Turbine blade cooling hole arrangement

Number of patents in Portfolio can not be more than 2000

United States of America

PATENT NO 11208898
SERIAL NO

16780368

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Abstract

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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 Owner(s)

  • RAYTHEON TECHNOLOGIES CORPORATION

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Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Jariwala, Parth Cambridge, US 10 31
LoRicco, Nicholas M Windsor, US 40 134
Lundgreen, Ryan Granby, US 8 4
Morton, Jeffrey T Manchester, US 27 115
Niezelski, David A Manchester, US 19 62
Schneider, Alex J South Glastonbury, US 10 21

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