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公开(公告)号：US10107498B2
公开(公告)日：2018-10-23
申请号：US14567753
申请日：2014-12-11
Applicant: General Electric Company
Inventor： Stanley Kevin Widener , Lewis Berkley Davis, Jr. , Gregory Thomas Foster , Kaitlin Marie Graham , Krishnakumar Venkataraman
Abstract: Embodiments of the present disclosure provide injection systems for fuel and air. According to one embodiment, an injection system can include a mixing zone embedded within a surface of a turbine nozzle and positioned between a first outlet and a second outlet, the turbine nozzle separating a combustor of a power generation system from a turbine stage of the power generation system, wherein the first outlet is oriented substantially in opposition to the second outlet; a first injection conduit for delivering a carrier gas to the mixing zone through the first outlet; and a second injection conduit for delivering a fuel to the mixing zone through a second outlet; wherein the carrier gas and the fuel intermix within the mixing zone upon leaving the first injection conduit and the second injection conduit.
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公开(公告)号：US10053989B2
公开(公告)日：2018-08-21
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：US09995149B2
公开(公告)日：2018-06-12
申请号：US14143443
申请日：2013-12-30
Applicant: General Electric Company
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D5/188 , F05D2240/305 , F05D2240/306 , F05D2250/71 , F05D2250/711 , F05D2250/712 , F05D2250/713 , F05D2250/75 , F05D2260/22141 , Y02T50/676
Abstract: A turbine blade having an airfoil defined by a concave shaped pressure side outer wall and a convex shaped suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The turbine blade may further include a rib configuration that partitions the chamber into radially extending flow passages. The rib configuration may include a camber line rib having a wavy profile. The wavy profile may include at least one back-and-forth “S” shape.
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公开(公告)号：US20180135430A1
公开(公告)日：2018-05-17
申请号：US15354221
申请日：2016-11-17
Applicant: General Electric Company
Inventor： David Wayne Weber , Gregory Thomas Foster , Robert Peter Hanet
CPC classification number: F01D5/187 , B22C9/108 , B22C9/12 , B22C21/14 , F01D25/12 , F05D2220/30 , F05D2230/60
Abstract: A core for an airfoil casting, including: a cantilevered core section; and a boss extending from the cantilevered core section to an outer profile of the core.
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公开(公告)号：US20180112541A1
公开(公告)日：2018-04-26
申请号：US15334474
申请日：2016-10-26
Applicant: General Electric Company
Inventor： David Wayne Weber , Gregory Thomas Foster
CPC classification number: F01D5/187 , F01D5/147 , F01D9/041 , F02C3/04 , F05D2220/32 , F05D2240/122 , F05D2240/304 , F05D2240/35 , F05D2250/185 , F05D2260/202 , F05D2260/205
Abstract: A trailing edge cooling system for a multi-wall blade, including: a cooling circuit, including: an outward leg extending toward a trailing edge of the multi-wall blade and fluidly coupled to a coolant feed; a return leg extending away from the trailing edge of the multi-wall blade and fluidly coupled to a coolant collection passage; and a turn for coupling the outward leg and the return leg; wherein the outward leg is radially offset from the return leg along a radial axis of the multi-wall blade.
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Patent Agency Ranking
公开(公告)号：US09938836B2
公开(公告)日：2018-04-10
申请号：US14978224
申请日：2015-12-22
Applicant: General Electric Company
Inventor： David Wayne Weber , Gregory Thomas Foster , Michelle Jessica Iduate , Brendon James Leary , Aaron Ezekiel Smith
CPC classification number: F01D5/187 , F01D9/041 , F05D2220/32 , F05D2240/304 , F05D2260/20 , F05D2260/2212 , Y02T50/676
Abstract: One aspect of the disclosure provides for a turbine airfoil. The turbine airfoil may include a trailing edge having: a set of cooling channels having a first cooling channel fluidly connected to a second cooling channel; a first section having a first pin bank cooling arrangement, the first section fluidly connected to the first cooling channel; and a second section having a second pin bank cooling arrangement, the second section fluidly connected to the second cooling channel and being radially inward of the first section.
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公开(公告)号：US20170328220A1
公开(公告)日：2017-11-16
申请号：US15152707
申请日：2016-05-12
Applicant: General Electric Company
Inventor： David Wayne Weber , Gregory Thomas Foster , Michelle Jessica Iduate , Brendon James Leary , Jacob Charles Perry, II
CPC classification number: F01D5/187 , F01D5/141 , F01D5/147 , F01D9/02 , F01D25/12 , F05D2220/32 , F05D2240/305 , F05D2240/306 , F05D2250/14 , F05D2250/185 , F05D2250/711 , F05D2250/712 , F05D2260/201 , F05D2260/202 , F05D2260/22141
Abstract: An internal rib for a blade airfoil has a concave surface defined to ensure durability and provide desired heat transfer. A concave surface faces a pressure side or suction side outer wall. A width is between a first end and a second end, and a depth is a length of a normal depth line between a midpoint of the concave surface and an intersection point of the depth line with the pressure or suction side outer wall. An irregular arc is defined within an arc angle centered at the intersection point, the irregular arc has a first arc radius equivalent to the depth at the midpoint of the concave surface and a second arc radius where the arc angle intersects the concave surface equivalent to a product of the depth and a shape factor. The shape factor has a substantially linear relationship with the aspect ratio.
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公开(公告)号：US20170328219A1
公开(公告)日：2017-11-16
申请号：US15152698
申请日：2016-05-12
Applicant: General Electric Company
Inventor： Brendon James Leary , Elisabeth Kraus Black , Gregory Thomas Foster , Michelle Jessica Iduate , Jacob Charles Perry, II
CPC classification number: F01D5/187 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2250/75 , F05D2260/22141 , F05D2260/941 , Y02T50/676
Abstract: A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and forming a radially extending coolant receiving chamber. A rib partitions the radially extending chamber into a first passage on a first side of the rib and an adjacent second passage on an opposing second side of the rib. Each passage is enclosed at an end of the radially extending chamber by an end member of the radially extending chamber. A turn opening is defined in an end of the rib through which the coolant passes between the first passage and the second passage within the end member of the radially extending chamber. A bulbous projection extends along the end of the rib and on opposing radially extending sides of the turn opening to reduce stress in the rib and/or connecting fillets.
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公开(公告)号：US20170175547A1
公开(公告)日：2017-06-22
申请号：US14977247
申请日：2015-12-21
Applicant: General Electric Company
CPC classification number: F01D5/187 , F01D5/186 , F02C3/04 , F05D2220/32 , F05D2240/305 , F05D2240/307 , F05D2250/185 , F05D2260/205
Abstract: A cooling system according to an embodiment includes: a serpentine cooling circuit, the serpentine cooling circuit including a first leg extending in a first direction, a second leg extending in a second direction, and a turn fluidly coupling the first leg and the second leg; and an air feed cavity for supplying cooling air to the serpentine cooling circuit; wherein the first leg of the serpentine cooling circuit extends radially outward from and at least partially covers at least one central plenum of a multi-wall blade, and wherein the second leg of the serpentine cooling circuit extends radially outward from and at least partially covers a first set of near wall cooling channels of the multi-wall blade.
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公开(公告)号：US09669458B2
公开(公告)日：2017-06-06
申请号：US14173949
申请日：2014-02-06
Applicant: General Electric Company
Inventor： David Wayne Weber , Gregory Thomas Foster , Benjamin Paul Lacy , Aaron Ezekiel Smith , Dustin Michael Earnhardt
CPC classification number: B22C7/02 , B22C9/04 , B22C9/10 , B22C9/103 , B22C9/108 , B22C9/24 , F01D5/186 , F05D2230/211 , F05D2240/81 , F05D2260/204
Abstract: A core for forming micro channels within a turbine component is provided. The core includes a base comprising a first side and a second side; and a core assembly coupled to the second side. The core assembly further includes a plurality of channel members, wherein each channel member has a first end, a second end, and a channel body coupled to and extending between said first end and said second end. The channel body includes a channel shape configured to form the micro channels within the turbine component.
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