Abstract: A process for producing a crack-free and dense three-dimensional article of a gamma-prime precipitation-strengthened nickel-base superalloy, with more than 6 wt. % of [2 Al (wt. %)+Ti (wt. %)], which involves: (a) preparing a powder layer of a gamma-prime precipitation-strengthened nickel-based alloy material, with uniform thickness on a SLM apparatus substrate plate, or on a previously processed powder layer; (b) melting the prepared powder layer by scanning with a focused laser beam an article cross section area according to a three-dimensional sliced model with calculated cross sections, stored in the SLM control unit; (c) lowering the substrate plate by one layer thickness; and (d) repeating (a) to (c) until reaching a final cross section according to the three-dimensional sliced model, wherein, for (b), the laser power, focus diameter of the focal spot, and scan speed of the focused laser beam are adjusted to obtain heat dissipation welding.

Abstract: A gas turbine engine component has an axial seal pin assembly for sealing between adjacent platform regions where the seal pin assembly design provides a seal pin damper slot extending to a forward axial stop in a forward buttress region. The forward axial stop includes a relief slot to interrupt the loadpath from the airfoil into the blade neck and attachment regions to reduce the stress concentrations in these regions.

Abstract: The present invention relates to a system and method for joining adjacent sections of a compressor diaphragm. A splitline jumper is positioned within a recessed portion of a seal ring segment of the adjacent compressor diaphragms. The splitline jumper is sized and oriented so as to prevent axial movement of the compressor diaphragms relative to each other and also to prevent rotational movement of the seal ring relative to the diaphragm.

Abstract: A cooled wall segment in the hot gas path of a gas turbine. The wall segment includes a first surface, exposed to a medium of relatively high temperature, a second surface, exposed to a medium of relatively low temperature, and side surfaces connecting the first and second surface and defining a height of the wall segment. At least one cooling channel for a flow-through of a fluid cooling medium extends through the wall segment. Each cooling channel is provided with an inlet and an outlet for the cooling medium. The at least one cooling channel includes at least two heat transfer sections, a first heat transfer section extending essentially parallel to the first surface at a first distance from the first surface and a second heat transfer section extending essentially parallel to the first surface at a second distance, whereby the second distance is less than the first distance.

Abstract: A method for operating a combustion device includes supplying a fuel and an oxidizer into the combustion device and burning them. According to the method, during at least a part of a transient operation, an additional fluid is supplied together with the fuel, and its amount is regulated to counteract combustion pulsations.

Abstract: The disclosure pertains to a turbine with a gas turbine blade and a rotor heat shield for separating a space region through which hot working medium flows from a space region inside a rotor arrangement of the turbine. The rotor heat shield includes a platform which forms an axial heat shield section and which is arranged substantially parallel to the surface of a rotor and a radial heat shield section at the upstream end of the axial heat shield section, which is extending in a direction away from the surface of the axial heat shield section towards the hot gas. Further the turbine comprises a blade rear cavity which is delimited by the downstream end of the platform and/or the downstream end of the blade foot, the radial heat shield section. The disclosure further refers to a gas turbine blade and a rotor heat shield designed for such a turbine.

Abstract: The method for adjusting a natural gas temperature for a fuel supply line of a gas turbine engine includes measuring by infrared analysis the natural gas percentage content of methane (CH4), ethane (C2H6), propane (C3H8), butane (C4H10), carbon dioxide (CO2), calculating the nitrogen (N2) percentage content as the complement to 100 of the measured percentage content of methane (CH4), ethane (C2H6), propane (C3H8), butane (C4H10), carbon dioxide (CO2), calculating an index indicative of the natural gas energy content and adjusting the natural gas temperature on the basis of the index.

Abstract: A casing body for a hot gas flow includes an outer casing body having a hot gas side with a precisely prepared locating surface. A pin-type retainer is disposed on the locating surface, and an inner heat shield is disposed at a distance from the hot gas side of the outer casing body and fastened to the retainer.

Abstract: The axial compressor has a two-stage guide vane cascade at the discharge-side end of the rotor. The guide vanes of the second stage of the cascade are staggered in the circumferential direction in relation to the guide vanes of the first stage in such a way that vortex streamers created by the guide vanes of the first stage cannot impinge upon the guide vanes of the second stage.

Abstract: A method for tuning a combustor of a gas turbine engine based on one or more monitored operating conditions is provided. One or more operating conditions of the gas turbine engine are monitored. The monitored operating conditions may include, for example, a low frequency tone, a high frequency tone, and a ratio of the low frequency tone to the high frequency tone. It is determined whether the ratio of the low frequency tone to the high frequency tone is within a first predefined normal range. If the ratio of the low frequency tone to the high frequency tone is within the first predefined normal range, a determination is made not to tune the gas turbine engine. But, if the ratio of the low frequency tone to the high frequency tone is not within the first predefined normal range, a determination is made to tune the gas turbine engine.

Abstract: A method and apparatus for the operation of a gas turbine unit with an evaporative intake air cooling system in the intake air pathway, wherein the return water flow of the evaporative intake air cooling system is used for the cooling of components of the gas turbine unit and/or of a generator coupled to the gas turbine unit and/or of another element coupled to the gas turbine unit, and a gas turbine unit adapted to be operated using this method.

Abstract: The invention relates to a component for a thermal machine, in particular a gas turbine, which includes a corner and/or edge subjected to a thermally high load. The cooling of the component is improved in a manner such that at least one cooling channel is countersunk into the surface of the component in the immediate vicinity of the corner and/or edge in order to cool the corner and/or edge.

Abstract: The invention refers to a method for manufacturing a hybrid component including the following steps of manufacturing a preform as a first part of the hybrid component, then successively building up on that preform a second part of the component from a metallic powder material by means of an additive manufacturing process by scanning with an energy beam, thereby establishing a controlled grain orientation in primary and in secondary direction of at least a part of the second part of the component. The controlled secondary grain orientation is realized by applying a specific scanning pattern of the energy beam, which is aligned to the cross section profile of the component or to the local load conditions for the component.

Abstract: A configuration for joining a ceramic layer has a thermal insulating material to a metallic layer. The configuration includes an interface layer made of metallic material located between the ceramic layer and the metallic layer, which includes a plurality of interlocking elements on one of its sides, facing the ceramic layer, the ceramic layer comprising a plurality of cavities aimed at connecting with the corresponding interlocking elements of the interface layer. The configuration also includes a brazing layer by means of which the interface layer is joint to the metallic layer. The invention also refers to a method for obtaining such a configuration.

Abstract: Methods are provided for ensuring non-excessive variation of a gradient of an applied split bias versus firing temperature of a gas turbine engine. It is determined that an incremental split bias step is to be taken, and a current firing temperature of the gas turbine engine is identified on a graph. A first difference between a split schedule and an applied schedule gradient is calculated using lower firing temperatures than the current firing temperature, and a second difference is calculated using higher firing temperatures. If the first difference exceeds a predetermined limit, the incremental split bias step is not allowed at a lower firing temperature, and similarly, if the second difference exceeds a predetermined limit, the incremental split bias step is not allowed at a higher firing temperature.

Abstract: 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.

Abstract: The method for adjusting a natural gas temperature for a fuel supply line of a gas turbine engine includes measuring by infrared analysis the natural gas percentage content of methane (CH4), ethane (C2H6), propane (C3H8), butane (C4H10), carbon dioxide (CO2), calculating the nitrogen (N2) percentage content as the complement to 100 of the measured percentage content of methane (CH4), ethane (C2H6), propane (C3H8), butane (C4H10), carbon dioxide (CO2), calculating an index indicative of the natural gas energy content and adjusting the natural gas temperature on the basis of the index.

Abstract: A method is provided for operating a gas turbine plant including a compressor, which on an inlet side inducts intake air and compresses it, providing compressor exit air on a discharge side. The plant also includes a combustion chamber where fuel is combusted, using compressor exit air, forming a hot gas; and a turbine, where the hot gas is expanded, performing work. The method includes extracting compressed air from the compressor, directing it as cooling air flow into the combustion chamber and/or into the turbine for cooling thermally loaded components. The method also includes controlling at least one cooling air flow, for achieving specific operating targets, using a control element depending on an operating target. A gas turbine plant is also provided having at least one control element for cooling air flow control, and a gas turbine controller which controls the gas turbine plant based on selectable control parameter sets.

Abstract: The present invention discloses a novel apparatus and way for controlling a velocity of a fuel-air mixture entering a gas turbine combustion system. The apparatus comprises a hemispherical dome assembly which directs a fuel-air mixture along a portion of the outer wall of a combustion liner and turns the fuel-air mixture to enter the combustion liner in a manner coaxial to the combustor axis and radially outward of a pilot fuel nozzle so as to regulate the velocity of the fuel-air mixture.

Abstract: An impingement cooled wall arrangement includes: an impingement sleeve and a wall exposed to a hot gas during operation, wherein the impingement sleeve is at least partly disposed in a plenum, and spaced at a distance from the wall to form a cooling flow path between the wall and the impingement sleeve such that compressed gas injected from the plenum through apertures in the cooling sleeve during operation impinges on the wall and flows as a cross flow towards an exit at a downstream end of the cooling flow path. Plural turbulators have a leading edge arranged on the wall. A center of at least one of the apertures is aligned along the longitudinal axis with the leading edge of at least one of a turbulators.