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公开(公告)号：US10392945B2
公开(公告)日：2019-08-27
申请号：US15599912
申请日：2017-05-19
Applicant: General Electric Company
Inventor： Sandip Dutta , Scott Francis Johnson , Joseph Anthony Weber
Abstract: The present disclosure is directed to a cooling system for a turbomachine. The cooling system includes a turbomachine component defining a turbomachine component cavity. The cooling system also includes an insert positioned within the turbomachine component cavity for cooling the turbomachine component. The insert includes an insert body and a spring body. The spring body includes a first portion fixedly coupled to the insert body, a second portion in sliding engagement with the turbomachine component, and a third portion in sliding engagement with the insert body.
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公开(公告)号：US20170101890A1
公开(公告)日：2017-04-13
申请号：US14880565
申请日：2015-10-12
Applicant: General Electric Company
Inventor： Sandip Dutta , Benjamin Paul Lacy , Joseph Anthony Weber , Peter Galen Stevens
CPC classification number: F01D25/12 , F01D9/041 , F02C3/04 , F02C7/12 , F05D2220/32 , F05D2240/128 , F05D2240/35 , F05D2240/81 , F05D2260/204 , F05D2260/221 , Y02T50/676
Abstract: A turbine nozzle includes an airfoil that extends in span from an inner band to an outer band where the inner band and the outer band define outer flow boundaries of the turbine nozzle. The inner band includes a gas side surface that is at least partially covered by one or more inner plates. The inner band also includes a plurality of cooling channels formed within the gas side surface beneath the one or more inner plates. The outer band includes a gas side surface that is at least partially covered by one or more outer plates. The outer band comprises a plurality of cooling channels formed within the gas side surface beneath the one or more outer plates.
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公开(公告)号：US10989070B2
公开(公告)日：2021-04-27
申请号：US15995072
申请日：2018-05-31
Applicant: General Electric Company
Inventor： Brad Wilson VanTassel , Evan Andrew Sewall , Joseph Anthony Weber , Travis J Packer , Joseph Daniel Franzen, Jr. , Bryan David Lewis
Abstract: A turbine having a stationary shroud ring formed about rotor blades. The stationary shroud ring may include an inner shroud segment. The inner shroud segment may include a cooling configuration that includes a crossflow channel. The crossflow channel may extend lengthwise between an upstream end and a downstream end, and, therebetween, include a junction point that divides the crossflow channel lengthwise into upstream and downstream sections, with the upstream section extending between the upstream end and the junction point, and the downstream section extending between the junction point and the downstream end. The crossflow channel may have a cross-sectional flow area that varies lengthwise such that a cross-sectional flow area of the upstream section decreases between the upstream end and the junction point, and a cross-sectional flow area of the downstream section increases between the junction point and the downstream end.
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公开(公告)号：US10052683B2
公开(公告)日：2018-08-21
申请号：US14977028
申请日：2015-12-21
Applicant: General Electric Company
Inventor： Gregory Thomas Foster , David Wayne Weber , Michelle Jessica Iduate , Brendon James Leary , Joseph Anthony Weber
CPC classification number: B22C9/103 , B22C9/108 , B22C9/12 , B22C9/24 , B22C21/14 , F01D5/187 , F05D2220/32 , F05D2230/21 , F05D2260/20 , G01B17/02 , G01B21/08
Abstract: A core for a turbine airfoil casting according to an embodiment includes: a center plenum section; and a plurality of outer passage sections; wherein the center plenum section includes at least one boss extending outwardly from the center plenum to an outer profile of the core.
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公开(公告)号：US20180112547A1
公开(公告)日：2018-04-26
申请号：US15334450
申请日：2016-10-26
Applicant: General Electric Company
Inventor： Zachary John Snider , Gregory Thomas Foster , Joseph Anthony Weber , James Fredric Wiedenhoefer
CPC classification number: F01D9/065 , F01D5/147 , F01D5/186 , F01D5/187 , F01D9/041 , F01D9/06 , F01D25/08 , F05D2220/32 , F05D2240/122 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2260/202 , F05D2260/204
Abstract: A turbine airfoil for a rotating blade or stationary nozzle vane includes an airfoil body including a leading edge and a trailing edge. A coolant supply passage extends within the airfoil body, and a coolant return passage extends within the airfoil body. A first trench is in an external surface of the airfoil body, the first trench extending to the trailing edge and being in fluid communication with the coolant supply passage. A second trench is in the external surface of the airfoil body, the second trench extending to the trailing edge and being in fluid communication with the coolant return passage and the first trench. A cover seats in the airfoil body and encloses the trenches to form coolant passages with the airfoil body. In embodiments, two coolant passages to and back from the trailing edge may be used to allow for a recycling flow.
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Patent Agency Ranking
公开(公告)号：US09932838B2
公开(公告)日：2018-04-03
申请号：US14977228
申请日：2015-12-21
Applicant: General Electric Company
CPC classification number: F01D5/187 , F02C3/04 , F05D2220/32 , F05D2240/305 , F05D2240/307 , F05D2250/185 , F05D2260/202
Abstract: A cooling system according to an embodiment includes: a three-pass serpentine cooling circuit; and an air feed cavity for supplying cooling air to the three-pass serpentine cooling circuit; wherein the three-pass serpentine cooling circuit extends radially outward from and at least partially covers at least one central plenum and a first set of near wall cooling channels of a multi-wall blade.
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公开(公告)号：US20170175541A1
公开(公告)日：2017-06-22
申请号：US14977102
申请日：2015-12-21
Applicant: General Electric Company
Inventor： David Wayne Weber , Gregory Thomas Foster , Gary Michael Itzel , Brendon James Leary , Joseph Anthony Weber
CPC classification number: F01D5/187 , F01D5/18 , F01D5/186 , F02C3/04 , F02C7/12 , F05D2220/32 , F05D2240/127 , F05D2240/307 , F05D2240/35 , F05D2260/202 , F05D2260/22141
Abstract: A cooling system according to an embodiment includes: a pin fin bank cooling circuit; and an air feed cavity for supplying cooling air to the pin fin bank cooling circuit; wherein the pin fin bank cooling circuit extends radially outward from and at least partially covers at least one central plenum of a multi-wall blade and a first set of near wall cooling channels of the multi-wall blade.
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公开(公告)号：US20170173672A1
公开(公告)日：2017-06-22
申请号：US14977028
申请日：2015-12-21
Applicant: General Electric Company
Inventor： Gregory Thomas Foster , David Wayne Weber , Michelle Jessica Iduate , Brendon James Leary , Joseph Anthony Weber
CPC classification number: B22C9/103 , B22C9/108 , B22C9/12 , B22C9/24 , B22C21/14 , F01D5/187 , F05D2220/32 , F05D2230/21 , F05D2260/20 , G01B17/02 , G01B21/08
Abstract: A core for a turbine airfoil casting according to an embodiment includes: a center plenum section; and a plurality of outer passage sections; wherein the center plenum section includes at least one boss extending outwardly from the center plenum to an outer profile of the core.
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公开(公告)号：US10815807B2
公开(公告)日：2020-10-27
申请号：US15995082
申请日：2018-05-31
Applicant: General Electric Company
Inventor： Brad Wilson VanTassel , Steven Paul Byam , Joseph Anthony Weber , Evan Andrew Sewall , Travis J Packer
Abstract: A turbine of a gas turbine engine that includes a stationary shroud ring having inner shroud segments circumferentially stacked about a hot gas path. The inner shroud segments may include a first inner shroud segment that includes: a cooling configuration having cooling channels configured to receive and direct a coolant through an interior of the first inner shroud segment, where each of the cooling channels extends lengthwise between a first end and a second end that includes an outlet formed through an exterior surface of the first inner shroud segment; a circumferential edge; a slot formed in the circumferential edge; and a sealing member positioned within the slot. The outlet of at least one of the cooling channels may be positioned within the slot.
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公开(公告)号：US10774683B2
公开(公告)日：2020-09-15
申请号：US15485536
申请日：2017-04-12
Applicant: General Electric Company
Inventor： Robert Frank Hoskin , Robert Aldo Del Freo , Joseph William Janssen , Joseph Leonard Moroso , Eric Alan Overholt , Matthew Ian Van Biervliet , Joseph Anthony Weber
Abstract: A fixture for drilling a hole in a superalloy turbine blade includes a mount to selectively hold a root of the superalloy turbine blade with the superalloy turbine blade extending from the mount. The fixture may also include an actuator to apply a force to elastically deform at least a portion of the superalloy turbine blade when held by the mount from a relaxed, initial position to an elastically deformed position, the at least a portion of the superalloy turbine blade having a curvature in the elastically deformed position not present in the relaxed, initial position. The fixture may also include a drill guide configured to guide a drilling element into the superalloy turbine blade in the elastically deformed position.
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