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公开(公告)号：US11480057B2
公开(公告)日：2022-10-25
申请号：US15791745
申请日：2017-10-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Timothy J. Jennings , Carey Clum
Abstract: An airfoil may include an airfoil body that defines a skin chamber, a skin chamber outlet opening, and a tip flag chamber. In various embodiments, the skin chamber is in fluidic communication with the tip flag chamber via the skin chamber outlet opening. In various embodiments, the airfoil body further defines an outlet hole disposed on at least one of a trailing edge and a pressure side of the airfoil. The tip flag chamber may be in fluidic communication with the outlet hole (e.g., cooling circuit air in the tip flag chamber may exit the airfoil via the outlet hole). In various embodiments, the tip flag chamber extends parallel and directly adjacent to the outermost tip of the airfoil.
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公开(公告)号：US11434770B2
公开(公告)日：2022-09-06
申请号：US15471731
申请日：2017-03-28
Applicant: United Technologies Corporation
Inventor： Carey Clum , Ricardo Trindade
Abstract: An airfoil has a pressure side wall and a suction side wall circumferentially spaced apart from the pressure side wall. Each radially extends between a root region and a tip region, and each axially extends between a leading edge and a trailing edge. The airfoil also has a gusset, a squealer pocket, and a tip pocket. The gusset extends between the pressure side wall and the suction side wall. The squealer pocket is formed in the tip region and is disposed between the leading edge, the gusset, the pressure side wall, and the suction side wall. The tip pocket is formed in the tip region and is spaced apart from the squealer pocket. The tip pocket is disposed between the trailing edge, the gusset, the pressure side wall, and the suction side wall.
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3.发明授权公开(公告)号：US11092339B2
公开(公告)日：2021-08-17
申请号：US16239879
申请日：2019-01-04
Applicant: United Technologies Corporation
Inventor： Dennis M. Moura , Carey Clum
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 device secured to first component, the lateral flow injection device fluidly connecting a flow path located proximate to the second surface of the first component to the cooling channel, the lateral flow injection device being configured to direct airflow from the airflow path into the cooling channel in about 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：US10968753B1
公开(公告)日：2021-04-06
申请号：US16552450
申请日：2019-08-27
Applicant: United Technologies Corporation
Inventor： Tracy A. Propheter-Hinckley , Carey Clum , Timothy J. Jennings
Abstract: Airfoils for a gas turbine engines and gas turbine engines are described. The airfoils include an airfoil body extending in a radial direction from a first end to a second end, and axially from a leading edge to a trailing edge. A radially extending leading edge channel is formed in the leading edge of the airfoil body, having first and second channel walls that join at a channel base. A first leading edge impingement cavity is located within the airfoil body proximate the leading edge and is defined, in part, by the first channel wall. A leading edge feed cavity is arranged aft of the first leading edge impingement cavity to supply air into the first leading edge impingement cavity. A first leading edge impingement hole is formed in the first channel wall and angled toward a portion of the second channel wall.
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5.发明授权公开(公告)号：US10823417B2
公开(公告)日：2020-11-03
申请号：US15709333
申请日：2017-09-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Carey Clum , Shayan Ahmadian , Christopher W. Robak
Abstract: A combustor may include a combustor shell, a particle collection panel, and a combustor panel. The combustor shell may define a plurality of first impingement holes, the particle collection panel may include a plurality of particle collection chambers and may define a plurality of second impingement holes, and the combustor panel may define a plurality of effusion holes. The particle collection panel may be disposed inward of the combustor shell and the combustor panel may be disposed inward of the particle collection panel. Each particle collection chamber may have a closed inward end and an opening defined in an outward end. The particle collection chambers may be configured to entrap particulates.
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Patent Agency Ranking
公开(公告)号：US10760432B2
公开(公告)日：2020-09-01
申请号：US15723461
申请日：2017-10-03
Applicant: United Technologies Corporation
Inventor： Carey Clum , Timothy J. Jennings
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：US10590779B2
公开(公告)日：2020-03-17
申请号：US15832491
申请日：2017-12-05
Applicant: United Technologies Corporation
Inventor： Christopher Whitfield , Carey Clum , Dominic J. Mongillo, Jr.
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.
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公开(公告)号：US20200025083A1
公开(公告)日：2020-01-23
申请号：US16241187
申请日：2019-01-07
Applicant: United Technologies Corporation
Inventor： Dennis M. Moura , Carey Clum
Abstract: According to one embodiment, a gas turbine engine component assembly is provided. The gas turbine engine component assembly comprising: a first component having a first surface and a second surface opposite the first surface, the first component including a cooling hole extending from the second surface to the first surface through the first component, wherein the second surface of the first component is oriented relative to a first airflow path such that airflow in the first airflow path separates from the second surface of the first component; and a first fairing secured to the first component proximate the second surface of the first component, the first fairing being configured to redirect airflow in the first airflow path such that the airflow exits the first fairing oriented parallel with the second surface of the first component.
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公开(公告)号：US10513947B2
公开(公告)日：2019-12-24
申请号：US15613686
申请日：2017-06-05
Applicant: United Technologies Corporation
Inventor： Carey Clum , Adam Generale
Abstract: A turbine assembly may comprise a platform defining a platform cavity cooled by a platform flow with a vane extending from the platform. A platform-fed through cavity is defined by the vane and cooled by a first portion of the platform flow. A direct-fed through flow cavity is defined in the vane and cooled by a direct-fed through flow. The direct-fed through flow cavity and the platform-fed through cavity meet at an outlet to expel an outgoing through flow from the outlet. A platform-fed serpentine cavity may be defined in the vane and separated from the platform-fed through cavity by a divider. The platform-fed serpentine cavity is cooled by a second portion of the platform flow.
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公开(公告)号：US10422229B2
公开(公告)日：2019-09-24
申请号：US15465262
申请日：2017-03-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Carey Clum , Mark F. Zelesky
Abstract: An airfoil may include an external airfoil surface and an airfoil body. The airfoil body may include an external wall structure and an internal wall structure. The external airfoil surface may be adjacent the external wall structure. The airfoil body may define a skin core that is at least partially defined by a first section of the external wall structure and a first section of the internal wall structure. The airfoil body may also define an embedded core that is at least partially defined by the first section of the internal wall structure. An embedded core heat transfer augmentation feature may be formed within the embedded core on an embedded core surface of the first section of the internal wall structure.
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