Patent ID: 9194587
Filing Date: 2015-11-24
Classification: F23R

Abstract:
1. A gas turbine combustion chamber comprising: a pilot fuel nozzle arranged in a central section of a cylinder which opens at one end towards a combustion chamber, the pilot fuel nozzle comprises: a pilot cone having an inner side and an outer side, wherein a plurality of main burners are arranged around the pilot fuel nozzle with respect to the radial direction, wherein the pilot cone is arranged on the pilot fuel nozzle at a combustion chamber end and having an opening at the combustion chamber end, such that a pilot flame is formed in the pilot cone by mixing air and pilot fuel in order to ignite a fuel injected by the plurality of main burners, wherein the pilot cone includes a plurality of turbulence generators on its inner side and/or its outer side, wherein the plurality of turbulence generators are trapezoidal and/or triangular strips which are arranged at an opening of the pilot cone over the entire circumference of the opening of the pilot cone, and wherein the trapezoidal and/or triangular strips are arranged on the pilot cone alternately at an angle of +/−30°.