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公开(公告)号：US20190071976A1
公开(公告)日：2019-03-07
申请号：US15697886
申请日：2017-09-07
Applicant: General Electric Company
Inventor： Zachary Daniel Webster , Aaron Ezekiel Smith , Kirk D. Gallier
CPC classification number: F01D5/186 , F01D9/023 , F01D9/041 , F01D9/065 , F01D25/12 , F02K1/822 , F05D2220/323 , F05D2230/50 , F05D2240/11 , F05D2240/124 , F05D2240/306 , F05D2240/81 , F05D2250/73 , F05D2260/202 , F23R3/002 , F23R2900/03042
Abstract: An apparatus and method relating to a cooling hole of a component of a turbine engine. The cooling hole can extend from an inlet to an outlet to define a connecting passage. The cooling hole can contain a diffusing section. The diffusing section can be defined by an interior surface having variable geometries.
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公开(公告)号：US10208605B2
公开(公告)日：2019-02-19
申请号：US14884009
申请日：2015-10-15
Applicant: General Electric Company
Inventor： Matthew Lee Krumanaker , Steven Robert Brassfield , Robert Frederick Bergholz , Aaron Ezekiel Smith , Weston Nolan Dooley
Abstract: A turbine engine comprises an airfoil having one or more internal cooling circuits. The cooling circuits can be fed with a flow of cooling fluid from one or more cooling air inlet passages in fluid communication with the cooling circuits. The cooling circuits can provide the cooling fluid flow within the airfoil to cool the airfoil, as well as provide a cooling fluid to a plurality of film holes to create a cooling film on the external surface of the airfoil.
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公开(公告)号：US20180347375A1
公开(公告)日：2018-12-06
申请号：US15609488
申请日：2017-05-31
Applicant: General Electric Company
Inventor： Matthew Thomas Beyer , Gregory Terrence Garay , Aaron Ezekiel Smith
Abstract: An apparatus and method for cooling an airfoil tip for a turbine engine can include an airfoil, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the airfoil at the tip. A plurality of cooling holes can be provided in the tip rail at the tip. A flow of cooling fluid can be provided through the cooling holes from the interior of the airfoil to cool the tip of the airfoil.
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公开(公告)号：US10094226B2
公开(公告)日：2018-10-09
申请号：US14938261
申请日：2015-11-11
Applicant: General Electric Company
Inventor： Aaron Ezekiel Smith , Metodi Blagoev Zlatinov , Thomas Earl Dyson
IPC: F01D5/18
Abstract: A component is provided and comprises at least one wall comprising a first and a second surface. At least one film cooling hole extends through the wall between the first and second surfaces and has an outlet region at the second surface. The film cooling hole includes a first expansion section being a side diffusion portion and a second expansion section being a layback diffusion portion, wherein the side diffusion portion is upstream and spaced from the layback diffusion portion.
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公开(公告)号：US20180230812A1
公开(公告)日：2018-08-16
申请号：US15405648
申请日：2017-01-13
Applicant: General Electric Company
Inventor： Junwoo Lim , Jeffrey Douglas Rambo , Aaron Ezekiel Smith
IPC: F01D5/18
CPC classification number: F01D5/186 , F05D2220/323 , F05D2240/303 , F05D2250/10 , F05D2250/12 , F05D2250/18 , F05D2250/312 , F05D2250/324 , F05D2250/34 , F05D2250/38 , F05D2260/202 , Y02T50/676
Abstract: An apparatus and method for an engine component for a turbine engine including an exterior wall separating a hot fluid flow exterior of the engine component from a cooling fluid flow interior of the engine component. A cooling circuit can be provided within the component having a cooling passage. At least two film holes can extend through the exterior wall for providing a cooling film along the exterior of the wall. The film holes can overlap one another relative to the hot fluid flow.
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Patent Agency Ranking
公开(公告)号：US10012091B2
公开(公告)日：2018-07-03
申请号：US14818695
申请日：2015-08-05
Applicant: General Electric Company
Inventor： Victor John Morgan , George Andrew Gergely , Frederic Woodrow Roberts, Jr. , Aaron Ezekiel Smith
CPC classification number: F01D5/187 , B23P15/02 , F01D9/065 , F05D2240/81 , F05D2250/314 , F05D2250/75 , F05D2260/2212 , F05D2260/2214
Abstract: Embodiments of the present disclosure provide components for hot gas path (HGP) components and methods of forming the same. A structure according to the present disclosure can include: an HGP component extending radially from a rotor axis of a turbomachine, the HGP component including a tapered edge; a plurality of first passages in fluid communication with a preliminary cooling zone of the HGP component, and extending through a sidewall positioned between the preliminary cooling zone and the tapered edge; and a plurality of second passages extending through at least the tapered edge, wherein each of the plurality of second passages is in fluid communication with the flow path for the operative fluid and at least one passage of the plurality of first passages, and wherein at least one of the plurality of second passages is radially displaced from each passage of the plurality of first passages.
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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：US09909427B2
公开(公告)日：2018-03-06
申请号：US14978235
申请日：2015-12-22
Applicant: General Electric Company
Inventor： Aaron Ezekiel Smith , Gregory Thomas Foster , Michelle Jessica Iduate , Brendon James Leary , David Wayne Weber
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2240/304 , F05D2260/201 , F05D2260/203 , F05D2260/22141 , 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; 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; and a pressure side panel having a third pin bank cooling arrangement, the pressure side panel fluidly connected to the first cooling channel.
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公开(公告)号：US09759071B2
公开(公告)日：2017-09-12
申请号：US14143564
申请日：2013-12-30
Applicant: General Electric Company
Inventor： Lisa Anne Wichmann , Aaron Ezekiel Smith
CPC classification number: F01D5/187 , F01D5/188 , F05D2240/305 , F05D2240/306 , F05D2250/71 , F05D2250/711 , F05D2250/712 , F05D2250/713 , F05D2250/75 , F05D2260/201 , F05D2260/202 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
Abstract: A turbine blade comprising 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 that include a first flow passage and a second flow passage; and a crossover passage that fluidly connects an inlet formed in the first flow passage to an outlet formed in the second flow passage. The crossover passage may include a canted configuration relative to the second flow passage.
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公开(公告)号：US20170175548A1
公开(公告)日：2017-06-22
申请号：US14977270
申请日：2015-12-21
Applicant: General Electric Company
Inventor： Aaron Ezekiel Smith , Gregory Thomas Foster
CPC classification number: F01D5/187 , F01D5/186 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2240/35 , F05D2240/81 , F05D2250/185 , F05D2260/201 , F05D2260/202 , F05D2260/204 , Y02T50/676
Abstract: A cooling system according to an embodiment includes: a leading edge cooling circuit including a pressure side serpentine circuit and a suction side serpentine circuit; a first mid-blade cooling circuit including a suction side serpentine circuit; a second mid-blade cooling circuit including a pressure side serpentine circuit; a trailing edge cooling circuit; and at least one air feed for supplying cooling air to the leading edge cooling circuit, the first mid-blade cooling circuit, the second mid-blade cooling circuit, and the trailing edge cooling circuit.
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