INTEGRALLY BLADED ROTOR
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United States of America Patent
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Issued Date -
Jun 13, 2019
app pub date -
Oct 24, 2018
filing date -
Nov 2, 2017
priority date (Note) -
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status (Latency Note)
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Abstract
An integrally bladed rotor for a gas turbine engine includes a rotor portion with an outer periphery. At least one airfoil includes a suction side and a pressure side extending between a leading edge and a trailing edge. The at least one airfoil extends radially from the outer periphery and has an airfoil thickness between the suction side and the pressure side. A first thickness on at least one of the pressure side and suction side of the airfoil in addition to the airfoil thickness that extends radially from the outer periphery defines a crack propagation boundary. A method of fabricating an integrally bladed rotor for a gas turbine engine is also disclosed.
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