US Patent 10557375 Segregated cooling air passages for turbine vane
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Patent abstract
An airfoil for a gas turbine engine includes a cavity including an internal surface of an outer wall. A baffle is disposed within the cavity and spaced apart from the internal surface. A partition is disposed between the baffle and the internal surface to divide a space between the baffle and the internal surface into at least a first passage and a second passage. A gas turbine engine is also disclosed.
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Patent Inventor Names
Nicholas M. LoRicco0
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Patent Jurisdiction
Patent Number
105573750
Date of Patent
February 11, 2020
0Patent Application Number
158631010
Date Filed
January 5, 2018
0Patent Citations Received
Patent Primary Examiner
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US Patent 10557375 Segregated cooling air passages for turbine vane
Infobox
Is a
Patent jurisdiction
Patent number
10557375
Date of patent
February 11, 2020
Patent application number
15863101
Date Filed
January 5, 2018
Patent primary examiner
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