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公开(公告)号：US11286790B2
公开(公告)日：2022-03-29
申请号：US17009936
申请日：2020-09-02
Applicant: Raytheon Technologies Corporation
Inventor： San Quach , Christopher King , Tracy A. Propheter-Hinckley
Abstract: A gas turbine engine component includes a wall that has an inner surface and an outer surface. An inlet is defined by the inner surface. At least one non-rectangular slot is defined by the outer surface and includes at least one protrusion extending into the slot. A slot passage fluidly connects the inlet to the at least one non-rectangular slot. The slot passage comprises an inlet portion that extends through the wall from the inlet to an intermediate portion. An outlet portion extends through the wall from the intermediate portion to the at least one non-rectangular slot.
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公开(公告)号：US11898450B2
公开(公告)日：2024-02-13
申请号：US17323436
申请日：2021-05-18
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Raymond Surace , San Quach , Bryan P. Dube
CPC classification number: F01D11/12 , F01D5/282 , F01D5/147 , F01D25/12 , F05D2220/323 , F05D2240/11 , F05D2240/125 , F05D2300/20 , F05D2300/6033
Abstract: An assembly for a gas turbine engine includes, among other things, an end wall including a main body extending between a first end portion and a second end portion to establish a seal face. The end wall includes a first attachment portion dimensioned to fixedly attach the main body to a static structure at a first attachment point. An airfoil extends radially inwardly from the end wall relative to an assembly axis. The airfoil includes an inner cavity extending between a first end portion and a second end portion, the first end portion adjacent the end wall of the airfoil. A spar member includes a spar body extending between a first end portion and a second end portion. The spar body extends at least partially through the inner cavity. The first end portion of the end wall is cantilevered from the first attachment point.
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公开(公告)号：US20230036836A1
公开(公告)日：2023-02-02
申请号：US17952693
申请日：2022-09-26
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： San Quach , Bryan P. Dube , Erik R. Granstand , Michael G. McCaffrey , Stephen G. Pixton
Abstract: In one exemplary embodiment, a flow path component assembly includes a support structure having an axial portion and a radial portion and an outer portion arranged between the support structure. The outer portion defines a gap between the outer portion and the axial portion of the support structure. A flange is positioned relative to the gap.
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Patent Agency Ranking
公开(公告)号：US20220372888A1
公开(公告)日：2022-11-24
申请号：US17323436
申请日：2021-05-18
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Raymond Surace , San Quach , Bryan P. Dube
Abstract: An assembly for a gas turbine engine includes, among other things, an end wall including a main body extending between a first end portion and a second end portion to establish a seal face. The end wall includes a first attachment portion dimensioned to fixedly attach the main body to a static structure at a first attachment point. An airfoil extends radially inwardly from the end wall relative to an assembly axis. The airfoil includes an inner cavity extending between a first end portion and a second end portion, the first end portion adjacent the end wall of the airfoil. A spar member includes a spar body extending between a first end portion and a second end portion. The spar body extends at least partially through the inner cavity. The first end portion of the end wall is cantilevered from the first attachment point.
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公开(公告)号：US20220316353A1
公开(公告)日：2022-10-06
申请号：US17221036
申请日：2021-04-02
Applicant: Raytheon Technologies Corporation
Inventor： San Quach , Bryan P. Dube , Erik R. Granstand , Michael G. McCaffrey , Stephen G. Pixton
Abstract: In one exemplary embodiment, a flow path component assembly includes a support structure that is a unitary component having an axial portion and a radial portion and an outer portion arranged between the support structure and a flow path. The outer portion defines a gap between the outer portion and the support structure axial portion. A flange extends into the gap.
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公开(公告)号：US11454129B1
公开(公告)日：2022-09-27
申请号：US17221036
申请日：2021-04-02
Applicant: Raytheon Technologies Corporation
Inventor： San Quach , Bryan P. Dube , Erik R. Granstand , Michael G. McCaffrey , Stephen G. Pixton
Abstract: In one exemplary embodiment, a flow path component assembly includes a support structure that is a unitary component having an axial portion and a radial portion and an outer portion arranged between the support structure and a flow path. The outer portion defines a gap between the outer portion and the support structure axial portion. A flange extends into the gap.
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公开(公告)号：US20220003120A1
公开(公告)日：2022-01-06
申请号：US17482478
申请日：2021-09-23
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： San Quach , Tracy A. Propheter-Hinckley , Steven Bruce Gautschi
Abstract: A component for a gas turbine engine includes, among other things, an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge, the airfoil extending radially from a platform to a tip, a tip pocket formed in the tip and terminating prior to the trailing edge, and one or more heat transfer augmentation devices formed in the tip pocket.
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公开(公告)号：US20220003119A1
公开(公告)日：2022-01-06
申请号：US16920014
申请日：2020-07-02
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Jaime G. Ghigliotty , David J. Candelori , San Quach
Abstract: An airfoil for a gas turbine engine is disclosed. In various embodiments, the airfoil includes a cooling passage; an outer wall separating a core flow path from the cooling passage; a diffuser in fluid communication with the cooling passage and opening into the core flow path, the diffuser being characterized by a linear ridge on a downstream end of the diffuser; and a thermal barrier coating covering the outer wall and the linear ridge.
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