Methods and apparatus for cooling gas turbine engine rotor assemblies
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United States of America Patent
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Mar 13, 2007
Grant Date -
Mar 2, 2006
app pub date -
Sep 2, 2004
filing date -
Sep 2, 2004
priority date (Note) -
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status (Latency Note)
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Abstract
A method for assembling a rotor assembly for gas turbine engine is provided. The method includes providing a first rotor blade that includes an airfoil, a platform, a shank, and a dovetail. The airfoil extends radially outward from the platform, the shank extends radially inward from the platform, and the dovetail extends from the shank, forming a recess within a portion of the shank. The method also includes coupling the first rotor blade to a rotor shaft using the dovetail, and coupling a second rotor blade to the rotor shaft such that a shank cavity is defined between the first and second rotor blade shanks. During operation, cooling air may enter and pressurize the shank cavity through the recessed portion.
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