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US Patent 10107109 Gas turbine engine component cooling assembly

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Patent Citations Received
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US Patent 12110810 Gas turbine engine bleed air flow control
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US Patent 11988155 Combined power system
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US Patent 11905975 Radial compressor with leading edge air injection
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Patent abstract

A rotor blade assembly includes at least one rotor blade including an airfoil that has a leading edge internal cooling passage that extends through the rotor blade and is in communication with cooling holes along a leading edge of the airfoil. A compression portion includes a compression passage that is in communication with the leading edge internal cooling passage.

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Michael G. McCaffrey0
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Infobox
Is a
Patent
Patent
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Patent Jurisdiction
United States Patent and Trademark Office
United States Patent and Trademark Office
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Patent Number
101071090
Date of Patent
October 23, 2018
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Patent Application Number
149652270
Date Filed
December 10, 2015
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Patent Citations Received
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US Patent 10934845 Dual cooling airflow to blades
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US Patent 11021961 Rotor assembly thermal attenuation structure and system
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Patent Primary Examiner
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Igor Kershteyn
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Edits on 12 Feb, 2022
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Patent citations received
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US Patent 11021961 Rotor assembly thermal attenuation structure and system
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US Patent 10934845 Dual cooling airflow to blades
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 US Patent 10107109 Gas turbine engine component cooling assembly

Infobox
Is a
Patent
Patent
Patent jurisdiction
United States Patent and Trademark Office
United States Patent and Trademark Office
Patent number
10107109
Date of patent
October 23, 2018
Patent application number
14965227
Date Filed
December 10, 2015
Patent primary examiner
‌
Igor Kershteyn

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