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公开(公告)号：US20230383663A1
公开(公告)日：2023-11-30
申请号：US18302976
申请日：2023-04-19
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Howard J. Liles
CPC classification number: F01D9/041 , F05D2260/20 , F05D2240/12 , F01D9/065
Abstract: A gas turbine engine includes a circumferential row of vanes arranged about a central engine axis. The vanes include respective internal cavities and vane outlet ports for conveying cooling air. A tangential onboard injector (TOBI) radially supports the vanes at an inner diameter of the circumferential row. The TOBI includes fore and aft annular walls and an outer diameter annular wall. The fore and aft annular walls and the outer diameter annular wall define an annular plenum. The outer diameter annular wall includes TOBI inlet ports that are connected, respectively, with the vane outlet ports to receive the cooling air from each of the vanes into the plenum. The TOBI includes axially-oriented nozzles for discharging the cooling air from the plenum in an aft direction.
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公开(公告)号：US11346228B1
公开(公告)日：2022-05-31
申请号：US17182389
申请日：2021-02-23
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Alyson T. Burdette , Bryan P. Dube , Howard J. Liles , James T. Roach
Abstract: A vane arc segment includes an airfoil fairing that has a fairing platform and an airfoil section that extends there from. The fairing platform defines a gaspath side and a non-gaspath side and includes a flange that projects from the non-gaspath side. The airfoil fairing is formed of a fiber-reinforced composite that includes a wishbone-shaped fiber layer structure that has first and second arms that converge and merge into a single leg. The first and second arms are formed of fiber plies comprised of a network of fiber tows. The single leg comprises fiber tows from each of the fiber plies of the first and second arms. The fiber tows of the first arm are interwoven in the single leg with the fiber tows of the second arm. The first arm, the second arm, or the single leg forms at least a portion of the flange.
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公开(公告)号：US20230407753A1
公开(公告)日：2023-12-21
申请号：US17843518
申请日：2022-06-17
Applicant: Raytheon Technologies Corporation
Inventor： Howard J. Liles , Tyler G. Vincent
CPC classification number: F01D5/189 , F01D5/282 , F05D2260/232 , F05D2300/6033 , F05D2240/126 , F01D5/284
Abstract: A component for a gas turbine engine includes a matrix composite component having a radially outer end and a radially inner end. The ceramic matrix component having an internal chamber defined by an inner surface. A spar is received within the internal cavity, and spaced from an inner surface of the matrix component defining a chamber with the inner surface. Flow guides are formed on one of an outer surface of the spar and the inner surface of the matrix component. The flow guides direct airflow towards a portion of the inner surface. An air inlet chamber is formed at one radial end of the spar and an air outlet chamber formed at an opposed radial end of the spar. The air inlet chamber is defined such that air will flow into the internal chamber, outwardly of the spar, and inwardly of the inner surface of the matrix component. A gas turbine engine is also disclosed.
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公开(公告)号：US11732589B1
公开(公告)日：2023-08-22
申请号：US17865949
申请日：2022-07-15
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Christian X. Campbell , Howard J. Liles
CPC classification number: F01D5/147 , F01D5/282 , F01D5/284 , F05D2220/323 , F05D2300/6033
Abstract: An airfoil vane multiplet includes airfoil tubes that each have airfoil tube fiber plies. A plurality of the airfoil tube fiber plies extend along the airfoil tube and turn to project outwardly from the airfoil tube. Connector fiber plies include airfoil holes through which the airfoil tubes extend. The connector fiber plies are interleaved with the plurality of airfoil tube fiber plies such that the airfoil tubes are secured together.
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公开(公告)号：US20230243037A1
公开(公告)日：2023-08-03
申请号：US17587354
申请日：2022-01-28
Applicant: Raytheon Technologies Corporation
Inventor： Ashley A. Smith , Andrew J. Lazur , Howard J. Liles
CPC classification number: C23C16/52 , C23C16/045 , C23C16/56 , C23C16/0272
Abstract: A method of improving surface roughness of ceramic matrix composites (CMCs) is provided. The method includes completing a formation of the CMCs and a chemical vapor infiltration (CVI) process to initially coat the CMCs, inspecting a CMC surface, identifying, from a result of the inspecting, a defect in the CMC surface that negatively impacts a surface roughness characteristic thereof, locally targeting and ablating the defect and re-inspecting the CMC surface to ensure that the defect is correct.
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Patent Agency Ranking
公开(公告)号：US20230235673A1
公开(公告)日：2023-07-27
申请号：US17585760
申请日：2022-01-27
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Christian X. Campbell , Howard J. Liles , Russell Kim
CPC classification number: F01D5/141 , F01D5/282 , F05D2220/32 , F05D2300/6033 , F05D2250/71
Abstract: A gas turbine engine includes a turbine section that has a plurality of turbine vanes. Each of the turbine vanes includes inner and outer platforms and an airfoil section that extends there between. The airfoil section is hollow and rib-less and has a first end at the outer platform and a second end at the inner platform. The airfoil section is tangentially bowed from the first end to the second end with a radius of curvature that is from 17 centimeters to 130 centimeters.
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公开(公告)号：US11655758B1
公开(公告)日：2023-05-23
申请号：US17709523
申请日：2022-03-31
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Jon Erik Sobanski , Howard J. Liles
CPC classification number: F02C3/06 , F01D9/041 , F02C7/28 , F05D2220/32 , F05D2240/35 , F05D2240/55 , F05D2300/614
Abstract: A vane arc segment includes a platform and an airfoil section that extends in a radial direction from the platform. The airfoil section has a pressure side and a suction side. The platform defines fore and aft axial sides, a core gaspath side, a non-core gaspath side, and first and second flanges that project from the non-core gaspath side. The first and second flanges define, respectively, first and second circumferential mate faces. The first and second flanges each are formed of upturned fiber plies from the platform such that the fiber plies in the first and second flanges are radially-oriented. The first and second circumferential mate faces have, respectively, first and second seal slots that each extend in a ply through-thickness direction across two or more of the fiber plies.
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公开(公告)号：US11608748B2
公开(公告)日：2023-03-21
申请号：US17339198
申请日：2021-06-04
Applicant: Raytheon Technologies Corporation
Inventor： Howard J. Liles , Tyler G. Vincent
Abstract: A method of forming a ceramic matrix composite component having an internal cooling circuit includes wrapping at least a first sheet around a first mandrel, wrapping at least a second sheet around a second mandrel, creating a first plurality of holes in the first sheet corresponding to a plurality of openings in the first mandrel, creating a second plurality of holes in the second sheet corresponding to a plurality of openings in the second mandrel, aligning the first mandrel and the second mandrel such that the first plurality of holes face and are aligned with the second plurality of holes, wrapping at least a third sheet around both the first mandrel and second mandrel to form a preform, the preform comprising each of the first sheet, the second sheet, and the third sheet, and densifying the preform. The first sheet, second sheet, and third sheet are formed from a ceramic fiber material.
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公开(公告)号：US11549380B2
公开(公告)日：2023-01-10
申请号：US17076043
申请日：2020-10-21
Applicant: Raytheon Technologies Corporation
Inventor： Bryan H. Farrar , Howard J. Liles
Abstract: A method of fabricating an airfoil includes drawing a continuous woven fabric ply over a contoured surface that has a geometry that is analogous to a geometry of an airfoil. The continuous woven fabric ply takes the geometry of the contoured surface to thereby form a contoured continuous woven fabric ply. The contoured continuous woven fabric ply is then wrapped around an airfoil tool to produce an airfoil preform. The airfoil tool has a geometry that is analogous to the airfoil. The contoured continuous woven fabric ply takes the geometry of the airfoil tool. The airfoil preform is then densified with a ceramic matrix to produce a ceramic matrix composite airfoil.
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公开(公告)号：US20220389822A1
公开(公告)日：2022-12-08
申请号：US17339198
申请日：2021-06-04
Applicant: Raytheon Technologies Corporation
Inventor： Howard J. Liles , Tyler G. Vincent
Abstract: A method of forming a ceramic matrix composite component having an internal cooling circuit includes wrapping at least a first sheet around a first mandrel, wrapping at least a second sheet around a second mandrel, creating a first plurality of holes in the first sheet corresponding to a plurality of openings in the first mandrel, creating a second plurality of holes in the second sheet corresponding to a plurality of openings in the second mandrel, aligning the first mandrel and the second mandrel such that the first plurality of holes face and are aligned with the second plurality of holes, wrapping at least a third sheet around both the first mandrel and second mandrel to form a preform, the preform comprising each of the first sheet, the second sheet, and the third sheet, and densifying the preform. The first sheet, second sheet, and third sheet are formed from a ceramic fiber material.
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