TURBINE AIRFOIL COOLING SYSTEM WITH PLATFORM COOLING CHANNELS
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United States of America Patent
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Issued Date -
Mar 23, 2017
app pub date -
Jun 5, 2014
filing date -
Jun 5, 2014
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Abstract
A cooling system (10) positioned within a turbine airfoil (12) useable in a turbine engine and having cooling channels (16) positioned within a platform (18) of the turbine airfoil (12) with exhaust outlets (20) at the pressure and suction side edges (22, 24) to prevent hot gas ingestion under the platform (18) is disclosed. The cooling channels (16) may be formed from main channels (26) extending from cooling fluid supply channels (64) aligned with the airfoil (12) and branch channels (30) extending between the main channels (26) and the pressure or suction side edges (22, 24). The cooling system (10) reduces the cooling surface area adjacent to the airfoil fillet (32) at the intersection (34) of the platform (18) and airfoil (12) and increases cooling surface area adjacent to the pressure side and suction side mate faces (22, 24) as compared with conventional designs. Such configuration of the cooling system (10) yields a more uniform platform temperature distribution, colder and higher pressure cooling air for platform cooling and less manufacturing expense than conventional designs.
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