US 2004/0055306 A1 · Premixed pilot burner for a combustion turbine engine

Abstract

A combustor (40) for a gas turbine engine is provided with a premix pilot fuel stage (42) in order to reduce the emission of oxides of nitrogen from the engine. An in-service engine may be modified to add the premix pilot fuel stage by delivering premix pilot fuel to a ring manifold (42) for tip-feeding a premix pilot fuel outlet member such as a swirler vane (78) or fuel peg (124). In this manner, complex and expensive components such as the top hat (46), support housing (48) and diffusion pilot burner assembly (44) may be used without modification. Thermal stresses caused by the differential cooling of the ring manifold by the premix pilot fuel (96) are reduced by a heat shield (94) installed within the manifold.

Claims28

Dependent claims

A combustor for a gas turbine engine comprising:

a combustor basket having a central axis;
a diffusion pilot nozzle disposed along the central axis within the combustor basket for delivering a diffusion pilot fuel to a combustion chamber;
a main fuel premixer section circumferentially disposed about the central axis radially outward of the diffusion pilot nozzle for delivering a premixed main fuel and air mixture to the combustion chamber;
a premix pilot fuel manifold disposed radially inward of the main fuel premixer section and radially outward of the diffusion pilot nozzle;
and
a pilot fuel premixer section radially disposed radially outward of the diffusion pilot nozzle and in fluid communication with the premix pilot fuel manifold to receive a premix pilot fuel for delivering a mixture of the premix pilot fuel and air to the combustion chamber.

3 more elements

Dependencies are inferred from the claim text.

Premixed pilot burner for a combustion turbine engine

Life of this patent

Premixed pilot burner for a combustion turbine engine

Life of this patent

Abstract

Claims28