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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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