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Patent Agency Ranking
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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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：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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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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