US 11,814,980 B2
Bladed disc
Sean A Walters, Bristol (GB); John Irving, Derby (GB); Nomesh P Kandaswamy, Bangalore (IN); Jessica Kennedy, Derby (GB); Benjamin Littley, Derby (GB); Kali Charan Nayak, Bangalore (IN); and Guy D Snowsill, Derby (GB)
Assigned to ROLLS-ROYCE plc, London (GB)
Filed by ROLLS-ROYCE plc, London (GB)
Filed on Oct. 14, 2022, as Appl. No. 17/966,285.
Claims priority of application No. 2114773 (GB), filed on Oct. 15, 2021.
Prior Publication US 2023/0122071 A1, Apr. 20, 2023
Int. Cl. F01D 5/06 (2006.01); F01D 5/30 (2006.01)
CPC F01D 5/06 (2013.01) [F01D 5/30 (2013.01); F05D 2220/323 (2013.01); F05D 2250/71 (2013.01)] 11 Claims
OG exemplary drawing
 
1. A bladed disc system for a turbine engine comprising a disk portion and a plurality of blade portions which are associated with a stator section and an intercavity sealing portion,
the disc portion being shaped such that the blade portions are able to fit within firtree slots in the disc portion, each of the blade portions comprising an aerofoil section and a root section, the aerofoil section having a portion shaped such that they extend proximate to the intercavity sealing portion,
the disc portion extending from a portion that connects with a drum to an outer edge at which the blade portions are connected with the disc portion having a width transition region in which a thickness of the disc portion increases from the point at which the disc portion connects to the drum to an outer edge at which the disc portion holds the blade portions,
wherein the width transition region has a curved width transition region with a radius of curvature r, and an overhanging portion which extends into an intercavity spacing between the width transition region and the intercavity sealing portion, and
wherein the radius of curvature r of the width transition region has a ratio with a width of the disc portion at the start of the curvature w before the width transition region with the value of the ratio r/w being between 0.35 and 1.1.