Patent Number: 7,086,232

Title: Multihole patch for combustor liner of a gas turbine engine

Abstract: A liner for a combustor of a gas turbine engine, including a shell having a first end adjacent to an upstream end of the combustor and a second end adjacent to a downstream end of the combustor, wherein at least one discrete region is subject to distress from impingement of hot gases, a plurality of cooling slots formed in the shell through which air flows for providing a cooling film along a hot side of the shell, and a group of cooling holes formed in the shell in the discrete region to augment the cooling film and provide convective bore cooling to the discrete region.

Inventors: Moertle; George Eric (Cincinnati, OH), Mills; Bruce Ernest (Goshen, OH), Holmes; James Patrick (Loveland, OH), Lind; David Albin (Mason, OH), Harris; Tariz Kay (Cincinnati, OH)

Assignee: General Electric Company

International Classification: F02C 1/00 (20060101); F02G 3/00 (20060101)

Expiration Date: 8/08/02018