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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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42.发明申请公开(公告)号：US20180112535A1
公开(公告)日：2018-04-26
申请号：US15334501
申请日：2016-10-26
Applicant: General Electric Company
Inventor： David Wayne Weber , Brendon James Leary
CPC classification number: F01D5/186 , F01D5/188 , F01D9/065 , F05D2220/32 , F05D2240/122 , F05D2240/123 , F05D2240/124 , F05D2240/304 , F05D2240/305 , F05D2240/306 , F05D2260/202
Abstract: A turbine blade airfoil including cooling circuits is disclosed. The airfoil may include a first pressure side cavity positioned adjacent a pressure side of the airfoil, where the first pressure side cavity is configured to receive a coolant. The airfoil may also include at least one distinct pressure side cavity positioned adjacent to and fluidly coupled to the first pressure side cavity, a trailing edge positioned between the pressure and a suction side, and a trailing edge cooling system positioned adjacent the trailing edge and in direct fluid communication with the first pressure side cavity. The trailing edge cooling system may be configured to receive a portion of the coolant from the first pressure side cavity.
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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：US20180051577A1
公开(公告)日：2018-02-22
申请号：US15239994
申请日：2016-08-18
Applicant: General Electric Company
CPC classification number: F01D5/187 , F01D9/041 , F01D25/12 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2240/81 , F05D2250/185 , F05D2260/201 , F05D2260/202
Abstract: A cooling system for a turbomachine blade including a multi-wall blade and a platform. A cooling circuit for the multi-wall blade includes: a central cavity and a plurality of outer cavities, wherein the central cavity comprises an intermediate passage of the cooling circuit, and wherein a flow of cooling air is fed into the cooling circuit through a first outer cavity of the plurality of outer cavities; and a connection for fluidly connecting a second outer cavity of the plurality of outer cavities to a platform core of the platform, the flow of cooling air passing through the connection into the platform core of the platform.
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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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Patent Agency Ranking
46.发明申请公开(公告)号：US20170328211A1
公开(公告)日：2017-11-16
申请号：US15152684
申请日：2016-05-12
Applicant: General Electric Company
Inventor： Brendon James Leary , Gregory Thomas Foster, II , Michelle Jessica Iduate , David Wayne Weber
CPC classification number: F01D5/186 , F01D5/187 , F01D9/02 , F01D9/065 , F01D25/12 , F05D2220/32 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2250/184 , F05D2250/71 , F05D2250/711 , F05D2250/712 , F05D2260/201 , F05D2260/22141 , Y02T50/676
Abstract: A turbine blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and form a radially extending chamber for receiving a coolant flow. A rib configuration may include: a leading edge transverse rib connecting to the pressure side outer wall and the suction side outer wall and partitioning a leading edge passage from the radially extending chamber. The rib configuration may also include a first center transverse rib connecting to the pressure side outer wall and the suction side outer wall and partitioning an intermediate passage from the radially extending chamber directly aft of the leading edge passage. The intermediate passage is defined by the pressure side outer wall, the suction side outer wall, the leading edge transverse rib and the first center transverse rib, and thus spans airfoil between its outer walls.
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47.发明申请公开(公告)号：US20170226870A1
公开(公告)日：2017-08-10
申请号：US15019487
申请日：2016-02-09
Applicant: General Electric Company
Inventor： Neil Ristau , Zachary James Taylor , David Wayne Weber
CPC classification number: F01D5/187 , F01D5/141 , F01D5/143 , F01D5/145 , F01D5/225 , F05D2220/32 , F05D2240/307 , F05D2250/74 , Y02E20/16 , Y02T50/673
Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge; and a tip shroud connected with a second end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, the tip shroud including a tip shroud fillet connecting the airfoil and the tip shroud and having a non-uniform thickness across an axial length of the airfoil.
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公开(公告)号：US09713838B2
公开(公告)日：2017-07-25
申请号：US13893508
申请日：2013-05-14
Applicant: General Electric Company
Inventor： David Wayne Weber , Dustin Michael Earnhardt , Michelle Jessica Rogers
CPC classification number: B22C21/14 , B22C9/108 , F01D5/187 , F01D25/12 , F05D2230/21 , Y10T428/12361 , Y10T428/24273
Abstract: A core tie having a varying cross sectional diameter, a component including such a core tie, and a method of casting a hot gas path component for a turbomachine are provided herein. In an embodiment, the core tie includes a tie member having an axial length; and a cross sectional diameter which varies along the axial length of the tie member. A variation in the cross sectional diameter of the tie member positively secures a position of the core tie relative to the core.
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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：US20170175542A1
公开(公告)日：2017-06-22
申请号：US14977124
申请日：2015-12-21
Applicant: General Electric Company
Inventor： David Wayne Weber , Mehmet Suleyman Ciray , Jacob Charles Perry, II
CPC classification number: F01D5/187 , F01D5/147 , F05D2220/30 , F05D2240/127 , F05D2250/185 , F05D2260/22141
Abstract: A turbine blade cooling system according to an embodiment includes: a first turn for redirecting a first flow of gas flowing through a first channel of a turbine blade into a central plenum of the turbine blade; and a second turn for redirecting a second flow of gas flowing through a second channel of the turbine blade into the central plenum; wherein the first turn is offset from the second turn to reduce impingement of the first flow of gas and the second flow of gas in the central plenum.
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