Abstract: A method for manufacturing a contoured hole, the hole being manufactured in a wall, the wall comprising a first, a second surface, and a wall thickness between the wall first and second surface. The comprises manufacturing a first non-penetrating hole extending from the first surface and into the wall, wherein a distal end of the first hole is located within the wall such that the first hole does not penetrate the wall second surface, and manufacturing a through hole, wherein the through hole is fluidly connected with first hole and penetrates the wall second surface.

Abstract: A method for barring a rotor of a thermally loaded turbomachine includes stopping normal operation of the turbomachine; providing a barring device for rotating the rotor about a machine axis; coupling the barring device to the rotor; letting the rotor cool down during cool down of the rotor rotating the rotor by means of the barring device. A damage of the machine due to thermally induced buckling during the barring process is avoided by consecutively determining the force or torque applied to the rotor by the barring device for rotating the rotor and/or the circumferential speed of the rotor during barring. The rotation of the rotor is controlled by means of the barring device in dependence of the determined force or torque and/or circumferential speed in order to reduce a bending or imbalance of the rotor, which is due to a nonuniform temperature distribution on the rotor during cool down.

Abstract: The invention relating to a A damper for combustion oscillation damping for a gas turbine, includes a resonator cavity with a box or cylinder shape, a neck in flow communication with the resonator cavity and a combustion chamber. The length Lneck of the neck is equal or greater than a maximum distance lmax that a hot gas ingested from the combustion chamber reaches in the neck. The maximum distance lmax is determined according to the following equation: l max = ? t 1 t 2 ? U - p ^ ? ? ? U ? ? ? ? sin ? ( ? ? ? t ) ? ? d ? ? t . With the solution of the present invention, the damper used to damping combustion oscillation may prevent hot gas ingestion during normal operations by uniquely determining the dimensions of the neck connecting the resonator cavity and the combustion chamber.

Abstract: In a method for operating a gas turbine, NOx is removed from the exhaust gases of the gas turbine by means of a selective catalysis device with the addition of NH3. The method achieves an extremely low NOx content while simultaneously achieving economic consumption of NH3 and avoiding NH3 in the exhaust gas by maintaining the NOx content of the exhaust gas at a constant level via a regulated return of a portion of the exhaust gas in varying operating conditions of the gas turbine, and by adjusting the addition of the NH3 in the selective catalysis device to the constant NOx level.

Abstract: The invention relates to a damper for reducing pulsations in a gas turbine, which includes an enclosure, a main neck extending from the enclosure, a spacer plate disposed in the enclosure to separate the enclosure into a first cavity and a second cavity and an inner neck with a first end and a second end, extending through the spacer plate to interconnect the first cavity and the second cavity. The first end of the inner neck remains in the first cavity and the second end remains in the second cavity. A flow deflecting member is disposed proximate the second end of the inner neck to deflect a flow passing through the inner neck. With the solution of the present invention, as a damper according to embodiments of the present invention operates, flow field hence damping characteristic in the second cavity constant regardless the adjustment of the spacer plate in the enclosure.

Abstract: The invention pertains to a power plant including a gas turbine, a heat recovery boiler arrangement with at least a boiler inlet, and an outlet side with a first exit connected to a stack and a second exit connected to a flue gas recirculation, which connects the second exit to the compressor inlet of the gas turbine. The heat recovery boiler arrangement includes a first boiler flue gas path from the boiler inlet to the first boiler exit, and a separate second boiler flue gas path from the boiler inlet to the second boiler exit. Additionally, a supplementary firing and a subsequent catalytic NOx converter are arranged in the first boiler flue gas path. Besides the power plant a method to operate such a power plant is an object of the invention.

Abstract: The present invention relates to a method of decelerating a turbine rotor of a turbine engine. At least one electric motor is engaged with the turbine rotor. A braking system, preferably the starting system, is engaged with the at least one electric motor, preferably the generator of the turbine engine, so as to use the at least one electric motor to apply a negative (braking) torque on the turbine rotor. The method includes after flame off, the braking system being used for dissipating kinetic energy available in the turbine engine after flame off by means of the at least one electric motor.

Abstract: The invention relates to a method for operating a gas turbine system, wherein the gas turbine system includes a compressor, a combustor, a heat recovery steam generator, a scrubber, a direct contact cooler. The method includes introducing the scrubbing fluid discharged from the scrubber into the direct contact cooler, contacting the scrubbing fluid in the direct contact cooler with the exhaust gas discharged from the heat recovery steam generator in order to remove a portion of nitrogen oxide therefrom; feeding the exhaust gas discharged from the direct contact cooler into the compressor. With the technical solution of the present invention, nitrogen oxide in the exhaust gas is reduced to a certain extent by means of used scrubbing fluid from the scrubber. This solution may improve the efficiency in reduction of nitrogen oxide with a simple and feasible manner.

Abstract: The invention relates to an ultrasonic NDT sensor arrangement for inspecting surfaces of variable geometry of metal bodies. The sensor arrangement includes a housing with a hollow inner space and an opening, through which part of an incoming sound beam exits the housing to enter a metal body to be tested. An ultrasonic sensor is coupled to the housing such that it emits said incoming sound beam directly into said hollow inner space in a direction towards the opening. The said inner space of the housing is filled with a first coupling fluid which is water. The opening of the housing is closed with a closing member, which is made of a silicone material and which has a similar density and velocity of sound compared to the first coupling fluid.

Abstract: A gas turbine combustor part of a gas turbine includes a wall, containing a plurality of near wall cooling channels extending essentially parallel to each other in a first direction within the wall in close vicinity to the hot side and being arranged in at least one row extending in a second direction. The near wall cooling channels are each provided at one end with an inlet for the supply of cooling air, and on the other end with an outlet for the discharge of cooling air. The inlets open into a common feeding channel for cooling air supply, and the outlets open into a common discharge channel for cooling air discharge. The feeding channel and the discharge channel extend in the second direction.

Abstract: A vane carrier is provided for a compressor or a turbine section of an axial turbo machine, especially one of a gas turbine, steam turbine, compressor, expander, comprises least a first and second functional means. The first functional means is a cylinder made of a material with a coefficient of thermal expansion (CTE) below 1.3×10?5 [1/K]. The cylinder is provided for carrying a plurality of vanes on its inner side. The second functional means is a support structure made of a material different to and less expensive than the material of said first functional means. The support structure is provided for defining an axial and lateral position of the first functional means within an outer casing of the axial turbo machine.

Abstract: A combustor wall element includes a wall having a front surface and a back surface. The front surface is provided on a front side of the wall and the back surface is provided on a back side of the wall. A through opening penetrates the wall from the front surface to the back surface. A duct is provided extending from the back surface and to a back end of the combustor wall element, and the duct is in fluid communication with the through opening. At least one cooling channel is provided inside the wall, wherein the cooling channel extends between a first open end and a second open end. At least a section of the cooling channel extends at least essentially parallel to the front surface.

Abstract: A method for manufacturing a mechanical component by additive manufacturing which includes at least one layering sequence of depositing a powder material and locally melting and resolidifying the powder material. In each layering sequence, a solid layer of solidified material is formed, wherein the solid layers jointly form a solid body. An annealing sequence subsequent to at least one layering sequence includes, locally heating at least a region of the solid body in effecting a local heat input to the immediately beforehand manufactured solid layer which was formed by the immediately precedent layering sequence, with temperature being is maintained below a melting temperature of the material.

Abstract: A composite turbine blade for high-temperature applications such as gas turbines or the like includes a root for mounting the blade in a corresponding circumferential assembly groove of a rotor and an airfoil connected to said root. An inner carrying structure is provided extending at least over a portion of the root as well as at least a portion of said airfoil. The inner carrying structure is made of a high strength eutectic ceramic and the airfoil is made of a ceramic matrix composite (CMC) material.

Abstract: A turbine vane for a rotary turbomachine has a turbine blade delimited by a concave pressure-side wall and a convex suction-side wall which are connected in the region of a vane front edge which can be assigned to the turbine blade and enclose a cavity which extends in the longitudinal extent of the vane front edge and is delimited on the inner wall by the pressure-side wall and the suction-side wall in the region of the vane front edge and by an intermediate wall which extends in the longitudinal direction to the vane front edge and connects the suction-side wall and the pressure-side wall on the inner wall. The intermediate wall has a perforation at least in sections in the connecting region to the suction-side wall and/or pressure-side wall, in order to increase the elasticity of the intermediate wall.

Abstract: The invention relates to a method for detecting a fuel leakage in the fuel distribution system between a fuel control valve and at least one burner of a gas turbine during the operation of the gas turbine. In order to detect a fuel leakage, the fuel consumption is approximated in accordance with the mechanical power of the gas turbine, the fuel amount fed to the fuel distribution system is determined, and the leakage flow is determined from the difference between the fed fuel amount and the fuel consumption. The invention further relates to a gas turbine for performing such a method.

Abstract: A method for reconditioning a hot gas path part of a gas turbine to flexibly adapt an operation regime of said gas turbine for subsequent operation intervals. The method includes providing a hot gas path part to be reconditioned; removing a predetermined area of the hot gas path part, resulting in a cutout at the hot gas path part; and manufacturing a coupon for insertion into the cutout to replace the removed area of the hot gas path part. The method further includes inserting the coupon into the cutout; and joining the hot gas path part with the coupon. The coupon is manufactured by a selective laser melting method resulting in a fine grain sized material with significantly improved low cycle fatigue lifetime. The hot gas path part is coated, at least in an area including the inserted coupon, with a metallic overlay with improved thermo-mechanical fatigue and oxidation lifetime.

Abstract: Methods and systems are provided for automatically tuning a combustor of a gas turbine engine during a transient period, such as when a state of the gas turbine engine is changing. Once it has been determined whether the state of the gas turbine engine is changing, it is then determined whether a lean blowout is imminent, which is based conditions being monitored. A stability bias is applied to the system if either the state is changing or if lean blowout is imminent until the lean blowout is no longer determined to be imminent. The stability bias monitors operating conditions of the gas turbine engine and determines when one of the operating conditions has overcome a threshold value. Once a threshold value is overcome, a fuel flow fraction is adjusted by a predefined increment. The application of the stability bias is gradually terminated once it is determined that the lean blowout is no longer imminent.

Abstract: A combustor front assembly for a gas turbine power plant, wherein the combustor front assembly is provided with at least a through hole for allowing gas flow into a combustion chamber, the combustor front assembly having a combustor front plate with at least a through hole and with an outer surface outside the combustor chamber; a combustor front segment having a through hole and coupled with the outer surface of the combustor front plate so that the through hole of the front segment is aligned with the through hole of the front plate; wherein the combustor front segment is clamped in position and forced against the outer surface of the combustor front plate.

Abstract: A method for operating a gas turbine (11) having a compressor (12), a turbine (14) and a combustor (13) with a pilot burner group (15a), a rich premix burner group (15b) and a lean premix burner group (15c), under changing composition of the incoming fuel gas (16), includes the steps of: continuously measuring, in real time, the composition of the fuel gas (16); and controlling the operation of the gas turbine (11) and the combustion of the burners (15a-c) by using the real time fuel gas composition measurements.