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公开(公告)号：US11759861B2
公开(公告)日：2023-09-19
申请号：US17232467
申请日：2021-04-16
Applicant: General Electric Company , Concept Laser GmbH
Inventor： Eric Edward Halla , Ramakrishna Venkata Mallina , Kishore Ramakrishnan , Shashwat Swami Jaiswal , Mohammed Mounir Shalaby , Adam Garret Susong , Peter Pontiller-Schymura
Abstract: A build unit for additively manufacturing three-dimensional objects may include an energy beam system having one or more irradiation devices respectively configured to direct one or more energy beams onto a region of a powder bed, and an inertization system including an irradiation chamber defining an irradiation plenum, one or more supply manifolds, and a return manifold. The one or more supply manifolds may include a downflow manifold configured to provide a downward flow of a process gas through at least a portion of the irradiation plenum defined by the irradiation chamber, and/or a crossflow manifold configured to provide a lateral flow of the process gas through at least a portion of the irradiation plenum defined by the irradiation chamber. The return manifold may evacuate or otherwise remove process gas from the irradiation plenum defined by the irradiation chamber.
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公开(公告)号：US11078797B2
公开(公告)日：2021-08-03
申请号：US16683659
申请日：2019-11-14
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：US09885243B2
公开(公告)日：2018-02-06
申请号：US14923685
申请日：2015-10-27
Applicant: General Electric Company
Inventor： Rohit Chouhan , Shashwat Swami Jaiswal , Zachary James Taylor
CPC classification number: F01D5/18 , F01D5/02 , F01D5/187 , F01D5/225 , F01D9/02 , F01D11/08 , F01D17/105 , F05D2220/32 , F05D2260/20
Abstract: A turbine bucket according to embodiments includes: a base; a blade coupled to the base, extending radially outward from the base, and 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; and a plurality of radially extending cooling passageways within the body; and a shroud coupled to the blade radially outboard of the blade, including: a plurality of radially extending outlet passageways fluidly connected with a first set of the plurality of radially extending cooling passageways within the body; and an outlet path extending at least partially circumferentially through the shroud and fluidly connected with all of a second, distinct set of the plurality of radially extending cooling passageways within the body.
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公开(公告)号：US20170138203A1
公开(公告)日：2017-05-18
申请号：US14942350
申请日：2015-11-16
Applicant: General Electric Company
Inventor： Shashwat Swami Jaiswal , Rohit Chouhan
CPC classification number: F01D5/187 , F01D5/186 , F01D5/225 , F05D2220/30 , F05D2230/10 , F05D2230/60 , F05D2240/30 , F05D2260/202
Abstract: A rotor blade includes an airfoil portion that extends in a radial direction from a root end to a tip end. A plurality of internal airfoil cooling passages is defined in the airfoil portion. The rotor blade also includes a tip shroud. The tip shroud includes a shroud plate coupled to the tip end. A plurality of tip shroud cooling passages is defined within the shroud plate. Each of the tip shroud cooling passages extends within the shroud plate in a direction generally transverse to the radial direction. Each tip shroud passage includes an inlet coupled in flow communication with at least one of the airfoil cooling passages, and an exit opening defined in, and extending therethrough, a radially outer surface of the tip shroud. The exit opening is coupled in flow communication with the inlet.
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公开(公告)号：US20170058680A1
公开(公告)日：2017-03-02
申请号：US14843069
申请日：2015-09-02
Applicant: General Electric Company
Inventor： Rohit Chouhan , Shashwat Swami Jaiswal
CPC classification number: F01D5/20 , F01D5/18 , F05D2220/32 , F05D2240/306 , F05D2240/307 , F05D2260/221 , Y02T50/673
Abstract: A rotor blade for a turbine of a gas turbine system. The rotor blade may include: an airfoil that includes a pressure sidewall and a suction sidewall defining an outer periphery, wherein the pressure sidewall and suction sidewall of the airfoil connect along a leading edge and a trailing edge; a tip that defines an outer radial end of the airfoil, wherein the tip included a cap on which an outboard projecting rail defines a tip cavity; and a rail gap formed through an aftward section of the rail.
Abstract translation: 一种用于燃气轮机系统的涡轮的转子叶片。 转子叶片可以包括：翼型件，其包括压力侧壁和限定外周边的吸力侧壁，其中翼型件的压力侧壁和抽吸侧壁沿着前缘和后缘连接; 限定所述翼型件的外径向端部的尖端，其中所述尖端包括盖，所述外侧突出轨道限定在所述顶盖腔体上; 以及通过轨道的后部形成的轨道间隙。
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Patent Agency Ranking
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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公开(公告)号：US20200095871A1
公开(公告)日：2020-03-26
申请号：US16683659
申请日：2019-11-14
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：US10247013B2
公开(公告)日：2019-04-02
申请号：US14974193
申请日：2015-12-18
Applicant: General Electric Company
Inventor： Shashwat Swami Jaiswal , Rohit Chouhan
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：US20160258301A1
公开(公告)日：2016-09-08
申请号：US14638531
申请日：2015-03-04
Applicant: General Electric Company
Inventor： Rohit Chouhan , Shashwat Swami Jaiswal
CPC classification number: F01D5/20 , F01D5/18 , F02C3/04 , F05D2220/32 , F05D2240/307 , F05D2240/35 , F05D2250/121 , F05D2250/141 , F05D2260/20
Abstract: A turbine rotor blade includes a tip portion having a pressure tip wall and a suction tip wall, a tip leading edge and a tip trailing edge. Also included is a squealer cavity at least partially defined by the pressure tip wall and the suction tip wall. Further included is at least one hole defined by the suction tip wall, the at least one hole configured to bleed a cooling flow out of the squealer cavity into a hot gas path to reduce pressure within the squealer cavity. Yet further included is a main body having a suction side wall and a pressure side wall each extending from a root portion of the turbine rotor blade to the tip portion.
Abstract translation: 涡轮转子叶片包括具有压力顶端壁和吸力端壁，尖端前缘和尖端后缘的尖端部分。 还包括至少部分地由压力顶端壁和吸力端壁限定的尖叫腔。 进一步包括至少一个由吸力端壁限定的孔，所述至少一个孔被配置为将冷却流体从呼吸器腔排出到热气体路径中，以减小鸣叫器腔内的压力。 另外还有一个主体，其具有吸力侧壁和压力侧壁，每个侧壁从涡轮转子叶片的根部延伸到顶端部分。
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公开(公告)号：US20240198425A1
公开(公告)日：2024-06-20
申请号：US18590325
申请日：2024-02-28
Applicant: General Electric Company , Concept Laser GmbH
Inventor： Eric Edward Halla , Ramakrishna Venkata Mallina , Kishore Ramakrishnan , Shashwat Swami Jaiswal , Mohammed Mounir Shalaby , Peter Pontiller-Schymura
CPC classification number: B22F10/77 , B22F10/28 , B22F12/33 , B22F12/70 , B33Y10/00 , B33Y30/00 , B33Y40/00 , B22F2201/10
Abstract: A build unit for additively manufacturing three-dimensional objects may include an energy beam system, an irradiation chamber, an inertization system having a return manifold configured to evacuate a process gas from the irradiation chamber. The return manifold includes a plurality of return manifold bodies and return manifold inlet disposed at a bottom of the irradiation chamber. The plurality of return manifold bodies includes one or more return manifold pathways downstream of the return manifold inlet. The plurality of return manifold bodies also includes one or more recapture pathways positioned to receive the process gas into the one or more return manifold pathways that flows past the return manifold inlet.
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