US 12,270,542 B2
Combustor liner with shield holes
Anquan Wang, Mason, OH (US); and Eric John Ruggiero, West Chester, OH (US)
Filed by GENERAL ELECTRIC COMPANY, Schenectady, NY (US)
Filed on Feb. 26, 2021, as Appl. No. 17/187,040.
Application 17/187,040 is a continuation of application No. 15/460,924, filed on Mar. 16, 2017, abandoned.
Prior Publication US 2021/0199296 A1, Jul. 1, 2021
Int. Cl. F23R 3/06 (2006.01); F23R 3/00 (2006.01)
CPC F23R 3/002 (2013.01) [F23R 3/06 (2013.01); F23R 2900/03041 (2013.01); F23R 2900/03042 (2013.01); Y02T 50/60 (2013.01)] 14 Claims
OG exemplary drawing
 
1. A combustor for a turbine engine comprising:
a combustor liner having an inner surface defining a combustion zone;
an annular dome mounted upstream of the combustion zone;
a plurality of mixer assemblies spaced circumferentially around the annular dome to form a fuel-air mixture, the fuel-air mixture comprising an axial component and a circumferential component, that is provided to the combustion zone;
a field defining an area of the combustor liner having a plurality of sparsely-spaced film holes defining a first distance between adjacent sparsely-spaced film holes; and
a patch defining an area located within the field at a location where the circumferential component interacts with the combustor liner during operation, the patch having a plurality of densely-spaced shield holes defining a second distance between adjacent densely-spaced shield holes, the second distance smaller than the first distance;
wherein the plurality of sparsely-spaced film holes have a length with a diffuser end defining a film hole exit and the plurality of densely-spaced shield holes have a circular shield hole exit and comprise a cylindrical shape along a full length of each shield hole.