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1.发明申请公开(公告)号：US20220381434A1
公开(公告)日：2022-12-01
申请号：US17882315
申请日：2022-08-05
Applicant: Raytheon Technologies Corporation
Inventor： Dennis M. Moura , Carey Clum
Abstract: A gas turbine engine component assembly is provided. The gas turbine engine component assembly, comprising: a first component having a first surface, a second surface opposite the first surface, and a cooling hole extending from the second surface to the first surface through the first component; 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 in fluid communication with the cooling hole for cooling the second surface of the second component; and a particulate capture device attached to at least one of the first component and the second component, the particulate capture device configured to aerodynamically separate the airflow from the particulate.
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公开(公告)号：US11649731B2
公开(公告)日：2023-05-16
申请号：US16811249
申请日：2020-03-06
Applicant: Raytheon Technologies Corporation
Inventor： Tracy A. Propheter-Hinckley , Carey Clum , Timothy J. Jennings
CPC classification number: F01D5/187 , B22C9/10 , B22C9/103 , B22C9/24 , F01D9/041 , F01D9/065 , F01D25/12 , F01D5/186 , F05D2220/32 , F05D2230/21 , F05D2230/211 , F05D2240/30 , F05D2260/201 , F05D2260/202 , F05D2260/205 , F05D2260/221
Abstract: Airfoils bodies having a first core cavity and a second core cavity located within the airfoil body that is adjacent the first core cavity. The second core cavity is defined by a first cavity wall, a second cavity wall, a first exterior wall, and a second exterior wall, wherein 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 and a central ridge extends into the second core cavity from at least one of the first cavity wall and the second wall and divides the second core cavity into a two-vortex chamber.
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公开(公告)号：US20210348761A1
公开(公告)日：2021-11-11
申请号：US17380494
申请日：2021-07-20
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Carey Clum , Dennis M. Moura
IPC: F23R3/00
Abstract: A dual wall liner for a gas turbine engine may comprise a shell having a first side and a second side, a panel contacting the shell, the panel at least partially defining a hot gas path through which a hot gas flows, wherein the first side of the shell faces the panel, wherein the shell includes a thermal barrier coating (TBC) disposed on the first side of the shell. The TBC may thermally protect the shell from heat from a hot gas path.
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公开(公告)号：US11719439B2
公开(公告)日：2023-08-08
申请号：US17380494
申请日：2021-07-20
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Carey Clum , Dennis M Moura
IPC: F23R3/00
CPC classification number: F23R3/002 , F23M2900/05004 , F23R2900/00018 , F23R2900/03043 , F23R2900/03045
Abstract: A dual wall liner for a gas turbine engine may comprise a shell having a first side and a second side, a panel contacting the shell, the panel at least partially defining a hot gas path through which a hot gas flows, wherein the first side of the shell faces the panel, wherein the shell includes a thermal barrier coating (TBC) disposed on the first side of the shell. The TBC may thermally protect the shell from heat from a hot gas path.
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Patent Agency Ranking
公开(公告)号：US11492912B2
公开(公告)日：2022-11-08
申请号：US16739254
申请日：2020-01-10
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Brandon W. Spangler , Carey Clum , Matthew A. Devore
Abstract: A gas turbine engine component comprises a body having a leading edge, a trailing edge, and a radial span. One internal channel in the body provides an upstream supply pressure. Another internal channel in body receives the upstream supply pressure and provides a downstream supply pressure. At least one axial rib separates an internal area adjacent to the trailing edge into a plurality of individual cavities. At least one pressure regulating feature is located at an entrance to at least one individual cavity entrance to control downstream supply pressure to the trailing edge. Exits formed in the trailing edge communicate with an exit pressure. The rib and pressure regulating features cooperate such that the downstream supply pressure mimics the exit pressure along the radial span.
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公开(公告)号：US10808548B2
公开(公告)日：2020-10-20
申请号：US15832478
申请日：2017-12-05
Applicant: Raytheon 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. 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：US11725521B2
公开(公告)日：2023-08-15
申请号：US16562630
申请日：2019-09-06
Applicant: Raytheon Technologies Corporation
Inventor： Carey Clum , Dominic J. Mongillo, Jr.
CPC classification number: F01D5/188 , B22C9/04 , B22C9/10 , B22C9/103 , F01D5/187 , F01D5/20 , F01D9/02 , F01D25/12 , F05D2220/32 , F05D2230/211 , F05D2230/50 , F05D2240/301 , F05D2240/304 , F05D2240/305 , F05D2240/306 , F05D2240/307 , F05D2260/202 , F05D2260/2212 , F05D2260/22141 , Y02T50/60
Abstract: Core assemblies for manufacturing airfoils and airfoils made therefrom are described. The core assemblies having a leading edge hybrid skin core positioned relative to a plurality of core bodies and configured to define a leading edge cavity at a leading edge of the manufactured airfoil. The leading edge hybrid skin core extends from a root region toward a tip region in a radial direction, the leading edge hybrid skin core extends above at least one of the plurality of core bodies to define an exit in a tip region of the manufactured airfoil, and the leading edge hybrid skin core has a height-to-width ratio of about 0.8 or less.
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8.发明申请公开(公告)号：US20220316705A1
公开(公告)日：2022-10-06
申请号：US17839188
申请日：2022-06-13
Applicant: Raytheon Technologies Corporation
Inventor： Dennis M. Moura , Carey Clum
Abstract: 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; a threaded stud including a first end and a second end opposite the first end, the threaded stud extending from the second surface of the first component; and a faired body operably secured to the threaded stud, wherein the faired body is shaped to redirect the airflow in a lateral direction parallel to the second surface of the first component such that a cross flow is generated.
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公开(公告)号：US10781697B2
公开(公告)日：2020-09-22
申请号：US15832455
申请日：2017-12-05
Applicant: Raytheon 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 at an outer surface and a cold side wall at an inner surface. The skin passage extends a height in the radial direction, a width in a width direction, and a thickness in a thickness direction. The thickness is less than the width. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage at a core passage surface. 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 first angle relative to the direction of fluid flow in the core passage. The first angle lies in a plane parallel to the thickness direction. The centerline of the resupply hole is arranged at a second angle relative to the direction of fluid flow in the core passage. The second angle lies in a plane parallel to the width direction. The second angle is at an acute angle. The first and second angles are configured to provide a low turbulence flow region in the skin passage.
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