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公开(公告)号：US20240410284A1
公开(公告)日：2024-12-12
申请号：US18331124
申请日：2023-06-07
Applicant: Raytheon Technologies Corporation
Inventor： Jeffrey T. Morton
Abstract: A turbine vane includes an airfoil section with an airfoil wall defining a leading edge and a trailing edge. A first side extends from the leading edge to the trailing edge and extends from a first end of the airfoil section to a second end of the airfoil section. A second side extends from the leading edge to the trailing edge and extends from the first end to the second end of the airfoil section. The airfoil wall also circumscribes an internal core cavity. A platform is attached to the first end of the airfoil section and a platform cavity is formed in the platform. A baffle is in the internal core cavity and includes a baffle tube extending from a first tube end to a second tube end. A chimney is connected to the first tube end and extends completely through the platform cavity.
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公开(公告)号：US11661852B2
公开(公告)日：2023-05-30
申请号：US17429097
申请日：2020-02-07
Applicant: Raytheon Technologies Corporation
Inventor： Nicholas M. LoRicco , Parth Jariwala , Alex J. Schneider , Bret M. Teller , Matthew S. Gleiner , Jeffrey T. Morton
CPC classification number: F01D5/187 , F01D5/087 , F05D2240/304 , F05D2250/711 , F05D2250/712 , F05D2260/201
Abstract: A turbine blade has an attachment root and an airfoil. A cooling passageway system has a plurality of trunks extending from respective inlets along the root inner diameter end from a leading trunk near a first axial end to a trailing trunk near a second axial end; and a plurality of outlets along the airfoil including trailing edge outlets fed by the trailing trunk. Viewed normal to a root end-to-end centerplane: the trailing trunk has a turn passing forward and then rearward; an outside of the turn protrudes forward; and the outside of the turn has a tighter curvature than an inside of the turn.
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公开(公告)号：US11208898B1
公开(公告)日：2021-12-28
申请号：US16780368
申请日：2020-02-03
Applicant: Raytheon Technologies Corporation
Inventor： Alex J. Schneider , Parth Jariwala , Nicholas M. LoRicco , Ryan Lundgreen , David A. Niezelski , Jeffrey T. Morton
Abstract: A turbine blade for a gas turbine engine. The turbine blade having a plurality of cooling holes defined therein, wherein the plurality of cooling holes are located in the turbine blade according to the coordinates of Table 1 and at least some of the plurality of cooling holes are located in an airfoil of the turbine blade.
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Patent Agency Ranking
公开(公告)号：US11060408B1
公开(公告)日：2021-07-13
申请号：US16780368
申请日：2020-02-03
Applicant: Raytheon Technologies Corporation
Inventor： Alex J. Schneider , Parth Jariwala , Nicholas M. LoRicco , Ryan Lundgreen , David A. Niezelski , Jeffrey T. Morton
Abstract: A turbine blade for a gas turbine engine. The turbine blade having a plurality of cooling holes defined therein, wherein the plurality of cooling holes are located in the turbine blade according to the coordinates of Table 1 and at least some of the plurality of cooling holes are located in an airfoil of the turbine blade.
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公开(公告)号：US20240426245A1
公开(公告)日：2024-12-26
申请号：US18213667
申请日：2023-06-23
Applicant: Raytheon Technologies Corporation
Inventor： Jon E. Sobanski , Jeffrey T. Morton , Andrew E. Breault
Abstract: An assembly is provided for an aircraft powerplant. This assembly includes a bladed rotor, a shroud and an actuation system. The bladed rotor includes a rotor base and a plurality of rotor blades arranged circumferentially around and connected to the rotor base. The shroud is adjacent tips of the rotor blades. The actuation system includes a water source and an actuator coupled to the shroud. The actuation system is configured to direct a quantity of water from the water source to the actuator to control clearance between the shroud and the tips of the rotor blades.
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公开(公告)号：US11346230B1
公开(公告)日：2022-05-31
申请号：US16780368
申请日：2020-02-03
Applicant: Raytheon Technologies Corporation
Inventor： Alex J. Schneider , Parth Jariwala , Nicholas M. LoRicco , Ryan Lundgreen , David A. Niezelski , Jeffrey T. Morton
Abstract: A turbine blade for a gas turbine engine. The turbine blade having a plurality of cooling holes defined therein, wherein the plurality of cooling holes are located in the turbine blade according to the coordinates of Table 1 and at least some of the plurality of cooling holes are located in an airfoil of the turbine blade.
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公开(公告)号：US20250027423A1
公开(公告)日：2025-01-23
申请号：US18224934
申请日：2023-07-21
Applicant: Raytheon Technologies Corporation
Inventor： Andrew E. Breault , Jeffrey T. Morton
Abstract: An assembly is provided for an aircraft powerplant. This assembly includes a rotating assembly, a first structure, a second structure and a thrust bearing. The rotating assembly includes a first bladed rotor and a second bladed rotor. The first bladed rotor includes a plurality of first rotor blades. The second bladed rotor includes a plurality of second rotor blades. The first structure is configured as or otherwise includes a first shroud. The first shroud circumscribes the first bladed rotor. The first shroud is adjacent first tips of the first rotor blades. The second structure is configured as or otherwise includes a second shroud. The second shroud circumscribes the second bladed rotor. The second shroud is adjacent second tips of the second rotor blades. The second shroud is configured to move along an axis relative to the first shroud. The thrust bearing couples the rotating assembly to the second structure.
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公开(公告)号：US20220098988A1
公开(公告)日：2022-03-31
申请号：US17429097
申请日：2020-02-07
Applicant: Raytheon Technologies Corporation
Inventor： Nicholas M. LoRicco , Parth Jariwala , Alex J. Schneider , Bret M. Teller , Matthew S. Gleiner , Jeffrey T. Morton
Abstract: A turbine blade has an attachment root and an airfoil. A cooling passageway system has a plurality of trunks extending from respective inlets along the root inner diameter end from a leading trunk near a first axial end to a trailing trunk near a second axial end; and a plurality of outlets along the airfoil including trailing edge outlets fed by the trailing trunk. Viewed normal to a root end-to-end centerplane: the trailing trunk has a turn passing forward and then rearward; an outside of the turn protrudes forward; and the outside of the turn has a tighter curvature than an inside of the turn.
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