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公开(公告)号：US11434768B2
公开(公告)日：2022-09-06
申请号：US17322211
申请日：2021-05-17
Applicant: Raytheon Technologies Corporation
Inventor： Christopher J. Peters , Emma J. Place , Jeffrey J. DeGray , Dominic J. Mongillo , Timothy J. Jennings , Raymond Surace , Jeremy B. Fredette
Abstract: An airfoil core includes a first core portion that has a hybrid skin core, a tip flag core, and a trailing edge core. A second core portion has a serpentine core and a leading edge core.
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公开(公告)号：US20220025769A1
公开(公告)日：2022-01-27
申请号：US17498551
申请日：2021-10-11
Applicant: Raytheon Technologies Corporation
Inventor： Emma J. Place , Carlos Calixtro
IPC: F01D5/18
Abstract: A core is provided for fabricating a blade to include an airfoil. The airfoil includes pressure and suction surfaces, leading and trailing edges extending along the pressure and suction surfaces and a tip shelf with a first sweep configuration and a wall. The core includes channel sections configured to form internal channels within the airfoil by casting processes and tip rods extending from respective portions of the channel sections proximate to a tip shelf location. The respective portions of the channel sections have a second sweep configuration corresponding to the first sweep configuration. The tip rods are configured to extend through the wall at an angle of about 5-12 degrees inclusive relative to a normal angle of the wall during the casting processes to form through-holes angled at about 5-12 degrees inclusive in the wall.
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公开(公告)号：US11898459B1
公开(公告)日：2024-02-13
申请号：US17856332
申请日：2022-07-01
Applicant: Raytheon Technologies Corporation
Inventor： Emma J. Place , Dominic J. Mongillo, Jr. , Jeremy B Fredette
CPC classification number: F01D5/186 , F01D5/02 , F05D2220/3212 , F05D2230/21 , F05D2250/74 , F05D2260/202
Abstract: Disclosed is a turbine blade for a gas turbine engine having a plurality of cooling holes defined therein, the plurality of cooling holes being located in an airfoil of the turbine blade according to coordinates of Table 1, wherein the coordinates of Table 1 are distances from a point of origin O on the turbine blade, the point of origin being located at a center point of an inner diameter edge of a forward root face of a root of the turbine blade.
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公开(公告)号：US11773731B2
公开(公告)日：2023-10-03
申请号：US17568358
申请日：2022-01-04
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Emma J. Place , Jeffrey Michael Jacques , Anthony C. Evans , Joshua W. Richards
CPC classification number: F01D5/22 , F01D5/16 , F01D5/187 , F01D11/006 , F05D2240/55 , F05D2240/80 , F05D2250/711 , F05D2250/712 , F05D2260/20 , F05D2260/96
Abstract: A damper seal for a gas turbine engine includes a damper body extending in a first direction between a leading edge portion and a trailing edge portion, extending in a second direction between first and second sidewalls, and extending in a third direction between a convex outer damper face and a concave inner damper face. The inner damper face establishes a damper pocket. The leading and trailing edge portions slope inwardly from opposite ends of the damper body to bound the damper pocket in the first direction. The first and second sidewalls extend from the leading edge portion to the trailing edge portion and slope inwardly from opposite sides of the damper body to bound the damper pocket in the second direction. The outer damper face is pre-formed according to a first predetermined geometry that substantially corresponds to a second predetermined geometry of a platform undersurface bounding a neck pocket of an airfoil. A method of damping for a gas turbine engine is also disclosed.
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公开(公告)号：US20230045259A1
公开(公告)日：2023-02-09
申请号：US17881803
申请日：2022-08-05
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Emma J. Place , Dominic J. Mongillo , Jeremy B. Fredette
Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes a platform section and an airfoil section extending in a spanwise direction from the platform section to a tip portion establishing a tip. The airfoil section has an external wall defining pressure and suction sides extending in a chordwise direction between a leading edge and a trailing edge, and the pressure and suction sides are spaced apart in a thickness direction between the leading edge and the trailing edge. The tip portion includes a tip pocket and a tip shelf extending inwardly from the tip. The tip pocket and tip shelf are on opposite sides of a shelf wall.
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Patent Agency Ranking
公开(公告)号：US12180857B2
公开(公告)日：2024-12-31
申请号：US18304922
申请日：2023-04-21
Applicant: Raytheon Technologies Corporation
Inventor： Emma J. Place , Bryan P. Dube , Pedro D. Laureano , Bernard Joseph Reilly, III , Mohamed Hassan , Edwin Otero , Andrew Correia , William R. Hackbarth, II , Jeffrey M. Jacques
Abstract: An attachment root for a blade includes a symmetric serration profile with multiple lobes. Contact surfaces of each lobe form equal contact angles with a line normal to a symmetry plane of the serration profile. Non-contact surfaces of lobes form angles greater than three degrees relative to the line that increase in a radially inward direction.
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公开(公告)号：US20240352861A1
公开(公告)日：2024-10-24
申请号：US18304922
申请日：2023-04-21
Applicant: Raytheon Technologies Corporation
Inventor： Emma J. Place , Bryan P. Dube , Pedro D. Laureano , Bernard Joseph Reilly, III , Mohamed Hassan , Edwin Otero , Andrew Correia , William R. Hackbarth, II , Jeffrey M. Jacques
CPC classification number: F01D5/3007 , F01D5/02
Abstract: An attachment root for a blade includes a symmetric serration profile with multiple lobes. Contact surfaces of each lobe form equal contact angles with a line normal to a symmetry plane of the serration profile. Non-contact surfaces of lobes form angles greater than three degrees relative to the line that increase in a radially inward direction.
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公开(公告)号：US11913353B2
公开(公告)日：2024-02-27
申请号：US17881803
申请日：2022-08-05
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Emma J. Place , Dominic J. Mongillo , Jeremy B. Fredette
CPC classification number: F01D5/186 , F01D5/141 , F05D2220/323 , F05D2240/30 , F05D2260/202
Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes a platform section and an airfoil section extending in a spanwise direction from the platform section to a tip portion establishing a tip. The airfoil section has an external wall defining pressure and suction sides extending in a chordwise direction between a leading edge and a trailing edge, and the pressure and suction sides are spaced apart in a thickness direction between the leading edge and the trailing edge. The tip portion includes a tip pocket and a tip shelf extending inwardly from the tip. The tip pocket and tip shelf are on opposite sides of a shelf wall.
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公开(公告)号：US20210277785A1
公开(公告)日：2021-09-09
申请号：US17322211
申请日：2021-05-17
Applicant: Raytheon Technologies Corporation
Inventor： Christopher J. Peters , Emma J. Place , Jeffrey J. DeGray , Dominic J. Mongillo , Timothy J. Jennings , Raymond Surace , Jeremy B. Fredette
Abstract: An airfoil core includes a first core portion that has a hybrid skin core, a tip flag core, and a trailing edge core. A second core portion has a serpentine core and a leading edge core.
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公开(公告)号：US12006836B2
公开(公告)日：2024-06-11
申请号：US17856042
申请日：2022-07-01
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Dominic J. Mongillo , Emma J. Place , Christopher J. Peters , Jeffrey J. DeGray , Timothy J. Jennings , Raymond Surace , Jeremy B. Fredette
IPC: F01D5/18
CPC classification number: F01D5/18 , F05D2220/32 , F05D2230/60 , F05D2260/20
Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes an airfoil section extending in a radial direction from a root section to a tip portion. The airfoil section has an external wall and an internal wall. The airfoil section establishes an internal cooling arrangement including a first cooling passage having a first section and a tip flag section. The tip flag section extends in the chordwise direction along the tip portion from the first section. The first section includes a plurality of branched paths established by at least one turning vane.
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