US 12,467,366 B2
Turbine engine with a nozzle having cooling features
Nancy Haviland Morton, Cincinnati, OH (US); Harjit S. Hura, Cincinnati, OH (US); Alison E. Schulte, Ortonville, MI (US); Michael David Gervasio, Cincinnati, OH (US); Daniel Osgood, Loveland, OH (US); Marie Myers, Cincinnati, OH (US); and Brett A. Rich, Crestview Hills, KY (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Evendale, OH (US)
Filed on Nov. 27, 2024, as Appl. No. 18/962,252.
Claims priority of provisional application 63/605,323, filed on Dec. 1, 2023.
Claims priority of provisional application 63/605,164, filed on Dec. 1, 2023.
Prior Publication US 2025/0179922 A1, Jun. 5, 2025
Int. Cl. F01D 5/00 (2006.01); F01D 5/14 (2006.01); F01D 5/18 (2006.01); F02C 7/18 (2006.01)
CPC F01D 5/18 (2013.01) [F01D 5/143 (2013.01); F02C 7/18 (2013.01)] 7 Claims
OG exemplary drawing
 
1. A nozzle segment for use in a turbine engine having an engine core including a combustor for generating hot combustion gases, the nozzle segment comprising:
a loading area surface configured to engage an adjacent nozzle segment, wherein the loading area surface defines a loading area (LA) between 0.000209 m2 and 0.000256 m2, inclusive of endpoints;
an inner band segment configured to be oriented in an upstream direction of the engine core and having an inner band radius (IBR) defined by an arc along the inner band segment, the IBR between 0.406 m and 0.411 m, inclusive of endpoints; and
one or more vanes that extend circumferentially, individual vanes of the one or more vanes including:
an airfoil including, an outer surface defining a leading edge, a trailing edge, a suction side, and a pressure side, the airfoil further including slots extending along the trailing edge in a generally radial direction, the slots defining a total slot flow area (SFA) between 0.0000160 m2 and 0.0000581 m2, inclusive of endpoints, and
a baffle insert extending within an internal cavity defined by the outer surface, the baffle insert including baffle walls and cooling holes formed in the baffle walls, the cooling holes defining a total cooling hole area (CHA) between 0.0001060 m2 and 0.0001940 m2, inclusive of endpoints;
wherein:

OG Complex Work Unit Math