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公开(公告)号：US10465527B2
公开(公告)日：2019-11-05
申请号：US15354221
申请日：2016-11-17
Applicant: General Electric Company
Inventor： David Wayne Weber , Gregory Thomas Foster , Robert Peter Hanet
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：US10450875B2
公开(公告)日：2019-10-22
申请号：US15334585
申请日：2016-10-26
Applicant: General Electric Company
Inventor： David Wayne Weber , Sandip Dutta , Brendon James Leary
IPC: F01D5/18
Abstract: Various geometries for a trailing edge cooling system for a turbine blade. The trailing edge cooling system may include a plurality of cooling circuits extending at least partially along a radial length of a trailing edge of the turbine blade. Each cooling circuit may include an outward leg extending axially toward the trailing edge, and a plurality of turn legs in fluid communication with the outward leg. The plurality of turn legs may be positioned adjacent the trailing edge. Each cooling circuit may also include a return leg positioned adjacent the outward leg and extending axially from the trailing edge. The return leg may include a first portion and a second portion. The first portion may have a first width, and a second may have a second width that is greater than the first width of the first portion.
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公开(公告)号：US10352176B2
公开(公告)日：2019-07-16
申请号：US15334474
申请日：2016-10-26
Applicant: General Electric Company
Inventor： David Wayne Weber , Gregory Thomas Foster
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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公开(公告)号：US10273810B2
公开(公告)日：2019-04-30
申请号：US15334501
申请日：2016-10-26
Applicant: General Electric Company
Inventor： David Wayne Weber , Brendon James Leary
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：US10221696B2
公开(公告)日：2019-03-05
申请号：US15239930
申请日：2016-08-18
Applicant: General Electric Company
Inventor： David Wayne Weber , Lana Maria Osusky
Abstract: A cooling circuit for a multi-wall blade according to an embodiment includes: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a central cavity disposed between the pressure side and suction side cavities, the central cavity including no surfaces adjacent the pressure and suction sides of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade, the first leading edge cavity located forward of the central cavity; a second leading edge cavity located forward of the first leading edge cavity; at least one impingement opening for fluidly coupling the first leading edge cavity to the second leading edge cavity; and at least one channel for fluidly coupling the central cavity to a tip of the multi-wall blade.
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Patent Agency Ranking
66.发明申请公开(公告)号：US20190063231A1
公开(公告)日：2019-02-28
申请号：US16170523
申请日：2018-10-25
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, the pressure side, the 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：US20190017389A1
公开(公告)日：2019-01-17
申请号：US15648564
申请日：2017-07-13
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Thomas Earl Dyson , Brendon James Leary , Gregory Terrence Garay , Gustavo Adolfo Ledezma , David Wayne Weber , Aaron Ezekiel Smith
IPC: F01D5/18
Abstract: An apparatus and method for cooling an airfoil tip for a turbine engine can include a blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall (94) enclosing an interior for the airfoil at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the airfoil to cool the tip of the airfoil.
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公开(公告)号：US09976425B2
公开(公告)日：2018-05-22
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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公开(公告)号：US20180112540A1
公开(公告)日：2018-04-26
申请号：US15334471
申请日：2016-10-26
Applicant: General Electric Company
Inventor： Robert Frank Hoskin , David Wayne Weber , Gregory Thomas Foster
CPC classification number: F01D5/187 , F01D5/147 , F05D2230/22 , F05D2230/237 , F05D2240/304 , F05D2260/202
Abstract: An edge coupon for an airfoil is provided. The coupon includes: a coupon body including: a coolant feed; an outward leg extending toward an edge of the coupon and fluidly coupled to the coolant feed; a return leg extending away from the edge of the coupon and radially offset from the outward leg along a radial axis of the coupon; a turn for fluidly coupling the outward leg and the return leg; a collection passage fluidly coupled to the return leg; and a coupling region configured to mate with an airfoil body of the airfoil.
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公开(公告)号：US20180112539A1
公开(公告)日：2018-04-26
申请号：US15334454
申请日：2016-10-26
Applicant: General Electric Company
Inventor： David Wayne Weber , Robert Peter Hanet , Gregory Thomas Foster , Brendon James Leary
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 set of outward legs extending toward a trailing edge of the multi-wall blade and fluidly coupled to a coolant feed; a set of return legs extending away from the trailing edge of the multi-wall blade and fluidly coupled to a coolant collection passage; and a connecting system for fluidly coupling the set of outward legs and the set of return legs; wherein the set of outward legs is radially offset from the set of return legs along a radial axis of the multi-wall blade.
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