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Patent Agency Ranking
公开(公告)号：US20170234142A1
公开(公告)日：2017-08-17
申请号：US15045553
申请日：2016-02-17
Applicant: General Electric Company
Inventor： Adebukola Oluwaseun Benson , Nicholas Alvin Hogberg , Xiuzhang James Zhang , Gary Michael Itzel , Mohankumar Banakar
CPC classification number: F01D5/187 , F01D5/186 , F02C3/04 , F05D2220/32 , F05D2240/304 , F05D2240/80 , F05D2250/185 , F05D2250/314 , F05D2250/38 , F05D2250/52
Abstract: The present disclosure is directed to a rotor blade for a gas turbine engine. The rotor blade includes a platform having a radially inner surface and a radially outer surface. A connection portion extends radially inwardly from the radially inner surface of the platform. An airfoil extends radially outwardly from the radially outer surface of the platform to an airfoil tip. The airfoil includes a leading edge portion and a trailing edge portion. The platform, the airfoil, and the connection portion collectively define a cooling circuit extending from an inlet defined by the connection portion to one or more outlet passages at least partially defined by the trailing edge portion of the airfoil. At least one of the one or more outlet passages include an entrance and an exit radially inwardly offset from the entrance.
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公开(公告)号：US20240151158A1
公开(公告)日：2024-05-09
申请号：US18410572
申请日：2024-01-11
Applicant: General Electric Company
Inventor： Prashant Bhujabal , Ravindra Shankar Ganiger , Narayanan Payyoor , Mohankumar Banakar , Weize Kang
CPC classification number: F01D25/162 , F01D5/06 , F02C7/06 , F05D2240/54 , F05D2240/61 , F05D2260/40311
Abstract: A bearing support assembly to support one or more bearings on a shaft. The bearing support assembly includes a bearing support frame configured to be coupled to a static frame, a plurality of ribs connected to the bearing support frame, and a bearing support connected to the plurality of ribs and configured to support a bearing of the one or more bearings. The bearing support assembly has a non-axisymmetric stiffness around a circumference of the bearing support assembly.
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公开(公告)号：US20230061131A1
公开(公告)日：2023-03-02
申请号：US17644475
申请日：2021-12-15
Applicant: General Electric Company
Inventor： Prashant Bhujabal , Ravindra Shankar Ganiger , Narayanan Payyoor , Mohankumar Banakar , Weize Kang
Abstract: A bearing support assembly to support one or more bearings on a shaft. The bearing support assembly includes a bearing support frame configured to be coupled to a static frame, a plurality of ribs connected to the bearing support frame, and a bearing support connected to the plurality of ribs and configured to support a bearing of the one or more bearings. The bearing support assembly has a non-axisymmetric stiffness around a circumference of the bearing support assembly.
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公开(公告)号：US11891905B2
公开(公告)日：2024-02-06
申请号：US17644475
申请日：2021-12-15
Applicant: General Electric Company
Inventor： Prashant Bhujabal , Ravindra Shankar Ganiger , Narayanan Payyoor , Mohankumar Banakar , Weize Kang
CPC classification number: F01D25/162 , F01D5/06 , F02C7/06 , F05D2240/54 , F05D2240/61 , F05D2260/40311
Abstract: A bearing support assembly to support one or more bearings on a shaft. The bearing support assembly includes a bearing support frame configured to be coupled to a static frame, a plurality of ribs connected to the bearing support frame, and a bearing support connected to the plurality of ribs and configured to support a bearing of the one or more bearings. The bearing support assembly has a non-axisymmetric stiffness around a circumference of the bearing support assembly.
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公开(公告)号：US20170356297A1
公开(公告)日：2017-12-14
申请号：US15180842
申请日：2016-06-13
Applicant: General Electric Company
CPC classification number: F01D5/3007 , F01D5/187 , F01D5/326 , F05D2220/32 , F05D2230/10 , F05D2260/81 , F05D2260/941 , Y02T50/673
Abstract: The present application thus provides a method for reducing stress on a turbine blade wherein each of the turbine blades includes a dovetail with lockwire tab. The method may include the steps of (a) determining a starting line for a backcut relative to a lockwire tab end, (b) determining a cut angle for the backcut, and (c) removing material from the lockwire tab according to the starting line and the cut angle to form the dovetail backcut. The starting line may be positioned about 0.6 inches (about 15.24 millimeters), plus or minus 0.065 inches (about 1.65 millimeters) from the lockwire tab end along the dovetail axis.
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