Patent ID: 7934381

Claim:
A fuel lance for a gas turbine installation with sequential combustion, in which hot gas is produced in a first combustion chamber and expanded in a subsequent turbine, and then flows through a subsequent second combustion chamber in which the fuel lance is arranged for injecting fuel into the hot gas, the fuel lance comprises a lance section which extends in a flow direction of the hot gas and includes at least an outer tube which is arranged concentrically to a lance axis, and a center tube which is concentrically arranged in the outer tube and in which the fuel is guided to a lance tip to be injected from a region of the lance tip through first injection openings on the lance tip into the hot gas, the center tube terminates at a distance from the lance tip and includes an opening at an end thereof which corresponds to a width of the center tube, a chamber is defined between the opening of the center tube and the lance tip, the chamber is delimited by the opening of the center tube and outer tube, the first injection openings are oriented so that the fuel jets which emerge from them form an acute angle with the lance axis.