Patent ID: 6834506
Filing Date: 2004-12-28
Classification: F23C,F23R

Abstract:
A main liquid fuel injection device for a combustion chamber of a gas turbine having a premixing chamber comprising:a plurality of generally radially extending, circumferentially spaced blades arranged about an axis of symmetry, each said blade having at least one fuel supply channel for receiving liquid fuel and injecting the fuel through a fuel injection port along a surface of the blade into the premixing chamber, each said blade having at least one cooling air supply channel for receiving cooling air and injecting the air through a cooling air injection port along a surface of the blade spaced from said fuel injection port and into the premixing chamber, enabling the flow of cooling air from the at least one cooling air supply channel to cool the blades; wherein said at least one cooling air supply channel and said at least one fuel supply channel in each blade are arranged in heat exchange relation relative to one another, enabling the flow of cooling air in the at least one cooling air supply channel to cool the at least one fuel supply channel, thereby minimizing or eliminating deposition of carbon residue on blade surfaces.