Rotor assembly with structural platforms for gas turbine engines

A rotor assembly for a gas turbine engine comprising:

• a rotatable hub including a main body extending along a longitudinal axis, and including an array of annular flanges extending about an outer periphery of the main body to define an array of annular channels along the longitudinal axis;
• an array of airfoils circumferentially distributed about the outer periphery, each one of the airfoils including an airfoil section extending from a root section received in the annular channels, the airfoil section extending between a leading edge and a trailing edge in a chordwise direction and extending between a tip portion and the root section in a radial direction, and the airfoil section defining a pressure side and a suction side separated in a thickness direction;
• and
• an array of platforms releasably secured to the hub, wherein each of the platforms includes a platform body and opposed rows of flexible retention tabs, each of the rows of retention tabs including a plurality of retention tabs that abut against the sheath of an adjacent airfoils of the array of airfoils to oppose movement of the respective airfoil section in the circumferential direction, wherein a plurality of slots are established along each of the rows of retention tabs, and each of the slots spaces apart an adjacent pair of the retention tabs in a respective one of the rows such that the adjacent pair of the retention tabs are non-overlapping, wherein the rows of retention tabs extend outwardly from the platform body and are dimensioned to wedge the platform between the adjacent airfoils, and each of the retention tabs is integrally formed with the platform body.

A gas turbine engine comprising:

• a fan section including a fan shaft rotatable about an engine longitudinal axis;
• wherein the fan section includes a rotor assembly, the rotor assembly comprising:
• a rotatable hub including a main body mechanically attached to the fan shaft, and including an array of annular flanges extending about an outer periphery of the main body to define an array of annular channels along the engine longitudinal axis;
• an array of airfoils circumferentially distributed about the outer periphery, each one of the airfoils including an airfoil section extending from a root section received in the annular channels;
• and
• an array of platforms releasably secured to the hub, wherein each of the platforms includes a platform body and opposed rows of flexible retention tabs, each of the rows of retention tabs including a plurality of retention tabs that extend from the platform body and are dimensioned to wedge the platform between adjacent airfoils and oppose circumferential movement of the adjacent airfoils relative to the engine longitudinal axis, wherein each of the retention tabs abuts against the airfoil section of a respective one of the adjacent airfoils, a plurality of slots are established along each of the rows of retention tabs, and each of the slots spaces apart an adjacent pair of the retention tabs in a respective one of the rows such that the adjacent pair of the retention tabs are non-overlapping, and each of the retention tabs is integrally formed with the platform body.