US 12,228,052 B2
Integrally bladed rotor with increased rim bending stiffness
Dikran Mangardich, Richmond Hill (CA); and Krishna Prasad Balike, Brampton (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed on Jul. 19, 2023, as Appl. No. 18/354,714.
Prior Publication US 2025/0027420 A1, Jan. 23, 2025
Int. Cl. F01D 5/34 (2006.01); F01D 5/06 (2006.01)
CPC F01D 5/34 (2013.01) [F01D 5/06 (2013.01); F05D 2220/323 (2013.01); F05D 2240/80 (2013.01); F05D 2260/94 (2013.01)] 18 Claims
OG exemplary drawing
 
1. An integrally bladed rotor for an aircraft engine, comprising:
a hub;
a circumferential array of blades extending from the hub, each blade having an airfoil extending from a gaspath side of a platform provided at a periphery of the hub, an edge of the airfoil disposed at an axial distance L1 from an adjacent axial edge of the platform; and
a projection extending radially inwardly from an interior side of the platform opposite to the gaspath side, the projection having an axial thickness t, a radial height h from the interior side of the platform, and an axial distance L2 from the adjacent axial edge of the platform;
wherein T is a radial thickness of the platform at an axial location of the projection; and
wherein

OG Complex Work Unit Math