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公开(公告)号：US12123323B2
公开(公告)日：2024-10-22
申请号：US18322771
申请日：2023-05-24
Inventor： Tsutomu Yoshihara
CPC classification number: F01D5/3007 , F01D5/326 , F05D2240/80 , F05D2250/75 , F05D2260/36
Abstract: A fixing structure for a rotor blade of an embodiment includes: a fixing groove penetrating blade implantation portions and a rotor wheel in a circumferential direction; a locking blade lastly fitted into a blade groove; and a latch member inserted from an axial direction into the fixing groove formed in the blade implantation portion of the locking blade and the rotor wheel forming the blade groove into which the blade implantation portion of the locking blade is fitted. The latch member includes: an inner peripheral latch disposed on a radially inner side; an outer peripheral latch disposed on a radially outer side; a center latch fitted between the inner peripheral latch and the outer peripheral latch, and a bent portion provided at an end portion on a downstream side in the axial direction of the inner peripheral latch, the bent portion being bent to fix the locking blade.
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公开(公告)号：US20240309771A1
公开(公告)日：2024-09-19
申请号：US18396822
申请日：2023-12-27
Applicant: DOOSAN ENERBILITY CO., LTD.
Inventor： Eojin KIM
IPC: F01D11/00
CPC classification number: F01D11/005 , F16J15/104 , F05D2240/55 , F05D2240/80
Abstract: Disclosed is a seal assembly and a turbine including the same, and according to one aspect of the present disclosure, a seal assembly includes: a first seal portion including a plurality of seal bodies stacked to be spaced apart from each other; and a second seal portion including a plurality of seal bodies stacked to be spaced apart from each other, and ends of the seal bodies of the first seal portion are inserted between the seal bodies of the second seal portion and each of the seal bodies is stacked alternately to form a stacked unit, and the seal bodies adjacent to each other are spaced apart from each other if an external force does not exist.
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公开(公告)号：US12071864B2
公开(公告)日：2024-08-27
申请号：US17581170
申请日：2022-01-21
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Howard J. Liles , Bryan P. Dube
CPC classification number: F01D9/041 , F01D5/284 , F01D9/042 , F05D2240/12 , F05D2240/80 , F05D2250/291 , F05D2260/30 , F05D2300/6033
Abstract: A gas turbine engine includes a turbine section disposed about an engine axis. The turbine section includes inner and outer diameter ceramic support rings that define a gaspath there between. Each of the inner and outer diameter ceramic support rings is monolithic and continuous. Ceramic vane arc segments are disposed in the gaspath and supported by the inner and outer diameter ceramic support rings. Each of the ceramic vane arc segments includes inner and outer platforms and an airfoil section there between. At least one retainer engages the inner or outer diameter ceramic support ring with the ceramic vane arc segments to retain the ceramic vane arc segments between the inner and outer diameter ceramic support rings.
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公开(公告)号：US20240125242A1
公开(公告)日：2024-04-18
申请号：US17966297
申请日：2022-10-14
Applicant: RTX Corporation
Inventor： Enzo DiBenedetto , Jackson David Johnson , Nicholas J. Lawliss
CPC classification number: F01D5/3007 , F01D5/326 , F05D2220/32 , F05D2220/36 , F05D2240/80 , F05D2260/36
Abstract: Fan assemblies for gas turbine engines include a rotor disk having a plurality of lugs with a plurality of slots defined between adjacent lugs. A fan platform is configured to be mounted to a lug of the plurality of lugs, the fan platform having a forward tab and an aft tab. An aft retention ring is configured to be fixedly attached to an aft side of the rotor disk and has a platform retention hook for receiving the aft tab of the fan platform. A forward retention ring is configured to be fixedly attached to a forward side of the rotor disk, the forward retention ring having a tab hook configured to attach the forward retention ring to the lug of the plurality of lugs and retain the forward tab of the fan platform to the lug of the plurality of lugs.
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公开(公告)号：US20240102393A1
公开(公告)日：2024-03-28
申请号：US18237938
申请日：2023-08-25
Applicant: ROLLS-ROYCE plc
Inventor： Bogachan ALPAN
CPC classification number: F01D5/188 , F01D9/041 , F05D2220/323 , F05D2230/232 , F05D2240/80
Abstract: A platform for a stator vane includes a platform body and a plug. The platform body defines: an inner surface, an outer surface offset from the inner surface, an internal fluid passageway disposed between the outer surface and the inner surface, and a core aperture extending from the outer surface to the internal fluid passageway. The plug is configured to be secured to the platform body. The plug is configured to occupy no less than 50% of the core aperture by volume whilst secured to the platform body to at least partially eliminate recirculation of a fluid conveyed by the internal fluid passageway within the core aperture.
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Patent Agency Ranking
公开(公告)号：US11891915B2
公开(公告)日：2024-02-06
申请号：US17726954
申请日：2022-04-22
Applicant: Hamilton Sundstrand Corporation
Inventor： Viktor Kilchyk
CPC classification number: F01D5/048 , F01D5/147 , F05D2240/301 , F05D2240/80 , F05D2250/18
Abstract: A rotor for a rotary machine includes a hub centered on a central axis, the hub comprising a shaft portion extending along the central axis, a disk portion circumferentially disposed about the shaft portion, a platform portion as a radially outermost extent of the shaft portion and the disk portion, and a branched support structure extending radially inward from the platform portion. The rotor further includes a plurality of blades extending outward from the platform portion of the hub. The branched support structure comprises a hub region and a blade support region associated with one blade of the plurality of blades.
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公开(公告)号：US11852034B2
公开(公告)日：2023-12-26
申请号：US16827135
申请日：2020-03-23
Applicant: RTX Corporation
Inventor： Matthew P. Forcier , Brian J. Schuler
CPC classification number: F01D5/146 , F01D9/041 , F01D11/001 , F04D29/324 , F04D19/02 , F04D29/542 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2240/55 , F05D2240/80
Abstract: A gas turbine engine includes a compressor section and a compressor case with a low pressure compressor (LPC) and a high pressure compressor (HPC). The HPC is aft of the LPC. The compressor case defines a centerline axis. The compressor section also includes a rotor disk defined between the compressor case and the centerline axis. A plurality of stages are defined radially inward relative to the compressor case. The plurality of stages include at least one tandem blade stage. The tandem blade stage includes a plurality of blade pairs. Each blade pair is circumferentially spaced apart from the other blade pairs, and is operatively connected to the rotor disk. Each blade pair includes a forward blade and an aft blade. The aft blade is configured to further condition air flow with respect to the forward blade without an intervening stator vane stage shrouded cavity therebetween.
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公开(公告)号：US11821320B2
公开(公告)日：2023-11-21
申请号：US17338807
申请日：2021-06-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Steven Douglas Johnson , Kevin Randall McManus , Rahul Anil Bidkar
CPC classification number: F01D11/001 , F01D11/025 , F01D11/22 , F05D2220/323 , F05D2240/11 , F05D2240/80 , F05D2260/38
Abstract: A turbine engine comprising an engine core having at least a compressor section, a combustor section, and a turbine section in axial flow arrangement defining an axial direction and an engine centerline. The turbine engine further having a rotor and a stator, a carriage assembly carried by the stator, and a seal assembly biased toward the rotor.
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公开(公告)号：US11815017B2
公开(公告)日：2023-11-14
申请号：US16850848
申请日：2020-04-16
Applicant: Raytheon Technologies Corporation
Inventor： Arun K. Theertham
CPC classification number: F02C7/00 , F01D11/005 , F02C7/28 , F05D2220/32 , F05D2240/24 , F05D2240/55 , F05D2240/80 , F05D2260/606
Abstract: A fan blade platform assembly includes a pressure side platform half that includes a first attachment wall, a first gas path wall, and a first connecting wall attached to both the first attachment wall and the first gas path wall. A suction side platform half includes a second attachment wall, a second gas path wall, and a second connecting wall attached to both the second attachment wall and the second gas path wall. A seal engages the pressure side platform half and the suction side platform half.
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公开(公告)号：US11814985B2
公开(公告)日：2023-11-14
申请号：US17932214
申请日：2022-09-14
Applicant: DOOSAN ENERBILITY CO., LTD.
Inventor： Jin Woo Song , Jin Ho Bae , Ki Baek Kim , Sung Chul Jung , Jae Yeon Choi
IPC: F01D5/30
CPC classification number: F01D5/3007 , F05D2240/80 , F05D2250/294 , F05D2260/36
Abstract: Disclosed herein are a grooved turbine blade, and a turbine and a gas turbine including the same. According to the disclosure, since a groove part is formed on a root member to disperse torsional stress, it is possible to improve durability of a rotor disk to which the turbine blade is assembled.
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