Turbine airfoil with leading edge impingement cooling
An example gas turbine engine airfoil (60) includes an airfoil wall (64) establishing a cavity (84) that extends axially from an airfoil leading edge portion (68) to an airfoil trailing edge portion (72) and extends radially from an airfoil inner end (76) to an airfoil outer end (80). The cavity (84...
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Main Authors | , , |
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Format | Patent |
Language | English French German |
Published |
29.08.2018
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Subjects | |
Online Access | Get full text |
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Summary: | An example gas turbine engine airfoil (60) includes an airfoil wall (64) establishing a cavity (84) that extends axially from an airfoil leading edge portion (68) to an airfoil trailing edge portion (72) and extends radially from an airfoil inner end (76) to an airfoil outer end (80). The cavity (84) is configured to receive a baffle (54) that is spaced from the airfoil leading edge portion (68) such that an impingement cooling area (92) is established between the airfoil leading edge portion (68) and the baffle (54) when the baffle (54) is received within the cavity (84). An array of nonuniformly distributed features (120) is disposed on the airfoil wall (64) within the impingement cooling area (92). The features (120) are configured to influence airflow within the impingement cooling area (92). |
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Bibliography: | Application Number: EP20100250362 |