

US20170350260A1 TURBINE COMPONENT AND METHODS OF MAKING AND COOLING A TURBINE COMPONENT 审中-公开
公开(公告)号：US20170350260A1
公开(公告)日：2017-12-07
申请号：US15174271
申请日：2016-06-06
申请人： GENERAL ELECTRIC COMPANY
发明人： Sandip DUTTA , James ZHANG , Gary Michael ITZEL , John McConnell DELVAUX , Matthew Troy HAFNER
IPC分类号： F01D5/18 , F01D9/02 , F01D25/12
CPC分类号： F01D5/187 , F01D5/147 , F01D5/282 , F01D9/02 , F01D25/12 , F05D2220/30 , F05D2230/22 , F05D2230/237 , F05D2230/31 , F05D2240/122 , F05D2240/304 , F05D2250/183 , F05D2250/184 , F05D2250/185 , F05D2260/20 , F05D2260/204 , F05D2300/175 , F05D2300/6033
摘要： A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. Radial cooling channels in the trailing edge portion of the airfoil permit radial flow of a cooling fluid through the trailing edge portion. Each radial cooling channel has a first end at a lower surface at a root edge of the trailing edge portion or at an upper surface at a tip edge of the trailing edge portion and a second end opposite the first end at the lower surface or the upper surface. A method of making a turbine component and a method of cooling a turbine component are also disclosed.

7. 发明申请

US20170321556A1 DAMPER RING 审中-公开
公开(公告)号：US20170321556A1
公开(公告)日：2017-11-09
申请号：US15145160
申请日：2016-05-03
申请人： Pratt & Whitney Canada Corp.
发明人： MAKSIM PANKRATOV
IPC分类号： F01D5/10 , F02C3/04
CPC分类号： F01D5/10 , F02C3/04 , F05D2220/32 , F05D2250/182 , F05D2250/183 , F05D2250/184
摘要： A damper ring is mounted in frictional engagement with a radially inwardly facing surface of a circumferential groove defined in a rotary part of a gas turbine engine. Energy dissipation is provided via sliding friction of the ring in the groove. The damper ring has a circumferentially segmented ring body having a non-uniform circumferential stiffness around its circumference including a locally reduced stiffness in a circumferential direction between each pair of circumferentially adjacent ring segments.

8. 发明申请

US20170275997A1 TURBOFAN AND INDOOR UNIT FOR AIR CONDITIONING APPARATUS 审中-公开
公开(公告)号：US20170275997A1
公开(公告)日：2017-09-28
申请号：US15507013
申请日：2014-10-30
申请人： Mitsubishi Electric Corporation
发明人： Seiji NAKASHIMA , Yoshiki SATO , Keisuke OISHI
IPC分类号： F01D5/14 , F01D5/04
CPC分类号： F01D5/145 , F01D5/04 , F04D29/281 , F04D29/30 , F04D29/666 , F05D2240/303 , F05D2250/183
摘要： A turbofan includes a boss rotatable about an axis, a main plate connected to the boss, a shroud having an intake hole, and a plurality of blades arranged between the main plate and the shroud. An undulating protrusion portion is arranged at a front edge portion of each blade. The undulating protrusion portion includes a plurality of protrusions. The pitches of the plurality of protrusions are formed so as to become smaller as approaching to the main plate side.

9. 发明申请

US20160348721A1 TAPERED LAND THRUST BEARING DEVICE AND TURBOCHARGER PROVIDED WITH THE BEARING DEVICE 审中-公开
标题翻译：带有轴承装置的带状陆面轴承装置和涡轮增压器
公开(公告)号：US20160348721A1
公开(公告)日：2016-12-01
申请号：US15113894
申请日：2014-02-27
申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.
发明人： Takaya FUTAE , Hideaki NISHIDA
IPC分类号： F16C33/10 , F04D17/10 , F01D25/16 , F16C17/04 , F16C33/12
CPC分类号： F16C33/107 , F01D25/168 , F02B39/00 , F05D2220/40 , F05D2250/182 , F05D2250/183 , F05D2250/191 , F05D2250/292 , F05D2250/611 , F16C17/045 , F16C17/047 , F16C33/1075 , F16C33/128 , F16C2360/24
摘要： An object is to provide a tapered land thrust bearing device with a land surface having a substantially reduced area without changing the contour shape of the land surface even if the area of the land surface is small, and high mechanical efficiency, as well as a turbocharger provided with the bearing device. A tapered land thrust bearing device includes: a flange portion fitted onto a rotary shaft and including a first thrust portion; and a thrust member including a second thrust portion which is disposed around a through hole and which faces the first thrust portion of the flange portion. The first thrust portion or the second thrust portion includes a plurality of land surfaces each of which is parallel to a plane orthogonal to an axis of the rotary shaft, the land surfaces being disposed at intervals in a circumferential direction of the through hole, a plurality of tapered surfaces each of which is disposed between the plurality of land surfaces, joined via a step to a boundary of the land surface on one side in the circumferential direction of the through hole, and joined continuously to a boundary of the land surface on the other side in the circumferential direction of the through hole, and at least one concave portion disposed on each of the plurality of land surfaces.
摘要翻译：本发明的目的是提供一种具有大大减小的面积而具有大幅减小的面积的锥形陆面推力轴承装置，而不改变陆面的轮廓形状，即使陆面的面积小，机械效率高，以及涡轮增压器设有轴承装置。锥形陆面推力轴承装置包括：安装在旋转轴上并包括第一推力部分的凸缘部分; 以及推力构件，其包括设置在通孔周围并且与凸缘部的第一推力部相对的第二推力部。所述第一推力部或所述第二推力部具有与所述旋转轴的轴正交的平面平行的多个台面，所述台面沿所述贯通孔的圆周方向间隔配置，所述锥形表面设置在所述多个台面表面之间，所述多个台面表面之间经由台阶在所述通孔的圆周方向上的一侧上的所述台面的边界接合，并且连续地连接到所述通孔的所述台面的边界在通孔的圆周方向上的另一侧，以及设置在多个台面的每一个上的至少一个凹部。

10. 发明申请

US20160222809A1 GAS TURBINE ENGINE WITH SEAL HAVING PROTRUSIONS 审中-公开
标题翻译：具有密封的气体涡轮发动机
公开(公告)号：US20160222809A1
公开(公告)日：2016-08-04
申请号：US15021945
申请日：2014-08-21
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Matthew Andrew Hough , Christopher Corcoran , Jeffrey S. Beattie
IPC分类号： F01D11/00
CPC分类号： F01D11/006 , F01D5/22 , F05D2250/181 , F05D2250/182 , F05D2250/183 , F05D2250/75 , F05D2260/22141
摘要： A gas turbine engine includes a turbine section. The turbine section includes a disk that is rotatable about an axis. A plurality of turbine blades are mounted around a periphery of the disk, and a plurality of seals are arranged between the turbine blades and the periphery of the disk. Each of the seals includes, with respect to the axis, a radially outer surface and a radially inner surface. The radially inner surface includes a plurality of protrusions.
摘要翻译：燃气涡轮发动机包括涡轮部分。涡轮机部分包括可围绕轴线旋转的盘。多个涡轮机叶片围绕盘的周边安装，并且多个密封件布置在涡轮机叶片与盘周边之间。每个密封件相对于轴线包括径向外表面和径向内表面。径向内表面包括多个突起。

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