Patent ID: 8001786
Filing Date: 2011-08-23
Classification: F23D,F23R

Abstract:
1. A combustor of a gas turbine engine, comprising: a fuel spray portion configured to spray a fuel to create a diffusion combustion region in a combustion chamber, the fuel spray portion including a fuel atomizing portion configured to atomize the fuel, and a diffusion passage portion disposed downstream of the fuel atomizing portion, the diffusion passage portion having a curved tube shape spreading radially outwardly in a downstream direction and being configured to diffuse the fuel and the air; a pre-mixture supply portion configured to supply a pre-mixture gas including the fuel and an air to create a pre-mixture combustion region in the combustion chamber, the pre-mixture supply portion being positioned concentrically with the fuel spray portion to surround the fuel spray portion; and fuel diffusion restraining means disposed on and projecting from an inner circumferential face of the diffusion passage portion for restraining a diffusion of an injected fuel by separating a stream of the injected fuel away from the inner circumferential face, the fuel diffusion restraining means having a triangular longitudinal section having an inner face that is substantially parallel with an axis of the fuel spray portion, wherein the inner face of the triangular longitudinal cross section of the fuel diffusion restraining means is located radially inward of the fuel spray portion with respect to the axis of the fuel spray portion.