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11.发明申请公开(公告)号：US20190219268A1
公开(公告)日：2019-07-18
申请号：US16239911
申请日：2019-01-04
Applicant: United Technologies Corporation
Inventor： Dennis M. Moura , Carey Clum
CPC classification number: F23R3/007 , F01D5/189 , F23R2900/03044
Abstract: A gas turbine engine component assembly comprising: a first component having a first surface and a second surface opposite the first surface, wherein the first component includes a cooling hole extending from the second surface to the first surface; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween; and a lateral flow injection feature integrally formed in the first component and fluidly connecting a flow path located proximate to the second surface of first component to the cooling channel, the lateral flow injection feature being configured to direct airflow from the airflow path through a passageway and into the cooling channel at least partially in a lateral direction parallel to the second surface of the second component such that a cross flow is generated in the cooling channel.
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公开(公告)号：US10329921B2
公开(公告)日：2019-06-25
申请号：US14878498
申请日：2015-10-08
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Carey Clum
Abstract: A component includes at least one thermal riser that extends from an exterior surface of the component. At least one cooling passage extends through a wall and adjoins an interior cooling passage and provides an exterior surface. At least one cooling passage is configured to direct cooling fluid through the wall adjacent to at least one thermocouple.
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公开(公告)号：US20190169997A1
公开(公告)日：2019-06-06
申请号：US15832478
申请日：2017-12-05
Applicant: United Technologies Corporation
Inventor： Christopher Whitfield , Carey Clum , Dominic J. Mongillo, Jr.
CPC classification number: F01D5/187 , F02C3/04 , F02C9/18 , F05D2220/32 , F05D2240/35 , F05D2250/185 , F05D2260/201 , F05D2260/202 , F05D2260/204 , F05D2260/2212
Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The core passage and the skin passage are configured to have a same direction of fluid flow. A resupply hole fluidly interconnects the core and skin passages. A centerline of the resupply hole is arranged at an acute angle relative to the direction of fluid flow in the core passage and is configured to provide a low turbulence flow region in the skin passage. The resupply hole has an exit at the skin passage and the exit has a diffuser.
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公开(公告)号：US20190169993A1
公开(公告)日：2019-06-06
申请号：US15832407
申请日：2017-12-05
Applicant: United Technologies Corporation
Inventor： Christopher Whitfield , Carey Clum , Dominic J. Mongillo, JR.
CPC classification number: F01D5/187 , F02C3/04 , F02C9/18 , F05D2220/32 , F05D2240/35 , F05D2260/201 , F05D2260/202 , F05D2260/204 , F05D2260/221
Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The core passage and the skin passage are configured to have a same direction of fluid flow. A resupply hole cluster includes first and second resupply holes that each fluidly interconnect the core and skin passages. The first and second resupply holes intersect one another and terminate in an exit at the skin passage.
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公开(公告)号：US20190101006A1
公开(公告)日：2019-04-04
申请号：US15723446
申请日：2017-10-03
Applicant: United Technologies Corporation
Inventor： Carey Clum , Timothy J. Jennings , Tracy A. Propheter-Hinckley
IPC: F01D5/18
Abstract: Airfoil bodies having a first core cavity and a second core cavity adjacent each other, with the second core cavity defined by a first cavity wall, a second cavity wall, a first exterior wall, and a second exterior wall. The first cavity wall is located between the second core cavity and the first core cavity and the first and second exterior walls are exterior walls of the airfoil body. The first cavity wall includes a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall. At least one first cavity impingement hole is formed within the first surface with a first impingement flow flowing from the first core cavity through the at least one first cavity impingement hole to impinge upon the first exterior wall and forms a first high momentum jet of impingement air thereon.
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Patent Agency Ranking
公开(公告)号：US20190101005A1
公开(公告)日：2019-04-04
申请号：US15723461
申请日：2017-10-03
Applicant: United Technologies Corporation
Inventor： Carey Clum , Timothy J. Jennings
CPC classification number: F01D5/186 , B22C9/10 , B22C9/22 , B22C9/24 , B22C13/10 , F01D5/187 , F01D9/065 , F05D2230/211 , F05D2260/202 , F05D2260/205
Abstract: Airfoils having a leading edge and a trailing edge, with a plurality of cavities therein including a leading edge hybrid cavity extending in a radial direction between a first end and a second end of the airfoil body along the leading edge. An airfoil side hybrid cavity is located toward the trailing edge relative to the leading edge hybrid cavity and positioned adjacent a side wall of the airfoil body. The airfoil side hybrid cavity extends in a radial direction between the first end and the second end and a divider rib extends radially between the first end and the second end along the side wall of the airfoil between the airfoil side hybrid cavity and the leading edge hybrid cavity. At least one first cross-over hole is formed within the divider rib to fluidly connect the airfoil side hybrid cavity to the leading edge hybrid cavity.
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公开(公告)号：US20190048728A1
公开(公告)日：2019-02-14
申请号：US15671328
申请日：2017-08-08
Applicant: United Technologies Corporation
Inventor： Carey Clum , Dominic J. Mongillo, JR.
Abstract: Airfoils including an airfoil body having leading and trailing edges and root and tip regions, wherein an aftward direction is from the leading edge toward the trailing edge and a radially outward direction is from root to tip, a forward-flowing serpentine flow path formed within the airfoil body defined by a first serpentine cavity, a second serpentine cavity, and a third serpentine cavity, wherein the first serpentine cavity is aftward of the second serpentine cavity, and the second serpentine cavity is aftward of the third serpentine cavity, a tip flag cavity extending aftward from proximate the leading edge to the trailing edge along the tip region, and at least one shielding cavity located between a portion of the forward-flowing serpentine flow path and an external surface of the airfoil body.
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公开(公告)号：US10202864B2
公开(公告)日：2019-02-12
申请号：US15019197
申请日：2016-02-09
Applicant: United Technologies Corporation
Inventor： Carey Clum , Dominic J. Mongillo
Abstract: A blade outer air seal segment assembly includes a blade outer air seal segment configured to connect with an adjacent blade outer air seal segment to form part of a rotor shroud. A cooling channel is disposed in the first turbine blade outer air seal segment. The cooling channel extends at least partially between a first circumferential end portion and a second circumferential end portion. At least one inlet aperture provides a cooling airflow to the cooling channel. A series of trip strips in the cooling channel cause turbulence in the cooling airflow. The trip strips include at least one chevron-shaped trip strip having a first and second leg joined at an apex arranged adjacent the inlet aperture. The trip strips also include at least one trip strip having a single skewed line.
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公开(公告)号：US20180347376A1
公开(公告)日：2018-12-06
申请号：US15613255
申请日：2017-06-04
Applicant: United Technologies Corporation
Inventor： Carey Clum , Evan P. Molony , Charles Thistle , Dominic J. Mongillo
CPC classification number: F01D5/187 , B22C9/103 , B22C9/24 , F01D5/081 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2230/211 , F05D2250/185 , F05D2260/202
Abstract: Airfoils having a body with leading and trailing edges and a first serpentine cavity within the body enabling a cooling flow in a first direction within the airfoil body, a second serpentine cavity fluidly connected to the first serpentine cavity enabling a cooling flow in a second direction, and a third serpentine cavity fluidly connected to the second serpentine cavity enabling a cooling flow in at least one of the first direction or a third direction. A resupply cavity is fluidly connected to the third serpentine cavity to supply a resupply air to the third serpentine cavity, a junction at the location of the second serpentine cavity, the resupply cavity and the third serpentine cavity, and a flow control feature arranged to turn the serpentine cooling air from the second direction and/or prevent resupply air backflow.
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公开(公告)号：US20170198838A1
公开(公告)日：2017-07-13
申请号：US14992646
申请日：2016-01-11
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Carey Clum
CPC classification number: F16L13/0209 , B23K1/0018 , B23K1/18 , B23K1/19 , B23K33/006 , B23K2101/001 , B23K2101/06 , B23K2103/05 , B23K2103/08 , F01D9/06 , F02C3/04 , F05D2220/32 , F05D2230/237
Abstract: Systems for tube-to-tube connections are described herein. A device having an aperture for receiving a tube may comprise: an inlet portion comprising a first diameter, the inlet portion located at an inlet of the aperture; a braze filler collector portion located axially adjacent to the inlet portion comprising a second diameter, the second diameter being greater than the first diameter; a necked portion located axially adjacent to the braze filler collector portion comprising a third diameter, the third diameter being less than the first diameter and the second diameter; a flow surface comprising a fourth diameter, the fourth diameter being less than the third diameter, the flow surface defining a void; and a collection pocket located axially adjacent to the necked portion, the collection pocket configured to collect a braze filler material from the necked portion to prevent the braze filler material from contacting the flow surface.
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