US 12,286,905 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 RTX CORPORATION, Farmington, CT (US)
Filed on Aug. 25, 2023, as Appl. No. 18/456,126.
Application 18/456,126 is a division of application No. 17/380,397, filed on Jul. 20, 2021, granted, now 11,753,951.
Application 17/380,397 is a continuation in part of application No. 16/163,641, filed on Oct. 18, 2018, granted, now 11,092,020, issued on Aug. 17, 2021.
Prior Publication US 2023/0399956 A1, Dec. 14, 2023
Int. Cl. F01D 5/30 (2006.01); F01D 5/02 (2006.01); F01D 5/14 (2006.01); F01D 5/28 (2006.01); F01D 11/00 (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)] 20 Claims
OG exemplary drawing
 
1. A rotor assembly for a gas turbine engine comprising:
a rotatable hub including a metallic 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;
a plurality of retention pins, each one of the retention pins extending through the root section of a respective one of the airfoils and through the array of annular flanges to mechanically attach each root section to the hub; and
wherein each of the retention pins includes a plurality of segments slideably received on an elongated carrier, and the carrier defines a curved pin axis when in an installed position.