A burner of a turbomachine, particularly a gas turbine engine, has at least one burner section having an annular wall surrounding a respective section of a burner interior, the annular wall including: an annular inner surface delimiting the burner interior, and a plurality of dampening cavities for the dampening of thermo-acoustic vibrations in the burner interior, each dampening cavity being connected to the annular inner surface through at least a dampening hole. A method of manufacturing such a burner includes additive manufacturing of the annular wall as an integrally formed component, or additive manufacturing of the upstream burner section, wherein the intermediate burner section and the downstream burner section as integrally formed component.

A method for determining fatigue lifetime consumption of an engine component, by defining a reference thermal load cycle, the reference thermal load cycle being characterized by a reference load cycle amplitude and a reference load cycle time, and determining a reference load cycle lifetime consumption. The method includes measuring a temperature of the engine component, determining a thermal load cycle based upon the temperature measurement, determining a load cycle amplitude, determining a load cycle time, relating the load cycle time to the reference load cycle time, thereby determining a load cycle time factor, relating the load cycle amplitude to the reference load cycle amplitude, thereby determining a load cycle amplitude factor, combining the load cycle time factor and the load cycle amplitude factor into a combined load cycle factor for determining a load cycle lifetime consumption.

The invention relates to a can-combustor for a can-annular combustor arrangement in a gas turbine. The can combustor includes an essentially cylindrical casing with an axially upstream front panel and an axially downstream outlet end. The can combustor further includes a number of premixed burners, extending in an upstream direction from said front panel and having a burner exit, supported by this front panel, for supplying a fuel/air mixture into a combustion zone inside the casing. Up to four premixed burners are attached to the front panel in a substantially annular array. Each burner has a conical swirl generator and a mixing tube to induce a swirl flow of said fuel/air mixture.

A burner of a turbomachine has an upstream burner section providing a first fuel and an oxygen containing fluid to an upstream end of a burner interior, a downstream burner section for providing a second fuel to a downstream end of the burner interior, and an intermediate burner section between the two sections. The intermediate burner section has an annular wall surrounding a mid-section of the burner interior. The annular wall has an annular cooling fluid passage, for guiding the oxygen containing fluid, and an annular fuel passage for guiding the second fuel to the downstream burner section, the annular fuel passage being more distant to the burner interior than the annular cooling fluid passage. Two annular slots are incorporated into the annular wall. The upstream burner section has at least one integrated fuel tube through a body of the upstream burner section, configured to feed the annular fuel passage.

A method is disclosed for operating an axially staged mixer arrangement with dilution air or dilution gas injection in connection with a combustion arrangement of a gas turbine engine or turbo machinery, having at least one combustion chamber, at least one mixer arrangement for admixing air or gas portions to the hot gas flow leaving the combustion chamber. The mixer arrangement includes a plurality of injectors for admixing air portions to cool at least the hot gas flow leaving combustion chamber. The spacing between the last injection location of acting injectors and at least one subsequently arranged dilution air injection, inside of the mixer arrangement in the hot gas flow, where there is no node between the injection locations, corresponds to a distance equal or approximating to half of convective wave length.

A method is provided for operating a gas turbine installation which has at least one compressor for compressing combustion air, at least one combustion chamber for combusting a supplied fuel, using the compressed combustion air, and also at least one turbine which is exposed to throughflow by the hot gases from the at least one combustion chamber. Both a first fuel on a carbon base, especially in the form of natural gas, and also a second fuel, in the form of a hydrogen-rich fuel or pure hydrogen, are used as fuel. A reduction of the CO.sub.2 emission without basic modifications to the installation is achieved by the first and the second fuels being intermixed and combusted together in the at least one combustion chamber.

A burner assembly for a combustor is provided with a pilot burner extending along a longitudinal axis and a premix burner surrounding the pilot burner; the pilot burner being integral with the premix burner.

A premixed dual fuel burner includes a burner head, a burner interior elongated along a main axis and having an upstream side enclosed by a swirler and a downstream side enclosed by a premixing section, and an injection component. The burner head and sides are serially arranged. The swirler includes an inlet section for introducing air and a main gas fuel. The injection component has a tapering structure positioned along the main axis which extends from the burner head into the burner interior. The injection component tapers from a burner head side and an injection side along the main axis. At the injection side a liquid fuel outlet introduces a main liquid fuel into the burner interior. The injection side is disposed in the burner interior. At least one of the at least one liquid fuel outlet is at a side of the injection side of the injection component.

A Helmholtz damper for a combustor of a gas turbine includes an enclosure defining a damping volume from which a neck portion extends and which has a flow path (F) for cooling and purging air with an inlet opening and an outlet opening to the enclosure. The outlet opening is formed in the neck portion. A seal is arranged at the neck portion adjacent to the outlet opening for cooling and purging air such that a cooling effect of the seal is provided.

A combustor arrangement includes a combustion chamber with a front panel, and a premix burner of the multi-cone type, which is connected to the front panel through an elongated mixing zone in an axially moveable fashion by a sealed sliding joint. A wide range of axial variation of the burner with a minimized influence of the leakage air flow on the oxidation process within the flame is achieved by positioning the sealed sliding joint upstream of the mixing zone.