A pilot burner for a combustor includes an inner conduit configured to deliver a fuel, and an outer conduit concentric with the inner conduit and configured to deliver air. An inner wall defines an inner plenum, and a partition wall is radially outward of the inner wall and defines an intermediate plenum with at least a portion of the inner wall. Exit passages fluidly couple the inner plenum to the intermediate plenum. An outer wall defines an outer plenum with at least a portion of the partition wall. A crossover section includes passages fluidly coupling the inner conduit to the outer plenum, and passages fluidly coupling the outer conduit to the inner plenum. An end plate includes openings to direct fuel, air for combustion, and air for cooling from the respective plenums.

A pilot burner for a combustor includes an inner conduit configured to deliver a fuel, and an outer conduit concentric with the inner conduit and configured to deliver air. An inner wall defines an inner plenum, and a partition wall is radially outward of the inner wall and defines an intermediate plenum with at least a portion of the inner wall. Exit passages fluidly couple the inner plenum to the intermediate plenum. An outer wall defines an outer plenum with at least a portion of the partition wall. A crossover section includes passages fluidly coupling the inner conduit to the outer plenum, and passages fluidly coupling the outer conduit to the inner plenum. An end plate includes openings to direct fuel, air for combustion, and air for cooling from the respective plenums.

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 concerns a gas turbine combustion system, including a gas turbine. The gas turbine includes at least one compressor, at least one combustion chamber for generating working gas, wherein the combustion chamber connected to receive compressed air from the compressor, at least one turbine connected to receive working gas from the combustion chamber. The combustion chamber consists of an individual can-combustor or comprising a number of can-combustors arranged in an annular can-architecture, wherein the can-combustor having at least one premixed burner. The ignition of the mixture starts at the premixed burner outlet and the flame is stabilized in the region of the premixed burner outlet by means of a backflow zone. The can-combustor comprising a number of premixed burners arranged uniformly or divided at least in two groups within the can-combustor.

A combustion chamber of a gas turbine including first and second premixed fuel supply devices connected to a combustion device having first zones connected to the first premixed fuel supply devices and second zones connected to the second premixed fuel supply devices. The second fuel supply devices are shifted along a combustion device longitudinal axis with respect to the first fuel supply devices. The first zones are axially upstream of the second premixed fuel supply devices.

A device for the post-combustion of exhaust air, comprises a burner, which has a fuel nozzle, and a burner cone and which protrudes in a raw-gas chamber, into an exhaust-air flow of exhaust air to be treated at least by the burner cone of the burner. The burner cone has a one- or a multi-part wall, which wall surrounds the pre-mixing chamber and has one or more wall segments. The fuel nozzle comprises an opening of at least one fuel outlet for discharging fuel into the pre-mixing chamber. The wall bounding the pre-mixing chamber outwardly on the lateral side has a structure such that the pre-mixing chamber formed in the interior of the wall opens in the downward direction in the manner of a funnel on at least one cone longitudinal segment symmetrically to an axis of symmetry defining the axial direction of the burner. The burner cone comprises, in at least one longitudinal segment of the cone longitudinal segment of the wall, which cone longitudinal segment opens in the manner of a funnel, a plurality of tangential inlet openings in order for exhaust air surrounding the burner cone to enter the pre-mixing chamber tangentially.

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 burner assembly for providing a flame and combustion gas to a plurality of inlets includes a burner frame having a channel formed therein. The channel extends parallel to a longitudinal plane defined by the plurality of inlets. A burner is mounted within the channel of the burner frame. The burner is arranged in fluid communication with the plurality of inlets. A burner bracket is used to mount the burner assembly within a burner box. The burner bracket defines a cavity within which the channel of the burner frame and the burner are positionable.

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 burner assembly for providing a flame and combustion gas to a plurality of inlets includes a burner frame having a channel formed therein. The channel extends parallel to a longitudinal plane defined by the plurality of inlets. A burner is mounted within the channel of the burner frame. The burner is arranged in fluid communication with the plurality of inlets. A burner bracket is used to mount the burner assembly within a burner box. The burner bracket defines a cavity within which the channel of the burner frame and the burner are positionable.