Combustor liner for a can-annular gas turbine engine and a method for constructing such a liner

Abstract

A combustor liner (30) for a can-annular gas turbine engine (10) and a method for constructing such a liner are provided. The combustor liner includes an annular wall member (32) A cooling channel (34, 42, 50, 54, 56, 58) is formed through the wall member and extends from an inlet end of the liner to an outlet end of the liner A property of the cooling channel may be varied along a length of the cooling channel. The cooling channel may be formed through the combustor liner using an electro-chemical machining (ECM) process or a three dimensional printing process (3DP).

Description

[0001]This application claims benefit of the 6 Feb. 2013 filing date of U.S. provisional patent application No. 61 / 761,367 which is incorporated by reference herein.FIELD OF THE INVENTION[0002]The present invention is generally related to gas turbine engines and, more particularly, to a combustor liner for a gas turbine engine, and a method for constructing such a linerBACKGROUND OF THE INVENTION[0003]Power generation systems, such as can-annular gas turbine engines, include sophisticated combustion components and processes for improving combustion efficiency. Market trends push for longer lifetime for components of the engine, reduced emissions of nitrogen oxides (NOx) and higher firing temperatures. Known combustor liners for can-annular gas turbine engines typically involve a pair of concentric rings, such as a plate with grooves and a sleeve which cooperate to direct cooling air to maintain appropriate liner temperatures at the combustor exhaust zone. These grooves are construct...

AI Technical Summary

Benefits of technology

The present invention relates to a new combustor liner for a gas turbine engine and a method for constructing it. The new combustor liner is designed to improve combustion efficiency and reduce emissions of nitrogen oxides. The invention solves the problem of structural limitations in known combustor liners, which may prevent the liner from being tailored to meet specific thermal transfer demands. The new combustor liner is formed using a process of subtraction or addition of material, which allows for the cooling channel to be designed more efficiently. The invention also includes specific shapes of cooling channels that can be used to further improve the cooling performance of the combustor liner. Overall, the invention provides an improved combustor liner for gas turbine engines that can better meet the demands of high-efficiency and low-emissions requirements.

Problems solved by technology

These grooves are constructed using traditional machining techniques, and, consequently are not suited for structural refinements which would allow to more efficiently meeting thermal transfer demands along the combustor liner Thus, there continues to be a need for an improved combustor liner for a can-annular gas turbine engine, and a method for constructing such a liner.

Images