Abstract: A method for monitoring the operation of a gas turbine is provided, in which component vibrations are detected during the operation of the gas turbine by an acceleration sensor arranged on the component, a plurality of signal sections being determined by a plurality of frequency bands fb from the signal forwarded and processed by the acceleration sensor. To avoid an unnecessary shutdown of the gas turbine to perform an inspection which subsequently proves unnecessary, thereby increasing the availability of the gas turbine, a total vibration period is determined by adding together the vibration periods of signal sections during which the amplitudes of the signal sections concerned are greater than a frequency band-specific threshold.

Abstract: An adaptation method for a modelling method in which, by means of target geometry, model geometry, which is derived from the target geometry, is created for an object to be produced by a selective laser melting method is provided. In the adaptation method, adapted model geometry is produced from the derived model geometry by dimension adaptation by means of a correction factor and/or by geometry adaptation by means of correction geometry.

Abstract: A fuel nozzle (2) for two fuels, with an inner pipe (5) with radially oriented outlet openings (7) for a first fuel and with an outer pipe (6), surrounding the inner pipe (5), with axially oriented outlet openings (10) for a second fuel; an axially extending groove (18) on an outer surface of the inner pipe (5) and a projection (19) inward from the outer pipe which engages in the groove (18) as an anti-torsion device (17) and which is arranged between two axial outlet openings (10). Alternative groove and projection configurations are disclosed.

Abstract: An adaptation method for a modelling method in which, by means of target geometry, model geometry, which is derived from the target geometry, is created for an object to be produced by a selective laser melting method is provided. In the adaptation method, adapted model geometry is produced from the derived model geometry by dimension adaptation by means of a correction factor and/or by geometry adaptation by means of correction geometry.

Abstract: A damping device for a gas turbine has at least one Helmholtz resonator and at least one duct, wherein the Helmholtz resonator has a resonator housing and at least one resonator neck pipe and the resonator housing encloses a resonance volume of the Helmholtz resonator, into which volume acoustic vibrations can be injected by means of the resonator neck pipe. The damping device enables a particularly effective damping of thermo-acoustic vibrations. For this purpose, the duct is formed with a duct jacket and at least one outlet opening. Acoustic vibrations of a fluid stream flowing through a burner plenum and a combustion chamber can be injected into the outlet opening. A cooling fluid can be applied to the duct and the at least one resonator neck pipe opens on the hot-gas side into such a duct upstream of the at least one outlet opening.

Abstract: The present invention relates to a burner system (1) comprising a pilot burner arrangement (2), a main burner arrangement (3) surrounding the pilot burner arrangement (2), a combustion chamber arranged downstream with respect to the pilot burner arrangement (2) and the main burner arrangement (3), and at least one resonator (17), wherein the main burner arrangement (3) defines a ring-shaped air supply (13) outwardly delimited by a burner cone (14) and provided with radially extending swirl vanes (15), wherein a resonator cavity (18) of the at least one resonator (17) is formed at the outside of the burner cone (14), wherein the resonator cavity (18) is provided with a plurality of resonator openings (20) defining a fluidic connection between the resonator cavity (18) and the combustion chamber.

Abstract: A method for monitoring the operation of a gas turbine is provided, in which component vibrations are detected during the operation of the gas turbine by an acceleration sensor arranged on the component, a plurality of signal sections being determined by a plurality of frequency bands fb from the signal forwarded and processed by the acceleration sensor. To avoid an unnecessary shutdown of the gas turbine to perform an inspection which subsequently proves unnecessary, thereby increasing the availability of the gas turbine, a total vibration period is determined by adding together the vibration periods of signal sections during which the amplitudes of the signal sections concerned are greater than a frequency band-specific threshold.

Abstract: A fuel nozzle including a nozzle tube and a nozzle outlet opening is provided. The nozzle tube is connected to a fuel feed line for feeding a fuel to the nozzle tube, wherein the fuel is fed from the nozzle outlet opening to an annular air stream surrounding the fuel nozzle, wherein a first nozzle tube section that extends up to the nozzle outlet opening is designed in a floral pattern in such a way that the fuel may be fed substantially coaxially into the air stream.

Abstract: A fuel nozzle (2) for two fuels, with an inner pipe (5) with radially oriented outlet openings (7) for a first fuel and with an outer pipe (6), surrounding the inner pipe (5), with axially oriented outlet openings (10) for a second fuel; an axially extending groove (18) on an outer surface of the inner pipe (5) and a projection (19) inward from the outer pipe which engages in the groove (18) as an anti-torsion device (17) and which is arranged between two axial outlet openings (10). Alternative groove and projection configurations are disclosed.

Abstract: A gas turbo set including a first turbine, a second turbine, and a combustion chamber connected between the first and second turbines and operated by auto-ignition is provided. The turbines and the combustion chamber are located on a common shaft that may be rotated about an axis. To increase the efficiency of the gas turbo set, the outer periphery of the second turbine is at a greater distance from the axis than that of the first turbine, leading to a reduction in the size and/or the number of turbine blades.

Abstract: A gas turbine combustion chamber includes a fuel nozzle with a cylindrical nozzle tube, in which a fluid flows, and a convexly formed nozzle cover, which is arranged downstream of the nozzle tube. The nozzle cover has a central point and a plurality of through-openings through which the fluid leaves the nozzle tube. The through-openings are arranged at different radial distances from the central point at two circular lines.

Abstract: A burner for a gas combustor and a method of operating the burner are disclosed. The burner includes a front surface area divided into a plurality of subareas and inlets arranged on the front surface area such that each subarea is encircled by at least four inlets and such that during operation of the burner, a gas recirculation in the combustor is facilitated corresponding to each subarea.

Abstract: Disclosed is a gas turbine fuel injector and swirler assembly, including: a delivery tube structure arranged on a central axis of the fuel injector and swirler assembly, a first fuel supply channel arranged in the delivery tube structure, a shroud surrounding the delivery tube structure, swirl vanes arranged between the delivery tube structure and the shroud, a radial passage in each swirl vane, communicating with the first fuel supply channel, a set of apertures open between the radial passage and the exterior surface of said each swirl vane, wherein a second fuel supply channel is arranged in the delivery tube structure extending to a downstream end of the delivery tube structure and a mixer with lobes for fuel injection is arranged at the downstream end. Further disclosed is an assembly method for assembling a fuel injector and swirler assembly.

Abstract: Disclosed is a gas turbine fuel injector and swirler assembly, including: a delivery tube structure arranged on a central axis of the fuel injector and swirler assembly, a first fuel supply channel arranged in the delivery tube structure, a shroud surrounding the delivery tube structure, swirl vanes arranged between the delivery tube structure and the shroud, a radial passage in each swirl vane, communicating with the first fuel supply channel, a set of apertures open between the radial passage and the exterior surface of said each swirl vane, wherein a second fuel supply channel is arranged in the delivery tube structure extending to a downstream end of the delivery tube structure and a mixer with lobes for fuel injection is arranged at the downstream end. Further disclosed is an assembly method for assembling a fuel injector and swirler assembly.

Abstract: A method of operating a multi-fuel combustion system is provided. The method includes a first phase and a second phase, wherein the first phase includes providing ignition to a combustor basket to ignite a first type of fuel, where the first type of fuel is supplied to the combustor basket through a first conduit. Also in first phase steam is also supplied to the first conduit in addition to the first type of fuel and steam is supplied to the second conduit after the ignition. In the second phase a second type of fuel is supplied to the combustor basket through the second conduit after ignition of the first fuel through the first conduit, while stopping the supply of the first fuel, and continuing to supply steam through both the first and second conduits.

Abstract: A multi-fuel combustion system is provided. The system includes a combustor basket adapted to combust at least two type of fuels. The combustor basket includes a circumferential wall with a plurality of openings. The combustion system further includes a first conduit adapted to provide a first type of fuel directly to the combustor basket and a second conduit adapted to provide a second type of fuel directly to the combustor basket. The combustion system also may include a third conduit adapted to inject at least one of the first type of fuel and the second type of fuel through the openings into the combustor basket.

Abstract: A method of operating a multi-fuel combustion system is provided. The method includes a first phase and a second phase, wherein the first phase includes providing ignition to a combustor basket to ignite a first type of fuel, where the first type of fuel is supplied to the combustor basket through a first conduit. Also in first phase steam is also supplied to the first conduit in addition to the first type of fuel and steam is supplied to the second conduit after the ignition. In the second phase a second type of fuel is supplied to the combustor basket after ignition of the first fuel through the second conduit, while stopping the supply of the first fuel.

Abstract: A burner for a gas combustor and a method of operating the burner are disclosed. The burner includes a front surface area divided into a plurality of subareas and inlets arranged on the front surface area such that each subarea is encircled by at least four inlets and such that during operation of the burner, a gas recirculation in the combustor is facilitated corresponding to each subarea.

Abstract: A fuel nozzle including a nozzle tube and a nozzle outlet opening is provided. The nozzle tube is connected to a fuel feed line for feeding a fuel to the nozzle tube, wherein the fuel is fed from the nozzle outlet opening to an annular air stream surrounding the fuel nozzle, wherein a first nozzle tube section that extends up to the nozzle outlet opening is designed in a floral pattern in such a way that the fuel may be fed substantially coaxially into the air stream.

Abstract: The present invention explains a multi-fuel combustion system. It consist of a combustor basket adapted to combust at least two type of fuels. The combustor basket has got a circumferential wall comprising a plurality of openings. The combustion system further has a first conduit adapted to provide a first type of fuel directly to the combustor basket, a second conduit adapted to provide a second type of fuel directly to the combustor basket and a third conduit adapted to inject at least one of the first type of fuel and the second type of fuel through the openings into the combustor basket.