Patent ID: 7972113
Filing Date: 2011-07-05
Classification: F01D,F05D,Y02T

Abstract:
1. A turbine rotor blade for use in a gas turbine engine, the turbine rotor blade comprising: an airfoil with a root section formed as a single piece; the root section is formed as a dovetail slot or a fir tree configuration; a first platform half and a second platform half; each of the two platform halves include a slot having at least a side and a bottom and being sized and shaped to complementarily fit the root section to prevent movement of the airfoil in all three degrees of motion and twist about an axis when the platform halves are placed around the root section; the two platform halves are not bonded to the root section so that the airfoil is thermally uncoupled from the two platform halves and the airfoil can be removed from the platform halves when the blade is removed from a slot in a turbine rotor disk by pulling the platform halves away from the root section; and, the airfoil is secured within the two platform halves when the platform is inserted into the slot of the turbine rotor disk.