US 2017/0248317 A1 · Combustor Assembly

Abstract

A combustor assembly for a gas turbine engine includes an inner liner, an outer liner, and a combustor dome. The inner liner, outer liner, and combustor dome together define at least in part a combustion chamber having an annulus height. Additionally, the combustor assembly includes a fuel-air injector hardware assembly positioned at least partially within an opening of the combustor dome. The fuel-air injector hardware assembly includes a heat shield located at least partially within the combustion chamber, the heat shield defining an outer diameter. A ratio of the annulus height of the combustion chamber to the outer diameter of the heat shield may be at least about 1.5:1.

Claims20

Dependent claims

A combustor assembly for a gas turbine engine, the combustor assembly comprising:

an inner liner, an outer liner, and a combustor dome together defining at least in part a combustion chamber having an annulus height, the combustor dome additionally defining an opening;
and
a fuel-air injector hardware assembly positioned at least partially within the opening of the combustor dome and comprising a heat shield located at least partially within the combustion chamber for shielding at least a portion of the fuel-air injector hardware assembly, the heat shield defining an outer diameter, a ratio of the annulus height of the combustion chamber to the outer diameter of the heat shield being at least about 1.3:1.

Dependencies are inferred from the claim text.

Combustor Assembly

Life of this patent

Combustor Assembly

Life of this patent

Abstract

Claims20