US 12,305,539 B2
Turbine
Robert Dewhirst, Huddersfield (GB); and Carl M. Wilson, Huddersfield (GB)
Assigned to Cummins Ltd., London (GB)
Appl. No. 18/711,350
Filed by Cummins Ltd, London (GB)
PCT Filed Nov. 17, 2022, PCT No. PCT/GB2022/052915
§ 371(c)(1), (2) Date May 17, 2024,
PCT Pub. No. WO2023/089316, PCT Pub. Date May 25, 2023.
Claims priority of application No. 2116678 (GB), filed on Nov. 18, 2021.
Prior Publication US 2025/0020066 A1, Jan. 16, 2025
Int. Cl. F01D 9/04 (2006.01); F01D 25/16 (2006.01); F01D 25/24 (2006.01)
CPC F01D 9/041 (2013.01) [F01D 25/16 (2013.01); F01D 25/243 (2013.01); F05D 2220/40 (2013.01); F05D 2240/128 (2013.01)] 18 Claims
OG exemplary drawing
 
1. The nozzle ring for a turbine of a turbocharger, the nozzle ring comprising:
a nozzle dividing wall extending generally perpendicular to a longitudinal axis of the nozzle ring; and
at least one nozzle vane extending from the nozzle dividing wall and having a leading edge defining a first radius relative to the longitudinal axis;
wherein the nozzle dividing wall further comprises a circumferentially extending outer rim defining a second radius relative to the longitudinal axis; and
wherein the ratio of the second radius to the first radius is at least around 1.05, and wherein at least one of:
the nozzle dividing wall comprises an annular flange from which the at least one nozzle vane extends, and wherein the outer rim is radially outwards of
the annular flange relative to the longitudinal axis so as to facilitate widening of
the outer rim relative to the nozzle dividing wall and
the outer rim of the nozzle dividing wall comprises a circumferentially extending groove configured to receive a sealing element.