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公开(公告)号：US10975710B2
公开(公告)日：2021-04-13
申请号：US16210393
申请日：2018-12-05
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Dominic Mongillo , Allan N. Arisi
Abstract: A component for a gas turbine engine includes a wall portion that includes an interior surface and an exterior surface. At least one cooling circuit is defined by the wall portion and includes a plurality of pedestals that extend across the cooling circuit. A width of the cooling circuit increases or decreases in a downstream direction. At least one cooling fluid inlet extends through the interior surface and is in fluid communication with the cooling circuit. At least one cooling fluid outlet extends through the exterior surface and is in fluid communication with the cooling circuit.
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公开(公告)号：US09988933B2
公开(公告)日：2018-06-05
申请号：US14478630
申请日：2014-09-05
Applicant: United Technologies Corporation
Inventor： Dominic Mongillo , Matthew S Gleiner
CPC classification number: F01D25/12 , F01D5/186 , F01D9/065 , F05D2240/35 , F05D2240/81 , F05D2250/71 , F05D2260/202 , F23R2900/03042 , Y02T50/676
Abstract: A gas turbine engine component includes a cooling hole. The component includes a first wall having an inlet, a second wall having an outlet and a metering section extending downstream from the inlet and having a substantially convex first surface and a substantially concave second surface. The component also includes a diffusing section extending from the metering section to the outlet. A gas turbine engine wall includes first and second surfaces and a cooling hole extending between an inlet at the first surface and an outlet at the second surface. The cooling hole includes a metering section commencing at the inlet and a diffusing section in communication with the metering section and terminating at the outlet. The metering section includes a top portion having a first arcuate surface and a bottom portion having a second arcuate surface. The first and second arcuate surfaces have arcs extending in substantially similar directions.
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公开(公告)号：US20200182152A1
公开(公告)日：2020-06-11
申请号：US16210393
申请日：2018-12-05
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Dominic Mongillo , Allan N. Arisi
Abstract: A component for a gas turbine engine includes a wall portion that includes an interior surface and an exterior surface. At least one cooling circuit is defined by the wall portion and includes a plurality of pedestals that extend across the cooling circuit. A width of the cooling circuit increases or decreases in a downstream direction. At least one cooling fluid inlet extends through the interior surface and is in fluid communication with the cooling circuit. At least one cooling fluid outlet extends through the exterior surface and is in fluid communication with the cooling circuit.
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Patent Agency Ranking
公开(公告)号：US10669861B2
公开(公告)日：2020-06-02
申请号：US15433130
申请日：2017-02-15
Applicant: United Technologies Corporation
Inventor： Brandon Spangler , Dominic Mongillo
Abstract: An airfoil may comprise an airfoil body having a leading edge, a trailing edge, an inner diameter end wall and an outer diameter end wall. A first cooling structure may be disposed within the airfoil body. The first cooling structure may comprise a first rib extending between the inner diameter end wall and the outer diameter end wall and may define a first radial passage configured to conduct a cooling airflow in a radial direction through the airfoil body. A second cooling structure may be disposed within the airfoil body. The second cooling structure may comprise a first baffle defining an axial passage configured to conduct the cooling airflow in an axial direction toward the trailing edge of the airfoil body.
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公开(公告)号：US10408453B2
公开(公告)日：2019-09-10
申请号：US15654324
申请日：2017-07-19
Applicant: United Technologies Corporation
Inventor： Dominic Mongillo , Christopher Whitfield , Tracy Propheter-Hinckley
Abstract: A grommet may define a dilution hole in a combustor panel. The grommet may comprise a set of upstream features such as, for example, a first inlet leading into a first plurality of passages with the first plurality of passages each having a first outlet directed towards an inner diameter of the grommet. A set of perimeter features may include a second inlet leading into a convective cooling passage having a plurality of internal cooling features. The convective cooling passage may further lead into a second plurality of passages each having a second outlet extending about the inner diameter of the grommet in a circumferential direction A set of downstream features may include a third inlet leading to a third plurality of passages each having a third outlet directed towards an outer diameter of the grommet.
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公开(公告)号：US20190024894A1
公开(公告)日：2019-01-24
申请号：US15654324
申请日：2017-07-19
Applicant: United Technologies Corporation
Inventor： Dominic Mongillo , Christopher Whitfield , Tracy Propheter-Hinckley
CPC classification number: F23R3/04 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2230/50 , F05D2240/35 , F05D2250/71 , F05D2260/202 , F05D2260/2214 , F23R3/002 , F23R3/06 , F23R2900/00018 , F23R2900/03042 , F23R2900/03043
Abstract: A grommet may define a dilution hole in a combustor panel. The grommet may comprise a set of upstream features such as, for example, a first inlet leading into a first plurality of passages with the first plurality of passages each having a first outlet directed towards an inner diameter of the grommet. A set of perimeter features may include a second inlet leading into a convective cooling passage having a plurality of internal cooling features. The convective cooling passage may further lead into a second plurality of passages each having a second outlet extending about the inner diameter of the grommet in a circumferential direction A set of downstream features may include a third inlet leading to a third plurality of passages each having a third outlet directed towards an outer diameter of the grommet.
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公开(公告)号：US10309239B2
公开(公告)日：2019-06-04
申请号：US14766496
申请日：2014-02-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon W. Spangler , Dominic Mongillo
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a wall having an internal surface and an outer skin, a cooling hole having an inlet extending from the internal surface and merging into a metering section, and a diffusion section downstream of the metering section that extends to an outlet located at the outer skin. The diffusion section of the cooling hole includes a first side diffusion angle, a second side diffusion angle and a downstream diffusion angle at a downstream surface of the diffusion section, the downstream diffusion angle being less than the first side diffusion angle and the second side diffusion angle.
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公开(公告)号：US20180230814A1
公开(公告)日：2018-08-16
申请号：US15433130
申请日：2017-02-15
Applicant: United Technologies Corporation
Inventor： Brandon Spangler , Dominic Mongillo
Abstract: An airfoil may comprise an airfoil body having a leading edge, a trailing edge, an inner diameter end wall and an outer diameter end wall. A first cooling structure may be disposed within the airfoil body. The first cooling structure may comprise a first rib extending between the inner diameter end wall and the outer diameter end wall and may define a first radial passage configured to conduct a cooling airflow in a radial direction through the airfoil body. A second cooling structure may be disposed within the airfoil body. The second cooling structure may comprise a first baffle defining an axial passage configured to conduct the cooling airflow in an axial direction toward the trailing edge of the airfoil body.
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