US 11,994,294 B2
Combustor liner
Hiranya Nath, Bengaluru (IN); Ravindra Shankar Ganiger, Bengaluru (IN); and Sripathi Mohan, Bengaluru (IN)
Assigned to GENERAL ELECTRIC COMPANY, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Sep. 13, 2022, as Appl. No. 17/931,700.
Claims priority of application No. 202211027643 (IN), filed on May 13, 2022.
Prior Publication US 2023/0366549 A1, Nov. 16, 2023
Int. Cl. F23R 3/06 (2006.01); F02C 7/04 (2006.01); F23R 3/00 (2006.01)
CPC F23R 3/06 (2013.01) [F02C 7/04 (2013.01); F23R 3/002 (2013.01); F23R 2900/03044 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A combustor comprising:
a skeleton mesh structure comprising a plurality of structural elements configured to mesh together to form the skeleton mesh structure, each of the plurality of structural elements comprising a frame and a plurality of louvers connected to the frame; and
an inner liner mounted to the skeleton mesh structure to define a combustion chamber, the inner liner comprising a plurality of inner planks mounted to the skeleton mesh structure, each of the plurality of inner planks being mounted to the frame of a corresponding one of the plurality of structural elements, the plurality of inner planks being exposable to hot flames within the combustion chamber, each of the plurality of inner planks comprises a plurality of holes,
wherein two successive louvers in the plurality of louvers are configured such that a first distance L1 between bottoms of the two successive louvers in the plurality of louvers is less than or equal to a second distance L2 between tops of the two successive louvers in the plurality of louvers such that the two successive louvers are spaced apart by a gap to define an opening to allow airflow to pass therethrough, and the plurality of holes of each of the plurality of inner planks are oriented such that a first portion of airflow exiting through the opening enters through at least one of the plurality of holes, and a second portion of airflow exiting through the opening propagates along a surface of each of the plurality of inner planks in a space between the bottoms of the two successive louvers and the surface of each of the plurality of inner planks.
 
10. A turbine engine comprising:
a combustor comprising:
(a) a skeleton mesh structure comprising a plurality of structural elements configured to mesh together to form the skeleton mesh structure, each of the plurality of structural elements comprising a frame and a plurality of louvers connected to the frame; and
(b) an inner liner mounted to the skeleton mesh structure to define a combustion chamber, the inner liner comprising a plurality of inner planks mounted to the skeleton mesh structure, each of the plurality of inner planks being mounted to the frame of a corresponding one of the plurality of structural elements, the plurality of inner planks being exposable to hot flames within the combustion chamber,
wherein two successive louvers in the plurality of louvers are configured such that a first distance L1 between bottoms of the two successive louvers in the plurality of louvers is less than or equal to a second distance L2 between tops of the two successive louvers in the plurality of louvers such that the two successive louvers are spaced apart by a gap to define an opening to allow airflow to pass therethrough, and a plurality of holes are defined through each of the plurality of inner planks and are oriented such that a first portion of airflow exiting through the opening enters through at least one of the plurality of holes, and a second portion of airflow exiting through the opening propagates along a surface of each of the plurality of inner planks in a space between the bottoms of the two successive louvers and the surface of each of the plurality of inner planks.