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公开(公告)号：US20180355727A1
公开(公告)日：2018-12-13
申请号：US15620896
申请日：2017-06-13
Applicant: General Electric Company
Inventor： Jalindar Appa Walunj , Shashwat Swami Jaiswal , Stephen Paul Wassynger , Xiuzhang James Zhang
Abstract: A blade for a turbomachine includes an airfoil extending radially between a root and a tip with a tip shroud coupled to the tip of the airfoil. The tip shroud includes a platform having an outer surface extending generally perpendicular to the airfoil. The tip shroud also includes a forward rail extending radially outward from the outer surface of the platform. The forward rail is oriented generally perpendicular to a hot gas path of the turbomachine. A cooling cavity is defined in a central portion of the platform. The tip shroud also includes a cooling channel extending between the cooling cavity and an ejection slot formed in the forward rail. The ejection slot is positioned radially outward of the outer surface of the platform of the tip shroud.
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公开(公告)号：US20170175536A1
公开(公告)日：2017-06-22
申请号：US14974193
申请日：2015-12-18
Applicant: General Electric Company
Inventor： Shashwat Swami Jaiswal , Rohit Chouhan
CPC classification number: F01D5/187 , F01D5/147 , F01D5/225 , F05D2220/32 , F05D2240/305 , F05D2240/306 , F05D2250/711 , F05D2250/712 , F05D2260/20 , F05D2260/202 , Y02T50/671 , Y02T50/673 , Y02T50/676
Abstract: A turbine rotor blade that includes an airfoil defined between a concave pressure face and a laterally opposed convex suction face, and a cooling configuration that includes a cooling channel for receiving and directing a coolant through an interior of the rotor blade. The cooling channel may include fluidly connected segments, in which: a supply segment extends radially through the airfoil; an outlet segment discharges the coolant from the rotor blade at a shallow angle relative to a flow direction of a working fluid through the turbine; and an elbow segment connects the supply segment to the outlet segment and is positioned near the outboard tip of the airfoil. The elbow segment may be configured for accommodating a change of direction between the supply segment and the outlet segment.
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公开(公告)号：US20170114647A1
公开(公告)日：2017-04-27
申请号：US14923693
申请日：2015-10-27
Applicant: General Electric Company
Inventor： Rohit Chouhan , Shashwat Swami Jaiswal , Gunnar Leif Siden , Zachary James Taylor
Abstract: A turbine bucket according to embodiments includes: a base; a blade coupled to base and extending radially outward from base, blade including: a body having: a pressure side; a suction side opposing pressure side; a leading edge between pressure side and suction side; and a trailing edge between pressure side and suction side on a side opposing leading edge; and a plurality of radially extending cooling passageways within body; and a shroud coupled to blade radially outboard of blade, shroud including: a plurality of radially extending outlet passageways fluidly connected with a first set of the plurality of radially extending cooling passageways within body; and an outlet path extending at least partially circumferentially through shroud and fluidly connected with all of a second, distinct set of the plurality of radially extending cooling passageways within body.
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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：US12083597B2
公开(公告)日：2024-09-10
申请号：US17978777
申请日：2022-11-01
Applicant: General Electric Company
Inventor： James J. Murray , Shashwat Swami Jaiswal , Rajesh Kumar Venkata Gadamsetty , Hiteshkumar Rameshchandra Mistry
Abstract: A gas manifold for single-nozzle deposition chambers comprising a base having a top surface and bottom surface defining a thickness; a primary nozzle having an inlet and outlet extending through the thickness of the base; and a secondary nozzle having an inlet extending partially through the top surface of the base and at least one channel extending a distance from a sidewall of the base having an outlet, the channel in fluid communication with the inlet of the secondary nozzle. The inlet of the primary nozzle has a hollow protrusion extending from the top surface of the base into the gas feed. The channel of the secondary nozzle includes a bend between the sidewall of the base and the outlet configured to pass between a first direct energy source and second direct energy source, the first energy source and second energy source disposed on a top wall of a chamber.
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Patent Agency Ranking
公开(公告)号：US20240139819A1
公开(公告)日：2024-05-02
申请号：US17978777
申请日：2022-11-01
Applicant: General Electric Company
Inventor： James J. Murray , Shashwat Swami Jaiswal , Rajesh Kumar Venkata Gadamsetty , Hiteshkumar Rameshchandra Mistry
Abstract: A gas manifold for single-nozzle deposition chambers comprising a base having a top surface and bottom surface defining a thickness; a primary nozzle having an inlet and outlet extending through the thickness of the base; and a secondary nozzle having an inlet extending partially through the top surface of the base and at least one channel extending a distance from a sidewall of the base having an outlet, the channel in fluid communication with the inlet of the secondary nozzle. The inlet of the primary nozzle has a hollow protrusion extending from the top surface of the base into the gas feed. The channel of the secondary nozzle includes a bend between the sidewall of the base and the outlet configured to pass between a first direct energy source and second direct energy source, the first energy source and second energy source disposed on a top wall of a chamber.
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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：US10704406B2
公开(公告)日：2020-07-07
申请号：US15620896
申请日：2017-06-13
Applicant: General Electric Company
Inventor： Jalindar Appa Walunj , Shashwat Swami Jaiswal , Stephen Paul Wassynger , Xiuzhang James Zhang
Abstract: A blade for a turbomachine includes an airfoil extending radially between a root and a tip with a tip shroud coupled to the tip of the airfoil. The tip shroud includes a platform having an outer surface extending generally perpendicular to the airfoil. The tip shroud also includes a forward rail extending radially outward from the outer surface of the platform. The forward rail is oriented generally perpendicular to a hot gas path of the turbomachine. A cooling cavity is defined in a central portion of the platform. The tip shroud also includes a cooling channel extending between the cooling cavity and an ejection slot formed in the forward rail. The ejection slot is positioned radially outward of the outer surface of the platform of the tip shroud.
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公开(公告)号：US10156145B2
公开(公告)日：2018-12-18
申请号：US14923697
申请日：2015-10-27
Applicant: General Electric Company
Inventor： Rohit Chouhan , Shashwat Swami Jaiswal , Stephen Paul Wassynger
Abstract: A turbine bucket according to various embodiments includes: a base; a blade coupled to the base and extending radially outward from the base, the blade including: a body having: a pressure side; a suction side opposing the pressure side; a leading edge between the pressure side and the suction side; and a trailing edge between the pressure side and the suction side on a side opposing the leading edge; a plurality of radially extending cooling passageways within the body; and at least one bleed aperture fluidly coupled with at least one of the plurality of radially extending cooling passageways, the at least one bleed aperture extending through the body at the trailing edge; and a shroud coupled to the blade radially outboard of the blade.
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公开(公告)号：US20170175535A1
公开(公告)日：2017-06-22
申请号：US14974155
申请日：2015-12-18
Applicant: General Electric Company
Inventor： Rohit Chouhan , Randall Richard Good , Hiteshkumar Rameshchandra Mistry , Shashwat Swami Jaiswal
CPC classification number: F01D5/18 , F01D5/187 , F01D5/20 , F01D5/225 , F05D2220/32 , F05D2240/307 , F05D2240/55 , F05D2260/20 , F05D2260/202 , Y02T50/671 , Y02T50/673 , Y02T50/676
Abstract: A turbine rotor blade that includes: an airfoil defined between a pressure face and a suction face; a tip shroud that includes a seal rail projecting from an outboard surface and, formed thereon, a cutter tooth; and a cooling configuration that includes a cooling channel for receiving and directing a coolant through an interior of the rotor blade. The cooling channel may include fluidly connected segments, in which: a supply segment extends radially through the airfoil; a cutter tooth segment is formed within the cutter tooth of the seal rail; and branching segments formed within at least one of the tip shroud and an outboard region of the airfoil. Each of the branching segments may extend between an upstream port, which connects to the cutter tooth segment, and an outlet port, which is formed on a target surface area, so that the branching segment bisects a target interior region.
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