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US Patent 12006836 Cooling arrangement for gas turbine engine component
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Patent
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Date Filed
July 1, 2022
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Date of Patent
June 11, 2024
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Patent Applicant
Raytheon Technologies
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Patent Application Number
17856042
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Patent Citations
US Patent 7413403 Turbine blade tip cooling
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US Patent 7597539 Turbine blade with vortex cooled end tip rail
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US Patent 7625178 High effectiveness cooled turbine blade
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US Patent 7665968 Cooled rotor blade
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US Patent 7857587 Turbine blades and turbine blade cooling systems and methods
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US Patent 8011889 Turbine blade with trailing edge tip corner cooling
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US Patent 8092179 Blade tip cooling groove
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US Patent 8702391 Gas turbine blade
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US Patent 9546554 Gas turbine engine components with blade tip cooling
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US Patent 9890644 Foundry core assembly for manufacturing a turbomachine blade, associated method of manufacturing a blade and associated blade
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•••
Patent Inventor Names
Emma J. Place
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Timothy J. Jennings
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Jeremy B. Fredette
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Dominic J. Mongillo
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Raymond Surace
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Christopher J. Peters
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Jeffrey J. DeGray
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Patent Jurisdiction
United States Patent and Trademark Office
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Patent Number
12006836
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Patent Primary Examiner
Courtney D Heinle
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CPC Code
F05D 2230/60
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F05D 2260/20
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F01D 5/18
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