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公开(公告)号：US20230167742A1
公开(公告)日：2023-06-01
申请号：US17537818
申请日：2021-11-30
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Thomas William Vandeputte
CPC classification number: F01D5/141 , F01D5/18 , F05D2220/30 , F05D2260/20 , F05D2230/60
Abstract: An apparatus and method for an engine component having a working airflow separated into a cooling airflow and a combustion airflow, the engine component comprising a plurality of circumferentially spaced airfoils rotatable about a centerline defining an axial direction, each airfoil comprising an outer wall bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip along a span-wise direction to define a span length; wherein each of the airfoils have an unguided turning angle to stagger angle ratio defined with respect to a percentage of the span length.
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公开(公告)号：US12228048B2
公开(公告)日：2025-02-18
申请号：US18487495
申请日：2023-10-16
Applicant: GENERAL ELECTRIC COMPANY
Abstract: A turbine engine includes a compressor section, a combustion section, and a turbine section, and an airfoil with an outer wall defining a pressure side and a suction side and extending between a leading edge and a trailing edge to define a mean camber line. A first thickness is defined between the pressure side and the suction side at a first location along the mean camber line.
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公开(公告)号：US11939880B1
公开(公告)日：2024-03-26
申请号：US17980134
申请日：2022-11-03
Applicant: General Electric Company
Inventor： Paul Hadley Vitt , Matthew Brian Surprenant , Brian David Keith , Prem Venugopal , Thomas William Vandeputte
CPC classification number: F01D5/02 , F01D5/14 , F05D2220/30
Abstract: A turbine engine stage includes a plurality of airfoils extending between an inner band and an outer band. Each airfoil in the plurality of airfoils can have an outer wall defining a pressure side and a suction side, with the outer wall extending between a leading edge and a trailing edge. An intervening flow passage is defined between two adjacent airfoils in the plurality of airfoils.
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公开(公告)号：US20240068370A1
公开(公告)日：2024-02-29
申请号：US17894307
申请日：2022-08-24
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F01D5/18 , F02C7/12 , F05D2260/20
Abstract: A turbine engine includes a compressor section, a combustion section, and a turbine section, and an airfoil with an outer wall defining a pressure side and a suction side and extending between a leading edge and a trailing edge to define a mean camber line. A first thickness is defined between the pressure side and the suction side at a first location along the mean camber line.
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公开(公告)号：US10465520B2
公开(公告)日：2019-11-05
申请号：US15217012
申请日：2016-07-22
Applicant: General Electric Company
Inventor： Thomas William Vandeputte
IPC: F01D5/14 , F01D9/04 , B23K26/342 , B23K15/00 , F01D9/06 , B33Y50/02 , B33Y80/00 , B29L31/08 , B23K101/00 , B23K103/18
Abstract: A blade includes an airfoil body defined by a concave pressure side outer wall and a convex suction side outer wall that connect along a leading edge and a trailing edge. The blade also includes a first corrugated surface extending from the trailing edge to the leading edge on an outer surface of the concave pressure side outer wall, and/or a second corrugated surface extending from the trailing edge to the leading edge on an outer surface of the convex suction side outer wall. The blade acts to reduce flow velocity losses associated with wake mixing by accelerating the mixing process from the source of the wake to minimize inflated unsteady mixing that occurs within a downstream blade row.
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Patent Agency Ranking
公开(公告)号：US09995166B2
公开(公告)日：2018-06-12
申请号：US14550506
申请日：2014-11-21
Applicant: General Electric Company
Inventor： Thomas William Vandeputte
CPC classification number: F01D17/162 , F01D5/145 , F01D9/045 , F05D2240/125
Abstract: A vane for a turbomachine includes a pressure surface and a suction surface opposite the pressure surface. The pressure surface and the suction surface define a width therebetween. The vane also includes a first end. The first end includes a distal portion, a proximal portion, a pressure surface first portion, and a suction surface first portion. At least one of the pressure surface first portion and the suction surface first portion slope away from the other of the pressure surface first portion and the suction surface first portion such that the width increases from a first end minimum width at the proximal portion to a first end maximum width at the distal portion.
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公开(公告)号：US12196087B2
公开(公告)日：2025-01-14
申请号：US17859456
申请日：2022-07-07
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Valeria Andreoli , Shashwat Swami Jaiswal , Thomas William Vandeputte
Abstract: A blade assembly for a gas turbine engine having an engine casing, with the blade assembly being configured to rotate about a rotational axis. The blade assembly having a blade, and at least one fin. The blade extending between a root and a tip, with the tip being spaced radially from the engine casing to define a space therebetween. The at least one fin extending radially with respect to the tip and into the space.
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公开(公告)号：US20240011407A1
公开(公告)日：2024-01-11
申请号：US17859456
申请日：2022-07-07
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Valeria Andreoli , Shashwat Swami Jaiswal , Thomas William Vandeputte
IPC: F01D11/02
CPC classification number: F01D11/02 , F05D2220/32 , F05D2240/30 , F05D2240/55
Abstract: A blade assembly for a gas turbine engine having an engine casing, with the blade assembly being configured to rotate about a rotational axis. The blade assembly having a blade, and at least one fin. The blade extending between a root and a tip, with the tip being spaced radially from the engine casing to define a space therebetween. The at least one fin extending radially with respect to the tip and into the space.
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公开(公告)号：US11795824B2
公开(公告)日：2023-10-24
申请号：US17537818
申请日：2021-11-30
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Thomas William Vandeputte
CPC classification number: F01D5/141 , F01D5/18 , F05D2220/30 , F05D2230/60 , F05D2260/20
Abstract: An apparatus and method for an engine component having a working airflow separated into a cooling airflow and a combustion airflow, the engine component comprising a plurality of circumferentially spaced airfoils rotatable about a centerline defining an axial direction, each airfoil comprising an outer wall bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip along a span-wise direction to define a span length; wherein each of the airfoils have an unguided turning angle to stagger angle ratio defined with respect to a percentage of the span length.
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公开(公告)号：US20250067193A1
公开(公告)日：2025-02-27
申请号：US18938401
申请日：2024-11-06
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Valeria Andreoli , Shashwat Swami Jaiswal , Thomas William Vandeputte
Abstract: A blade assembly for a gas turbine engine having an engine casing, with the blade assembly being configured to rotate about a rotational axis. The blade assembly having a blade, and at least one fin. The blade extending between a root and a tip, with the tip being spaced radially from the engine casing to define a space therebetween. The at least one fin extending radially with respect to the tip and into the space.
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