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.

Abstract: The invention relates to a method for operating a gas turbine power plant, including a gas turbine, a HRSG following the gas turbine, an exhaust gas blower, and a carbon dioxide separation plant which separates the carbon dioxide contained in the exhaust gases and discharges it to a carbon dioxide outlet, the gas turbine, HRSG, exhaust gas blower, and carbon dioxide separation plant being connected by means of exhaust gas lines. According to the method a trip of the gas turbine power plant includes the steps of: stopping the fuel supply, switching off the exhaust gas blower, and controlling the opening angle of a VIGV at a position bigger or equal to a position required to keep a pressure in the exhaust gas lines between the HRSG and the exhaust gas blower above a minimum required pressure. The invention relates, further relates to a gas turbine power plant configured to carry out such a method.

Abstract: The present disclosure refers to a method for operating a gas turbine having a compressor, a combustor, a turbine downstream of the combustor, and a total number of turbine outlet temperature measurement sensors. The method can include supplying a first fuel flow to one of the burners of one combustor, which is smaller than a second fuel flow to another one of the burners the same combustor, selecting a number of turbine outlet temperature measurements which is smaller than a total number of the turbine outlet temperature measurement sensors, and averaging measured temperatures of the selected turbine outlet temperature measurements to obtain an trimmed turbine outlet temperature which is used for controlling operation of the gas turbine.

Abstract: A stator component of a turbomachine includes at least one axially extending outer ring which serves as a frame of an inner ring composed of partial segments. The partial segments are arranged on one another such that, on the rotor side, to form a coherent circular circumferential surface in relation to the rotational movement of rotor blades. The individual partial segment is composed of a material of uniform construction or, at least in a radial direction, of multiple partial bodies constructed from different materials, such as for example ceramic, wherein a partial segment thus formed exhibits predetermined stress and/or expansion behavior as a function of the load ranges of the turbomachine.

Abstract: A Helmholtz damper for a gas turbine is disclosed which includes a static resonator volume, which can be connected via a neck to an inner space of the gas turbine to damp pressure pulsations developing in the inner space. The static resonator volume can be changed in order to match resonances of the Helmholtz damper with the pressure pulsations. A simple and effective self-adjustment can be achieved via volume changing by at least one first element, which is exposed to a varying temperature within the gas turbine and undergoes a deformation, which depends on the varying temperature.

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 for post-weld heat treatment of a without a filler material welded high strength component made of a gamma prime (??) strengthened superalloy can include providing the welded component, heating the welded component by applying a rapid heating-up rate in the range of 20° C./min to 40° C./min during the entire temperature range from room temperature (RT) up to a temperature T1 of at least 1000° C., holding the welded component at T1 and then heating the component by applying a slow heating-up rate of about 5° C./min to a final temperature Tf, then holding the welded component at Tf for a time tf sufficient for at least partially dissolving the gamma prime phase in a weld of the welded component and also in a base material surrounding the weld, and cooling the component with a cooling rate that is greater than or equal to about 20° C./min.

Abstract: The invention relates to a method of post-built up heat treatment of an additively manufactured high strength component made of a gamma-prime strengthened superalloy based on Ni or Co or Fe or combinations thereof. An application of a rapid heating-up rate of 25 to 60° C./min in a specific temperature range during the first post-built heat treatment after additive manufacturing avoids or at least minimizes the gamma-prime precipitation in the component during heat-up. This results in crack-free components/articles compared to significant cracking present in conventionally heat treated components.

Abstract: A method for positioning a rotor of a gas turbine automatically is provided that includes gathering data with a control unit, and processing this data to bring the rotor to a desired position which is set according a Human Machine Interface (HMI). The indication of the lay of the rotor to the control unit is done by a key phasor, which includes a sensor which gets a digital pulse for each revolution of a phasor cam wheel. This digital pulse is used to give the information of the lay of the rotor to the control unit.

Abstract: The invention relates to a method for manufacturing a component, especially of a gas turbine, made of a single crystal (SX) or directionally solidified (DS) nickelbase superalloy, including a heat treatment and a machining and/or mechanical treatment step. The ductility of the component is improved by doing the machining and/or mechanical treatment step prior to said heat treatment and a solution heat treatment of the component is done prior to the machining/mechanical treatment step.

Abstract: Disclosed is an aerodynamically shaped body for use in a hot fluid flow. The body extends along a camber line from a leading edge to a trailing edge and includes at least one coolant supply plenum provided inside the body, wherein the coolant supply plenum is delimited by a body wall. The body wall extends from a first side of the camber line to a second side of the camber line and extends over the leading edge, thereby providing a leading edge wall section. At least one first leading edge cooling duct extends from an inner surface to an outer surface of the wall and is in fluid communication with the coolant supply plenum through an inlet opening and opens out onto the outer surface through a discharge opening.

Abstract: An intake arrangement for a compressor in a gas turbine power plant includes at least a passageway having an elongated portion, and a circular portion at an end of the elongated portion. The circular portion may be arranged in proximity to the compressor at around a compressor inlet. The passageway may be divided at least circumferentially and radially across the entire elongated portion and at least partially across the circular portion to configure a plurality of flue gas and air inlet segments for respectively conveying flue gas and air streams therethrough. The flue and air gas streams from each of the respective plurality of flue gas and air inlet segments, converge to be blended into a target mass stream for being conveyed into the compressor.

Abstract: A gas turbine is provided and includes a compressor, which via an air intake inducts and compresses air; a combustion chamber, in which a fuel is combusted using the compressed air, producing a hot gas; and a turbine, equipped with turbine blades, in which the hot gas is expanded, performing work. A first device is provided in order to cool turbine blades with compressed cooling air. The first device includes at least one separate compressor stage which produces compressed cooling air independently of the compressor.

Abstract: A labyrinth seal is provided for sealing the annular interspace between the rotor and the stator of a steam turbine or gas turbine. The labyrinth seal includes a multiplicity of sealing strips which are arranged in series in the axial direction and fastened on the stator and project into the interspace. The sealing strips interact, with sealing effect, with rotor-side sealing elements which are arranged in a staggered manner. An improved sealing effect is achieved by the sealing strips in the cold installed state being offset in relation to a symmetrical position, wherein the offset has the reverse direction and the same amount as the distance by which the sealing strip is displaced relative to adjacent rotor-side sealing elements as a result of thermal expansions of the stationary and rotating components and support structure when being heated from the cold installed state to a hot steady-state operating condition.

Abstract: Methods are disclosed for treating a base materials in a form of metallic powder made of super alloys based on Ni, Co, Fe or combinations thereof, or made of TiAl alloys, which treated powder can be used for additive manufacturing, such as for Selective Laser Melting of three-dimensional articles.

Abstract: A turboengine component is disclosed, having at least one first, receiving, member and at least one second, received, member, the receiving member having at least one receiver opening, the received member including a body and at least one fixation post extending from the body. A retainer cavity is provided with a first retainer groove at an inner surface of the receiver opening. A second retainer groove is provided on a surface of the fixation post. A retainer member has a cross section and a longitudinal extent aligned with the lengthwise extent of the retainer cavity, the retainer member being displaceable within the retainer cavity along the lengthwise extent. The retainer member may be removed and the turboengine component may be disassembled without the damaging any of the received member and the receiving member.

Abstract: A turboengine blading member includes at least one airfoil and at least one platform provided at least one of a base and a tip of the airfoil. The airfoil has a profile body, a leading edge provided at a first side of the profile body, and a trailing edge section extending from a second side of the profile body and opposite the leading edge. The profile body is connected to the at least one platform. The trailing edge section cantilevers from the profile body and is provided without connection to the platform.

Abstract: The present disclosure refers to a method for operating a gas turbine with a sequential combustor arrangement having: a first burner, a first combustion chamber, and a second combustor. A fuel gas is separated into a rich fuel having a concentration of higher hydrocarbons which is higher than the concentration of higher hydrocarbons of the fuel gas supplied to the plant, and a lean fuel having a concentration of higher hydrocarbons which is lower than the concentration of higher hydrocarbons of the fuel gas. A first fuel and a second fuel mixed from at least one of the rich fuel, the lean fuel, and the fuel gas are fed to different combustors of the gas turbine.

Abstract: Disclosed is a turbo-engine component comprising a wall, the wall comprising a hot gas side surface and a coolant side surface. At least one coolant discharge duct is provided in said wall and opening out onto the hot gas side surface at a coolant discharge opening. A coolant flow direction is defined from the interior of the coolant discharge duct towards the discharge opening, the coolant discharge duct further being delimited by a delimiting surface thereof provided inside the wall. The coolant discharge duct has a first cross sectional direction and a second cross sectional direction. The coolant discharge duct is a blind cavity and is closed towards the coolant side surface, and further a dimension of the coolant discharge duct measured in the first cross sectional direction decreases in the coolant flow direction.

Abstract: Disclosed is a turbo-engine component and a method for cooling a turbo-engine component. The method includes guiding a working fluid flow along a hot gas side surface of a wall of the component and in a main working fluid flow direction, discharging a coolant discharge flow at the hot gas side surface from a coolant discharge duct provided in the wall, and supplying a coolant supply flow to the coolant discharge duct and through a coolant supply path. The method also includes discharging the coolant supply flow into the coolant discharge duct as a free jet oriented across a cross section of the coolant discharge duct, and directing the free jet onto an inner surface section of the coolant discharge duct, thus effecting impingement cooling of the inner surface section.