Patent ID: 8196409

Claim:
A fuel supply arrangement for a gas turbine burner ( 16 ), comprising a rear section (C) external to the burner ( 16 ) located between a turbine wall ( 27 ) and a fuel distribution system interface ( 19 ) directing fuel into fuel supply circuits, said fuel distribution system interface ( 19 ) having four fuel connections, for liquid fuel, gaseous fuel, pilot gas and liquid pilot fuel; an intermediate section (B) located between the turbine wall ( 27 ) and the backside wall ( 28 ) of a distribution chamber ( 33 ); and a front section (A) in front of the second section (B) located between said backside wall ( 28 ) of the distribution chamber ( 33 ) and a burner central backside block ( 29 ); said fuel distribution arrangement comprising a pipe ( 8 ) for gaseous fuel, a pipe ( 1 ) for liquid fuel, particularly oil, as well as a pipe ( 5 ) for pilot gas, and a pipe for liquid pilot fuel ( 6 ), particularly pilot oil; wherein in the rear section (C) the pipe ( 8 ) for gaseous fuel and the pipe ( 1 ) for liquid fuel are arranged concentrically, and in at least one portion of the intermediate section (B) the pipe ( 8 ) for gaseous fuel is arranged non-concentrically with the liquid fuel pipe ( 1 ).