Gas turbine engine turbine blade tip cooling
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United States of America Patent
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Sep 27, 2016
Grant Date -
Jul 31, 2014
app pub date -
Dec 28, 2012
filing date -
Dec 28, 2012
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil having an exterior surface that extends in a radial direction to a tip. A camber line at the tip extends from the leading edge to the trailing edge. Pressure and suction side shelves are arranged in the exterior surface on opposing sides of the camber line respectively in the pressure and suction side walls. A plateau is proud of and separates the pressure and suction side shelves. The plateau is arranged along the camber line and extends to the leading edge.
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Cited Art Landscape
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