TURBINE BLADE SHROUD FOR GAS TURBINE ENGINE WITH POWER TURBINE AND METHOD OF MANUFACTURING SAME
A blade for a gas turbine engine includes an airfoil that includes an internal passage. A shroud is arranged at an end of the airfoil and has a shroud perimeter. Axially spaced knife edges extend radially from the shroud. An area is provided between the knife edges. A pocket is recessed into the are...
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Main Authors | , |
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Format | Patent |
Language | English |
Published |
10.10.2019
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Subjects | |
Online Access | Get full text |
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Summary: | A blade for a gas turbine engine includes an airfoil that includes an internal passage. A shroud is arranged at an end of the airfoil and has a shroud perimeter. Axially spaced knife edges extend radially from the shroud. An area is provided between the knife edges. A pocket is recessed into the area and is circumscribed by a perimeter edge that is arranged interiorly of the shroud perimeter. An outlet fluidly connects the internal passage to the pocket. |
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Bibliography: | Application Number: US201815947254 |