Abstract: The invention refers to a method and a device for flame stabilization in a burner system of a stationary combustion engine, preferably a stationary gas turbine, in which a flow of an air/fuel mixture is produced and being swirled to form a vortex flow to which a swirl number is assignable before entering a combustion zone in which the vortex flow of the air/fuel mixture is ignited to form a flame within a reverse flow zone caused by vortex breakdown. The swirl number perturbation driven by thermoacoustic oscillation inside the burner system is controlled by affecting the vortex flow actively before entering the combustion zone on basis of changing a flame transfer function assigned to the burner system with the proviso of minimizing pulsation amplitudes of the flame transfer function.

Abstract: A fuel nozzle for a turbomachine includes a centerbody that extends axially with respect to a centerline of the fuel nozzle. A confining tube is positioned radially outward of the centerbody. A plurality of swirler vanes is disposed between the centerbody and the confining tube. Each of the plurality of swirler vanes includes a radially inner base and a radially outer tip. Each of the swirler vanes further includes an upstream portion that extends generally axially from a leading edge. A downstream portion extends from the upstream portion to a trailing edge. The downstream portion defines a bend length between the upstream portion and the trailing edge. The bend length at the radially outer tip is greater than the bend length at the radially inner base.

Abstract: A rotary machine includes at least one burner including a front panel having a front side and an opposing back side. The acoustic damper includes at least one wall, at least one cooling air inlet, at least one outlet, and at least one baffle. The wall extends from the back side of the front panel and defines a dampening chamber. The cooling air inlet is defined within the back side of the front panel and is configured to channel a flow of cooling air into the dampening chamber. The outlet is defined within the back side of the front panel and is configured to channel the flow of cooling air out of the dampening chamber. The baffle extends from the back side of the front panel and is configured to reduce a velocity of the flow of cooling air within the dampening chamber.

Abstract: An acoustic damper for a rotary machine includes at least one wall, at least one cooling air inlet, at least one outlet, and at least one cap. The at least one wall extends from a back side of a burner front panel such that the at least one wall partially defines a dampening chamber. The at least one cooling air inlet is defined within the back side of the front panel and is configured to channel a flow of cooling air into the dampening chamber. The at least one outlet is defined within the back side of the front panel and is configured to channel the flow of cooling air out of the dampening chamber. The at least one cap is positioned at least partially over the at least one cooling air inlet and is configured to reduce a velocity of the flow of cooling air within the dampening chamber.

Abstract: A fuel nozzle for a turbomachine includes a centerbody that extends axially with respect to a centerline of the fuel nozzle. A confining tube is positioned radially outward of the centerbody. A plurality of swirler vanes is disposed between the centerbody and the confining tube. Each of the plurality of swirler vanes includes a radially inner base and a radially outer tip. Each of the swirler vanes further includes an upstream portion that extends generally axially from a leading edge. A downstream portion extends from the upstream portion to a trailing edge. The downstream portion defines a bend length between the upstream portion and the trailing edge. The bend length at the radially outer tip is greater than the bend length at the radially inner base.

Abstract: A combustor for a turbomachine includes a rich combustion zone and a low temperature zone downstream of the rich combustion zone. A heat exchanger is positioned downstream of the rich combustion zone and upstream of the low temperature zone. The heat exchanger includes a plurality of air passages, a plurality of air inlets in fluid communication with the plurality of air passages, and a plurality of combustion gas passages. Each of the combustion gas passages extends between a combustion gas inlet in fluid communication with the rich combustion zone and a combustion gas outlet in fluid communication with the low temperature zone. The plurality of combustion gas passages are in thermal communication with the plurality of air passages.

Abstract: A rotary machine includes at least one burner including a front panel having a front side and an opposing back side. The acoustic damper includes at least one wall, at least one cooling air inlet, at least one outlet, and at least one baffle. The wall extends from the back side of the front panel and defines a dampening chamber. The cooling air inlet is defined within the back side of the front panel and is configured to channel a flow of cooling air into the dampening chamber. The outlet is defined within the back side of the front panel and is configured to channel the flow of cooling air out of the dampening chamber. The baffle extends from the back side of the front panel and is configured to reduce a velocity of the flow of cooling air within the dampening chamber.

Abstract: An acoustic damper for a rotary machine includes at least one wall, at least one cooling air inlet, at least one outlet, and at least one cap. The at least one wall extends from a back side of a burner front panel such that the at least one wall partially defines a dampening chamber. The at least one cooling air inlet is defined within the back side of the front panel and is configured to channel a flow of cooling air into the dampening chamber. The at least one outlet is defined within the back side of the front panel and is configured to channel the flow of cooling air out of the dampening chamber. The at least one cap is positioned at least partially over the at least one cooling air inlet and is configured to reduce a velocity of the flow of cooling air within the dampening chamber.

Abstract: 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.

Abstract: A method and apparatus are disclosed for mixing H2-rich fuels with air in a gas turbine combustion system, wherein a first stream of burner air and a second stream of a H2-rich fuel are provided. All of the fuel is premixed with a portion of the burner air to produce a pre-premixed fuel/air mixture. This pre-premixed fuel/air mixture is injected into the main burner air stream.

Abstract: A combustor for a turbomachine includes a rich combustion zone and a low temperature zone downstream of the rich combustion zone. A heat exchanger is positioned downstream of the rich combustion zone and upstream of the low temperature zone. The heat exchanger includes a plurality of air passages, a plurality of air inlets in fluid communication with the plurality of air passages, and a plurality of combustion gas passages. Each of the combustion gas passages extends between a combustion gas inlet in fluid communication with the rich combustion zone and a combustion gas outlet in fluid communication with the low temperature zone. The plurality of combustion gas passages are in thermal communication with the plurality of air passages.

Abstract: The present invention relates to an axial swirler, in particular for premixing of oxidizer and fuel in gas turbines. The axial swirler for a gas turbine burner includes a plurality of swirl vanes with a streamline cross-section being arranged around a swirler axis and extending in radial direction between an inner radius Rmin and an outer radius Rmax. Each swirl vane has a leading edge, a trailing edge, and a suction side and a pressure side extending each between the leading and trailing edges. A discharge flow angle ? between a tangent to the swirl vane camber line at its trailing edge and the swirler axis is first function of radial distance R from the swirler axis. A position of maximum camber of the swirl vane is second function of radial distance R from the swirler axis. At least one swirl vane of the first and second functions include each a respective local maximum and local minimum values along said radial distance from Rmin to Rmax. The invention also relates to a burner with such a swirler.

Abstract: A method for premixing air with a gaseous fuel for being burned in a combustion chamber includes: guiding the air in an air stream along a burner axis through a coaxial air tube into a combustion chamber arranged at an end of said air tube; and impressing a swirl on the air stream by passing it through a first swirl device concentrically arranged within the air tube and comprising a plurality of radially oriented first blades. The method further includes: injecting gaseous fuel into the air stream at the first swirl device; and mixing said air in said air stream with the injected gaseous fuel in a first mixing zone arranged just after said first swirl device.

Abstract: 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.

Abstract: An axial swirler, in particular for premixing of oxidizer and fuel in gas turbines, includes a series of swirl vanes with a streamline cross-section. Each swirl vane has a leading edge, a trailing edge, and a suction side and a pressure side extending each between the leading and trailing edges. The swirl vanes are arranged around a swirler axis, wherein the leading edges extend essentially in radial direction. Flow slots are formed between the suction side of each swirl vane and the pressure side of its nearest neighboring swirl vane. Furthermore, at least one swirl vane has a discharge flow angle between a tangent to its camber line at its trailing edge and the swirler axis that is monotonically increasing with increasing radial distance from the swirler axis. The invention also relates to a burner with such a swirler and a method of operating the burner.

Abstract: An axial swirler for a gas turbine burner includes a vane ring with a plurality of swirler vanes circumferentially distributed around a swirler axis. Each of the swirler vanes includes a trailing edge. In order to achieve a controlled distribution of the exit flow velocity profile and/or the fuel equivalence ratio in the radial direction. The trailing edge is discontinuous with the trailing edge having a discontinuity at a predetermined radius.

Abstract: The invention refers to a method and a device for flame stabilization in a burner system of a stationary combustion engine, preferably a stationary gas turbine, in which a flow of an air/fuel mixture is produced and being swirled to form a vortex flow to which a swirl number is assignable before entering a combustion zone in which the vortex flow of the air/fuel mixture is ignited to form a flame within a reverse flow zone caused by vortex breakdown. The swirl number perturbation driven by thermoacoustic oscillation inside the burner system is controlled by affecting the vortex flow actively before entering the combustion zone on basis of changing a flame transfer function assigned to the burner system with the proviso of minimizing pulsation amplitudes of the flame transfer function.

Abstract: A swirler including an annular housing with limiting walls. At least two vanes are arranged in the annular housing including the sidewalls of the swirler. The leading edge area of each vane has a profile, which is oriented parallel to a main flow direction prevailing at the leading edge position, wherein the profiles of the vanes turn from the main flow direction prevailing at the leading edge position to impose a swirl on the flow, and wherein, with reference to a central plane of the vanes the trailing edges are provided with at least two lobes in opposite transverse directions. A burner for a combustion chamber of a gas turbine including such a swirler and at least one nozzle having its outlet orifice at or in a trailing edge of the vane and to a method of operation of such a burner.

Abstract: The present invention relates to an axial swirler, in particular for premixing of oxidizer and fuel in gas turbines. The axial swirler for a gas turbine burner includes a plurality of swirl vanes with a streamline cross-section being arranged around a swirler axis and extending in radial direction between an inner radius Rmin and an outer radius Rmax. Each swirl vane has a leading edge, a trailing edge, and a suction side and a pressure side extending each between the leading and trailing edges. A discharge flow angle a between a tangent to the swirl vane camber line at its trailing edge and the swirler axis is first function of radial distance R from the swirler axis. A position of maximum camber of the swirl vane is second function of radial distance R from the swirler axis. At least one swirl vane of the first and second functions include each a respective local maximum and local minimum values along said radial distance from Rmin to Rmax. The invention also relates to a burner with such a swirler.

Abstract: A method for premixing air with a gaseous fuel for being burned in a combustion chamber includes: guiding the air in an air stream along a burner axis through a coaxial air tube into a combustion chamber arranged at an end of said air tube; and impressing a swirl on the air stream by passing it through a first swirl device concentrically arranged within the air tube and comprising a plurality of radially oriented first blades.