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公开(公告)号：US20240410656A1
公开(公告)日：2024-12-12
申请号：US18207527
申请日：2023-06-08
Applicant: Raytheon Technologies Corporation
Inventor： Michael G. McCaffrey
Abstract: An assembly is provided for an engine. This engine assembly includes a heat exchange apparatus, and the heat exchange apparatus includes a core, a shell and an inner flowpath. The core includes a core sidewall and a plurality of internal passages. The core sidewall extends axially along and circumferentially around an axis. The core sidewall extends radially from a core inner side to a core outer side. The core inner side forms an outer peripheral boundary of the inner flowpath. The internal passages are arranged circumferentially about the axis. Each of the internal passages extends axially in the core sidewall. The shell extends axially along and circumscribes the core. The shell is abutted radially against the core outer side.
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公开(公告)号：US20240360771A1
公开(公告)日：2024-10-31
申请号：US18308968
申请日：2023-04-28
Applicant: Raytheon Technologies Corporation
Inventor： Michael G. McCaffrey
CPC classification number: F01D11/14 , F02C7/28 , F05D2240/55
Abstract: A blade outer airseal (BOAS) assembly of a gas turbine engine includes a plurality of BOAS segments arrayed circumferentially about the engine central longitudinal axis, and a plurality of BOAS carriers located radially outboard of the plurality of BOAS segments. Each BOAS carrier is supportive of at least one BOAS segment. The BOAS assembly includes plurality of adjustment levers. Each adjustment lever is operably connected to at least two BOAS carriers of the plurality of BOAS carriers. Rotation of each adjustment lever about a respective pivot axis urges movement of the plurality of BOAS segments in a radial direction thereby adjusting a radial gap between the turbine rotor and the plurality of BOAS segments.
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公开(公告)号：US11867067B2
公开(公告)日：2024-01-09
申请号：US17831944
申请日：2022-06-03
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey
CPC classification number: F01D11/08 , F01D5/12 , F01D5/284 , F05D2240/55 , F05D2300/6033 , F05D2300/614
Abstract: An article includes a gas turbine engine component that has a ceramic matrix composite (CMC) body and a fiber layer circumscribing a cavity. There is a ceramic insert incorporated into the CMC article body, the insert bordering the cavity.
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公开(公告)号：US11852019B1
公开(公告)日：2023-12-26
申请号：US18330697
申请日：2023-06-07
Applicant: Raytheon Technologies Corporation
Inventor： Michael G. McCaffrey
CPC classification number: F01D11/003 , F01D11/08 , F05D2240/55 , F05D2250/711 , F05D2250/75
Abstract: Disclosed herein is a seal comprising an annular ring comprising: an outer diameter surface having an outer diameter, an inner diameter surface, a first height measured from the outer diameter surface to the inner diameter surface, wherein a first ratio of the outer diameter to the first height is greater than 10:1; and a cross-sectional shape comprising: a central beam extending from an inner end to an outer end, the central beam including a central axis that defines an angle with a neutral axis of the cross-sectional shape, the angle being between 5 degrees and 25 degrees; a first flange extending axially from the inner end of the central beam in a first axial direction; and a second flange extending axially from the outer end of the central beam in a second axial direction, the second axial direction being opposite the first axial direction.
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公开(公告)号：US20230392506A1
公开(公告)日：2023-12-07
申请号：US17831933
申请日：2022-06-03
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey
CPC classification number: F01D5/282 , F01D9/041 , F01D5/147 , F05D2240/12 , F05D2240/80 , F05D2300/6033
Abstract: A vane arc segment includes ceramic matrix composite (CMC) fairing that has an airfoil section, a first single-sided platform at the outer radial end projecting from the suction side wall, and a second single-sided platform at the inner radial end projecting from the pressure side wall. The first single-sided platform is comprised of a fiber layer that extends from the airfoil section and turns into the first single-sided platform, and the second single-sided platform is comprised of the fiber layer that from the airfoil section and turns into the second single-sided platform.
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Patent Agency Ranking
公开(公告)号：US20230383695A1
公开(公告)日：2023-11-30
申请号：US18202731
申请日：2023-05-26
Applicant: Raytheon Technologies Corporation
Inventor： Paul R. Hanrahan , Michael G. McCaffrey
CPC classification number: F02C6/20 , B64D27/10 , B64D27/24 , F02C9/16 , B64D2027/026
Abstract: A propulsion system includes a first propulsor rotor, a second propulsor rotor and a gas turbine engine core. The first propulsor rotor is configured to generate propulsive thrust. The second propulsor rotor is configured to generate propulsive lift. The gas turbine engine core includes a compressor section, a combustor section, a turbine section and a rotating structure. The rotating structure includes a turbine rotor within the turbine section. The gas turbine engine core is configured to rotate the rotating structure at a first rotational speed during a first mode to drive the first propulsor rotor to generate the propulsive thrust. The gas turbine engine core is configured to rotate the rotating structure at a second rotational speed during a second mode to drive the second propulsor rotor to generate the propulsive lift. The second rotational speed may be less than eighty percent of the first rotational speed.
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公开(公告)号：US11674402B2
公开(公告)日：2023-06-13
申请号：US16202898
申请日：2018-11-28
Applicant: Raytheon Technologies Corporation
Inventor： Michael G. McCaffrey
CPC classification number: F01D11/025 , F01D11/001 , F16J15/442 , F16J15/445 , F02C7/28 , F05D2220/321 , F05D2240/55
Abstract: A hydrostatic advanced low leakage seal configured to be disposed between relatively rotatable components. The seal includes a base. The seal also includes a shoe extending circumferentially. The seal further includes a radially outer beam operatively coupling the shoe to the base. The seal yet further includes a radially inner beam operatively coupling the shoe to the base, wherein one of the radially inner beam and the radially outer beam is oriented to be angled relative to the other of the radially inner and outer beam.
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公开(公告)号：US11549373B2
公开(公告)日：2023-01-10
申请号：US17123344
申请日：2020-12-16
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey
Abstract: A turbine section for a gas turbine engine according to an example of the present disclosure includes, among other things, a first turbine rotor coupled to a first turbine shaft. The first turbine shaft is rotatable about a longitudinal axis. A second turbine rotor is coupled to a second turbine shaft. The second turbine shaft is rotatable about the longitudinal axis, and the second turbine rotor is axially aft of the first turbine rotor relative to the longitudinal axis. An aft bearing assembly rotatably supports the second turbine shaft. The second turbine rotor includes a disk assembly that carries at least one row of turbine blades. The disk assembly is mechanically attached to the second turbine shaft at an attachment point. The attachment point is axially aft of the aft bearing assembly such that an aft portion of the second turbine shaft is cantilevered from the aft bearing system with respect to the longitudinal axis. The disk assembly includes a metallic material. Each of the turbine blades comprises a ceramic matrix composite (CMC) material.
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公开(公告)号：US11512651B2
公开(公告)日：2022-11-29
申请号：US17159525
申请日：2021-01-27
Applicant: Raytheon Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu , Michael G. McCaffrey
Abstract: A gas turbine engine includes a main compressor section with a downstream most location. A turbine section has a high pressure turbine. A tap line is connected to tap air from a location upstream of the downstream most location in the main compressor section. The tapped air is connected to a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and is connected to deliver air into the high pressure turbine. A bypass valve is positioned downstream of the main compressor section, and upstream of the heat exchanger. The bypass valve selectively delivers air directly to the cooling compressor without passing through the heat exchanger under certain conditions.
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公开(公告)号：US20210363674A1
公开(公告)日：2021-11-25
申请号：US16880341
申请日：2020-05-21
Applicant: Raytheon Technologies Corporation
Inventor： Michael G. McCaffrey
Abstract: Disclosed is a weaving assembly including a rotatable base, a base positional controller, a weave control grid, a warp fiber support, warp fiber arms, a warp fiber arm positional controller and a fill fiber wand.
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