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公开(公告)号：US10801325B2
公开(公告)日：2020-10-13
申请号：US15469715
申请日：2017-03-27
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo , Scott D. Lewis , Jeffrey T. Morton
Abstract: A blade for a gas turbine engine includes an airfoil which includes pressure and suction side surfaces joined at leading and trailing edges to provide an exterior airfoil surface. The airfoil extends from a 0% span position to a 100% span position at a tip. A mean chamber line is provided at the tip and extends from the leading edge to the trailing edge. The mean chamber line has a leading edge tangent line at the leading edge at the tip and a trailing edge tangent line at the trailing edge at the tip. The leading edge tangent line and the trailing edge tangent line intersect to provide a total camber angle in a range of −35° to 35°. The pressure side includes a tip shelf.
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公开(公告)号：US10400607B2
公开(公告)日：2019-09-03
申请号：US14627587
申请日：2015-02-20
Applicant: United Technologies Corporation
Inventor： Lane Thornton , Scott D. Lewis , Matthew A. Devore
Abstract: A cooling hole for a component includes a meter section and a diffuser section. The diffuser section has a footprint region defined by five sides, a first side of the five sides extending along substantially an entire height of the diffuser section and second and third sides of the five sides meeting in an obtuse angle opposite the first side. A component having the cooling hole and a method of forming the cooling hole are also disclosed.
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公开(公告)号：US10392943B2
公开(公告)日：2019-08-27
申请号：US15355173
申请日：2016-11-18
Inventor： Scott D. Lewis , Stephen Lynch , Shane Haydt
IPC: F01D5/18
Abstract: A component for a gas turbine engine including a body having at least one internal cooling cavity and a plurality of film cooling holes disposed along a first edge of the body. At least one of the film cooling holes includes a metering section defining an axis, and a diffuser section having a centerline. The centerline of the diffuser section is offset from the axis of the metering section.
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公开(公告)号：US10227875B2
公开(公告)日：2019-03-12
申请号：US14766190
申请日：2014-02-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Scott D. Lewis , Brandon M. Rapp , Jeffrey S. Beattie , Matthew Andrew Hough , Bret M. Teller , Jeffrey Michael Jacques , Max Asterlin
IPC: F01D5/18 , F01D11/08 , F23R3/00 , F23R3/04 , F01D9/06 , F01D25/12 , F23R3/06 , F01D9/02 , F23R3/02
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge, circumferentially extends between a first mate face and a second mate face, and includes a gas path surface and a non-gas path surface. The component defines at least one cavity that extends at least partially inside of the component. A first plurality of cooling holes extends from the at least one cavity to at least one of the first mate face and the second mate face and a second plurality of cooling holes extends from either the at least one cavity or the non-gas path surface to the gas path surface.
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公开(公告)号：US20180361512A1
公开(公告)日：2018-12-20
申请号：US15625688
申请日：2017-06-16
Inventor： Scott D. Lewis , Stephen Lynch , Shane Haydt
IPC: B23K26/384 , F01D5/18 , F01D9/02 , F01D25/12 , B23H7/24
CPC classification number: B23K26/384 , B23H1/04 , B23H7/24 , B23H9/10 , B23H9/14 , F01D5/186 , F01D9/02 , F01D9/023 , F01D9/065 , F01D25/12 , F02K1/822 , F05D2220/32 , F05D2230/12 , F05D2240/11 , F05D2240/81 , F05D2250/11 , F05D2250/21 , F05D2250/23 , F05D2260/202 , F23R3/002 , F23R3/06 , F23R2900/00018
Abstract: An electrode for electrical discharge machining (EDM) may comprise a diffuser portion and a tapered portion defining the tip of the electrode.A method for forming a film cooling hole may comprise moving a tool with respect to a film cooled gaspath component, forming a diffuser of the film cooling hole in response to the moving, and forming a tapered surface between a metering section and the diffuser of the film cooling hole.
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Patent Agency Ranking
公开(公告)号：US10156144B2
公开(公告)日：2018-12-18
申请号：US14871456
申请日：2015-09-30
Applicant: United Technologies Corporation
Inventor： San Quach , Steven Bruce Gautschi , Matthew A. Devore , Scott D. Lewis , Matthew S. Gleiner , Christopher King , Christopher Corcoran , David Donald Chapdelaine
Abstract: An airfoil for use in a gas turbine engine is provided. The airfoil having: a pressure surface and a suction surface each extending axially from a leading edge to a trailing edge of the airfoil, at least one of the pressure surface, the suction surface, the leading edge and the trailing edge terminating at an edge of a tip section of the airfoil; a plurality of internal cooling channels located within the airfoil; and at least one cooling hole in fluid communication with at least one of the plurality of internal cooling channels, wherein the at least one cooling hole is aligned with an opening or diffuser that extends directly from the at least one cooling hole and wherein the opening or diffuser is formed in and extends through the edge of the tip section of the airfoil.
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公开(公告)号：US20180274368A1
公开(公告)日：2018-09-27
申请号：US15469715
申请日：2017-03-27
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo , Scott D. Lewis , Jeffrey T. Morton
Abstract: A blade for a gas turbine engine includes an airfoil which includes pressure and suction side surfaces joined at leading and trailing edges to provide an exterior airfoil surface. The airfoil extends from a 0% span position to a 100% span position at a tip. A mean chamber line is provided at the tip and extends from the leading edge to the trailing edge. The mean chamber line has a leading edge tangent line at the leading edge at the tip and a trailing edge tangent line at the trailing edge at the tip. The leading edge tangent line and the trailing edge tangent line intersect to provide a total camber angle in a range of −35° to 35°. The pressure side includes a tip shelf.
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公开(公告)号：US10053992B2
公开(公告)日：2018-08-21
申请号：US14790231
申请日：2015-07-02
Applicant: United Technologies Corporation
Inventor： San Quach , Scott D. Lewis , Steven Bruce Gautschi , Christopher King , Christopher Corcoran , David Donald Chapdelaine
CPC classification number: F01D5/20 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: A gas turbine engine airfoil includes a body that provides an exterior airfoil surface that extends in a radial direction to a tip. The exterior surface has a leading edge in a forward direction and a trailing edge in an aft direction. The tip includes a squealer pocket that has a recess surface. A cooling passage is arranged in the body. Each of the cooling holes extends from an inlet at the cooling passage to an outlet at the recessed surface. The inlet and outlet are arranged at an angle in an angular direction relative to the recessed surface. The angular direction is toward at least one of the forward and aft directions.
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公开(公告)号：US10001023B2
公开(公告)日：2018-06-19
申请号：US15676152
申请日：2017-08-14
Applicant: United Technologies Corporation
Inventor： Scott D. Lewis
CPC classification number: F01D11/08 , F01D5/081 , F01D5/10 , F01D5/3007 , F01D11/008 , F01D25/06 , F01D25/12 , F05D2220/32 , F05D2230/60 , F05D2240/12 , F05D2240/307 , F05D2240/55 , F16J15/162 , Y02T50/672 , Y02T50/675
Abstract: A seal arrangement for a gas turbine engine according to an example of the present disclosure includes, among other things, a component including a body having a cold side surface adjacent to a mate face, and a seal member including a leading edge region and a trailing edge region spaced by sidewalls. The seal member defines one or more grooves. A length of the one or more grooves abuts the cold side surface to define one or more cooling passages, with at least one of the one or more cooling passages having a flared inlet defined by a corresponding one of the one or more grooves.
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公开(公告)号：US20170022839A1
公开(公告)日：2017-01-26
申请号：US15039945
申请日：2014-11-13
Applicant: United Technologies Corporation
Inventor： Scott D. Lewis , Atul Kohli , Thomas J. Praisner
CPC classification number: F01D11/08 , F01D5/12 , F01D5/143 , F01D9/02 , F01D11/006 , F05D2220/32 , F05D2240/11 , F05D2240/80 , F05D2250/192 , F05D2250/231
Abstract: An array of components in a gas turbine engine includes first and second structures respectively including first and second surfaces that are arranged adjacent to one another to provide a gap. The first and second surfaces respectively have first and second rounded edges at the gap that are arranged in staggered relationship relative to one another.
Abstract translation: 燃气涡轮发动机中的一组组件包括第一和第二结构，其分别包括彼此相邻布置以提供间隙的第一和第二表面。 第一和第二表面分别在间隙处具有相对于彼此以交错关系布置的第一和第二圆形边缘。
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