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公开(公告)号：US20240301799A1
公开(公告)日：2024-09-12
申请号：US18118365
申请日：2023-03-07
Applicant: Raytheon Technologies Corporation
Inventor： Brandon W. Spangler
CPC classification number: F01D5/20 , F01D5/187 , F05D2240/305 , F05D2240/306 , F05D2240/307 , F05D2260/202
Abstract: A blade for a gas turbine engine, including: an airfoil having a leading edge, a pressure side, a suction side and a trailing edge that extend to a tip of the airfoil; a leading edge cavity located within the airfoil; at least one main body cavity located within the airfoil; pressure side skin core passages located within the airfoil; suction side skin core passages located within the airfoil, the at least one main body cavity being fluidly isolated from the pressure side skin core passages and the suction side skin core passages and the at least one main body cavity being located between the pressure side skin core passages and the suction side skin core passages; a trailing edge feed cavity located within the airfoil; and a tip plenum located proximate to the tip of the airfoil, the tip plenum being fluidly coupled to the at least one main body cavity, wherein the tip plenum is located above the pressure side skin core passages and the trailing edge feed cavity and extends to the trailing edge of the airfoil.
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公开(公告)号：US20180216237A1
公开(公告)日：2018-08-02
申请号：US15419705
申请日：2017-01-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Daniel V. Viens , Michael Paul Humbert , Joseph V. Mantese , Raja Kountanya
CPC classification number: C23C24/10 , B23K13/01 , B23K26/34 , C23C26/00 , F01D5/147 , F05D2220/32 , F05D2230/30 , F05D2240/303 , F05D2240/305
Abstract: A method for forming an abrasive surface includes utilizing an energy source to form a melt pool layer in a substrate and applying abrasive grit into the melt pool layer. A method for forming an abrasive surface including applying an abrasive grit to a substrate and utilizing an energy source to form a melt pool layer in the substrate without disturbing the abrasive grit such that the abrasive grit becomes embedded in the melt pool layer.
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公开(公告)号：US09970302B2
公开(公告)日：2018-05-15
申请号：US14739944
申请日：2015-06-15
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , Srikanth Chandrudu Kottilingam , Carlos Miguel Miranda , Gary Michael Itzel
CPC classification number: F01D5/187 , F01D5/147 , F01D5/186 , F01D5/288 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/122 , F05D2240/304 , F05D2240/305 , F05D2240/306 , F05D2260/202 , F05D2260/204 , Y02T50/672 , Y02T50/676
Abstract: A hot gas path component includes a substrate having an outer surface and an inner surface. The inner surface defines an interior space. The outer surface defines a pressure side surface and a suction side surface. The pressure and suction side surfaces are joined together at a leading edge and at a trailing edge. A first cooling passage is formed in the suction side surface of the substrate. It is coupled in flow communication to the interior space. A second cooling passage, separate from the first cooling passage, is formed in the pressure side surface. The second cooling passage is coupled in flow communication to the interior space. A cover is disposed over at least a portion of the first and second cooling passages. The interior space channels a cooling fluid to the first and second cooling passages, which channel the cooling fluid therethrough to remove heat from the component.
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公开(公告)号：US20180087526A1
公开(公告)日：2018-03-29
申请号：US15280957
申请日：2016-09-29
Applicant: General Electric Company
Inventor： Sunil Rajagopal , Michael James Dutka
CPC classification number: F04D29/384 , F01D5/141 , F02C3/04 , F04D29/324 , F04D29/544 , F05D2220/32 , F05D2220/3216 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2250/74 , Y02T50/673
Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
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公开(公告)号：US20180087525A1
公开(公告)日：2018-03-29
申请号：US15280943
申请日：2016-09-29
Applicant: General Electric Company
Inventor： Paul G. Deivernois , Sunil Rajagopal
CPC classification number: F04D29/384 , F01D5/141 , F02C3/04 , F04D29/324 , F04D29/544 , F05D2220/3216 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2250/74 , Y02T50/673
Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
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Patent Agency Ranking
公开(公告)号：US09926788B2
公开(公告)日：2018-03-27
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：US20180080475A1
公开(公告)日：2018-03-22
申请号：US15272716
申请日：2016-09-22
Applicant: General Electric Company
Inventor： Marc Edward Blohm , Sunil Rajagopal
CPC classification number: F04D29/544 , F02C3/04 , F04D29/324 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2250/74 , Y02T50/673
Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
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公开(公告)号：US20180073373A1
公开(公告)日：2018-03-15
申请号：US15560234
申请日：2016-03-22
Applicant: SAFRAN , SAFRAN AIRCRAFT ENGINES
Inventor： Sylvain PAQUIN , Charlotte Marie DUJOL , Patrice ENEAU , Hugues Denis JOUBERT , Adrien Bernard Vincent ROLLINGER
CPC classification number: F01D5/284 , B22C9/04 , B22C9/10 , F01D5/18 , F01D5/187 , F05D2230/21 , F05D2230/211 , F05D2240/305 , F05D2300/20
Abstract: A ceramic core used for fabricating a hollow turbine blade for a turbine engine by using the lost-wax casting technique and shaped to constitute the cavities of the blade as a single element, includes, in order to feed the insides of these cavities jointly with cooling air, core portions that are to form first and second lateral cavities and that are connected to a core portion that is to form at least one central cavity, firstly in the core root via at least two ceramic junctions, and secondly at various heights up the core via a plurality of other ceramic junctions of positioning that defines the thickness of the internal partitions of the blade, while also ensuring additional cooling air for predetermined critical zones of the first and second lateral cavities.
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公开(公告)号：US09869324B2
公开(公告)日：2018-01-16
申请号：US14858155
申请日：2015-09-18
Applicant: Sharp Kabushiki Kaisha
Inventor： Yukishige Shiraichi , Masaki Ohtsuka
IPC: F04D29/24 , F04D29/28 , F04D29/26 , F04D29/38 , F04D29/30 , F04D17/04 , F04D29/66 , B29C45/26 , F04D17/10 , F04D25/02 , F04D29/42 , F04D17/08 , B29L31/08
CPC classification number: F04D29/281 , B29C45/26 , B29L2031/08 , F04D17/04 , F04D17/08 , F04D17/10 , F04D25/02 , F04D29/26 , F04D29/282 , F04D29/283 , F04D29/30 , F04D29/384 , F04D29/4226 , F04D29/666 , F05D2240/301 , F05D2240/303 , F05D2240/304 , F05D2240/305 , F05D2240/306 , F05D2250/711 , F05D2250/712 , F05D2250/713
Abstract: A fan includes a plurality of blade portions arranged spaced apart from each other in a circumferential direction, each blade portion having a blade surface including a pressure surface disposed on a rotational direction side of the fan and a suction surface disposed on a back side of said pressure surface. The plurality of the blade portions include a first blade portion and a second blade portion in which when they are rotated around the rotation axis of the fan and overlapped on one blade portion, one of an inner edge portion and an outer edge portion is disposed to be coincident with each other, and the other of the inner edge portion and the outer edge portion is disposed to be displaced from each other.
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公开(公告)号：US09765631B2
公开(公告)日：2017-09-19
申请号：US14143587
申请日：2013-12-30
Applicant: General Electric Company
Inventor： Aaron Ezekiel Smith , Stanley Frank Simpson , Lisa Anne Wichmann
CPC classification number: F01D5/187 , B23P15/04 , F01D5/147 , F01D5/188 , F01D5/284 , F05D2240/305 , F05D2240/306 , F05D2250/71 , F05D2250/711 , F05D2250/712 , F05D2250/713 , F05D2250/75 , F05D2260/22141 , F05D2260/941 , F05D2300/17 , F05D2300/20 , Y02T50/672 , Y02T50/676 , Y10T29/49337 , Y10T29/49341
Abstract: A turbine blade that includes 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, and a blade outer shell that defines an outer surface of the airfoil. The rib configuration is a non-integral component to the blade outer shell.
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