Patent ID: 9435532
Filing Date: 2016-09-06
CPC Classification: F23C,F23D,F23R

Claim Text:
1. Burner of a gas turbine, comprising: at least two part cone shells arranged offset with respect to one another and defining a cone shaped chamber with longitudinal tangential slots for feeding air therein; a lance carrying a liquid fuel nozzle arranged centrally in the cone shaped chamber and configured to inject only a liquid fuel jet, the liquid fuel nozzle having a circular cross section, and wherein a portion of the internal flow path of the nozzle facing the cone shaped chamber is divergent in shape, wherein an internal diffuser angle (α) between a wall of the nozzle and a longitudinal axis of the cone shaped chamber is less than 5° and is constant along the length of the divergent portion of the nozzle, and the diverging portion of the nozzle has a diffuser length to internal nozzle diameter ratio between 2-6, and the internal nozzle diameter is a smaller diameter of the diverging portion, and wherein the cone shaped chamber has a cross section which is greater than a cross section of an exit of the liquid fuel nozzle at a location of fuel injection into the chamber, and wherein the lance terminates at an exit plane of the diverging portion of the nozzle, the liquid fuel nozzle having a first portion with a constant internal diameter, and extending in a direction of the longitudinal axis of the cone shaped chamber to a second portion downstream of the first portion, the second portion facing the cone shaped chamber and is divergent in shape, and wherein the internal diameter of the first portion is equal to an internal diameter of the second portion at an inlet of the second portion; and wherein the liquid fuel nozzle is arranged in the cone shaped chamber such that immediately outside of the nozzle, droplets can start to separate from a generated liquid fuel jet, and the generated liquid jet is substantially cylindrical with a cross section larger than a largest inner cross section of the nozzle.