US 11,753,951 B2
Rotor assembly for gas turbine engines
Jason Husband, South Glastonbury, CT (US); James Glaspey, Farmington, CT (US); and Aaron John Pepin, West Hartford, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RAYTHEON TECHNOLOGIES CORPORATION, Farmington, CT (US)
Filed on Jul. 20, 2021, as Appl. No. 17/380,397.
Application 17/380,397 is a continuation of application No. 16/163,641, filed on Oct. 18, 2018, granted, now 11,092,020.
Prior Publication US 2021/0348515 A1, Nov. 11, 2021
This patent is subject to a terminal disclaimer.
Int. Cl. F01D 5/30 (2006.01); F01D 5/14 (2006.01); F01D 5/28 (2006.01); F01D 11/00 (2006.01); F01D 5/02 (2006.01)
CPC F01D 5/3053 (2013.01) [F01D 5/02 (2013.01); F01D 5/147 (2013.01); F01D 5/282 (2013.01); F01D 5/3038 (2013.01); F01D 11/008 (2013.01); F05D 2240/301 (2013.01); F05D 2240/80 (2013.01); F05D 2260/30 (2013.01); F05D 2260/31 (2013.01); F05D 2300/603 (2013.01); F05D 2300/702 (2013.01)] 12 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a fan section including a fan shaft rotatable about an engine longitudinal axis;
at least one bearing assembly supporting the fan shaft; and
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, wherein each of the annular channels receives a composite reinforcement member that extends about the outer periphery;
an array of airfoils each including an airfoil section extending from a root section; and
a plurality of retention pins, each of the retention pins extending through the root section of a respective one of the airfoils, across the annular channels at a position radially outward of the respective composite reinforcement member, and through the annular flanges to mechanically attach each root section to the hub; and
a fan drive turbine that drives the fan shaft through a geared architecture, wherein the at least one bearing assembly is positioned radially outward of the outer periphery of the hub with respect to the engine longitudinal axis, and the at least one bearing assembly supports the fan shaft at a position radially outward of the geared architecture with respect to the engine longitudinal axis.