Abstract: A method for manufacturing a stage of a steam turbine comprising the steps of milling a block of material to define a sector having a plurality of blades, each blade having an external surface; machining an opening in the external surface of at least one of the blades; machining a cavity in fluid communication with the opening; the step of machining the cavity being performed by wire electric discharge machining.

Abstract: A combustor for a gas turbine is described. The combustor comprises a combustor liner, a metering plate attached to an end of the combustor liner and a combustor casing at least partially surrounding the combustor liner. An end cover is further connected to the combustor casing. The combustor liner is connected to the combustor casing by means of a retainer arranged between the metering plate and the end cover, and attached to the metering plate and to the end cover.

Abstract: An automatic ring valve 10 comprising a valve seat 12 provided with a plurality of gas flow passages 14 arranged according to at least one annular row, at least a shutter 18 comprising at least one ring-shaped portion for selectively closing and opening the gas flow passages 14, wherein said ring-shaped portion of the shutter 18 comprises a fiber-reinforced matrix 40, at least one contrasting member for contrasting an opening movement of ring-shaped portion of the shutter 18, wherein said ring-shaped portion of the shutter 18 comprises a structural core 18A made by said fiber-reinforced matrix 40, and wherein at least a portion of said structural core 18A is covered by at least one primary layer 18B, designed to improve fracture and/or impact and/or wear resistance of said ring-shaped portion.

Abstract: A magnetic bearing assembly for a rotary machine having a rotor shaft, comprising a stator magnetic circuit secured to a stationary support element and comprising at least one body of ferromagnetic material and at least one coil, both being fitted in a protective annular housing leaving uncovered a surface of revolution of said ferromagnetic body and a surface of revolution of said one coil, the magnetic bearing assembly comprising an annular thrust collar secured to the rotor shaft and radially extending towards the stator magnetic circuit by a radial portion, said radial portion facing the uncovered surfaces of said ferromagnetic body and said one coil. The annular thrust collar comprises at least one flow channel.

Abstract: An apparatus for sealing an internal environment of a turbomachine includes a first chamber connectable in fluid communication with a high pressure environment of a turbomachine so that a working fluid can flow from the high pressure environment to the first chamber; and a second chamber in fluid communication with a lubrication circuit so that a lubricant can flow from the lubrication circuit to the second chamber. The first and second chambers are arranged in fluid communication with each other so that the working fluid can flow from the first to the second chamber. A return line for the working fluid is in fluid communication with the first chamber and connectable in fluid communication with a low pressure environment of the turbomachine so that the working fluid can flow from the first chamber to the low pressure environment. A pressure regulating device is included along the return line and is configured to provide a predetermined pressure drop.

Abstract: The impeller includes a main body with a root, a shroud and a plurality of blades connecting the root and the shroud. Protection elements are associated to the blades and constitute at least the front part of the blades. The protection elements may consist of separate bodies or may be grouped together to form one or more protection bodies. In an embodiment, the material of the protection elements is different from the material of the main body, and may be, for example, a cobalt base alloy having a chromium content greater than 20% or nickel base alloy having a chromium content greater than 12%.

Abstract: A method for reducing NOx emissions in a gas turbine in which a flow of primary air and a flow of fuel are fed into a dual annular counter rotating swirler, the primary air flow being fed into the inner and outer annular chambers, wherein the method comprises the step of injecting the flow of fuel into the inner annular chamber; another embodiment is a gas turbine air fuel mixer comprising a dual annular counter rotating swirler comprising a fuel supplying element adapted to supplying fuel inside the inner chamber of the swirler; another embodiment is a gas turbine provided by such air fuel mixer.

Abstract: A method for starting and operating a plant for the liquefaction of a gaseous product comprising the steps of electrically connecting a variable frequency drive to a motor of a first machine string; increasing the speed of the motor of the first machine string up until a first predefined threshold; electrically disconnecting the variable frequency drive from the motor of the first machine string; electrically connecting the variable frequency drive to a motor of a second machine string; the first predefined threshold is function of said frequency of the power supply grid. The variable frequency drive can be switched during operation of the plant among the strings according to process requirements.

Abstract: A compressed air energy storage system is described, including a compressor fluidly coupled to a compressed air reservoir and an expansion train including at least a first turbine. The system further includes an electric machine aggregate configured: for converting electric power into mechanical power and driving the compressor therewith during the energy storing mode; and for converting mechanical power produced by the expansion train into electric power during the power production mode. A combustor is configured for receiving fuel and compressed air and producing combustion gas, and for supplying the combustion gas to the first turbine.

Abstract: The component of the turbomachine comprises a body of the component, a bond layer covering a base surface of the body, and a top layer covering the bond layer and made of abradable ceramic material. The base surface of the component has patterned protrusions and, through two covering steps used for forming the bond layer and the top layer, also the top surface of the component has patterned protrusions. The pattern protrusions of the base surface may be obtained in different ways, for example casting, milling, grinding, electric discharge machining or additive manufacturing. The patterned protrusions belong to an abradable seal of the turbomachine, and may be shaped and sized to maintain specified clearances and to reduce flow of a working fluid within turbomachinery equipment and/or it's components.

Abstract: The present disclosure relates to a turbomachine assembly, which includes a shaft, a radial gas expander supported on the shaft between a first bearing and a second bearing, and a compressor supported on the shaft in overhung position adjacent to one or the other of the first and second bearings. The compressor includes a plurality of movable inlet nozzles and the radial gas expander includes a plurality of movable guide vanes.

Abstract: The coupling load measurement method allows to measure load between a first driving shaft and a second driven shaft connected by a hub coupled both with the first shaft and with the second shaft by at least one flexible coupling element coupled to the hub and to the first shaft and/or to the second shaft; the method comprises, during operation of the shafts, a measurement step of measuring a distance variation respect to a reference distance between a first flange of the hub and a second flange of the flexible coupling element and the step of using the measured distance variation for calculating the load.

Abstract: A Centrifugal compressor impeller including a plurality of blades extending from a hub, each blade having a first wall defining a pressure side of the blade, and a second wall defining a suction side of the blade, and a free end defining a tip of the blade, the tip presenting a raised rim aligned to the first wall, the second wall of the blade being at least partially aligned with a surface of the tip free from the raised rim.

Abstract: A turbomachine impeller is disclosed, which includes: a hub having a rotation axis; a shroud; a plurality of blades between the hub and the shroud; and a plurality of flow vanes, each flow vane being defined between the hub, the shroud and neighboring blades, each flow vane having a flow vane inlet and a flow vane outlet. Each flow vane extends radially inwardly from the flow vane inlet towards a radially innermost flow vane section, and from the radially innermost flow vane section to a flow vane outlet.

Abstract: A method for manufacturing a machine component made of metal-based material is described. The method comprises the steps of: providing a powder blend comprising at least one metal-containing powder material and at least one strengthening dispersor in powder form, wherein the strengthening dispersor in powder form has an average grain size less than an average grain size of the metal-containing powder material; and forming the machine component by an additive manufacturing process using the powder blend.

Abstract: The arrangement for monitoring rubbing between a rotary part and a stationary part in a rotating turbomachine comprises at least one mechanical oscillations detector for measuring mechanical oscillations at least one point of the turbomachine, at least one particles detector for measuring debris passing in at least one section of a flow path of the turbomachine, and an electronic monitoring unit electrically or electromagnetically connected to the oscillations detector and the particles detector, and arranged to acquire and process signals generated by the oscillations detector and the particles detector. The electronic monitoring unit uses the oscillations measurement primarily for estimating presence of rubbing and the debris measurement primarily for estimating severity of rubbing.

Abstract: A sector for the assembly of a stage of a turbine comprises a central and a peripheral portion; a plurality of blades attached between the central and the peripheral portions; a first and a second side opposite to each other, the first side is configured to join with the second side of another sector, the first side is provided with a first connecting portion and the second side is provided with a second connecting portion configured to mate with a first connecting portion of a first side of another sector.

Abstract: A compressor system is described, including: at least a first compressor having a suction side and a delivery side; an anti-surge line; an anti-surge valve arranged along the anti-surge line and controlled for recirculating a gas flow from the delivery side back to the suction side of the compressor; a heat removal arrangement between the anti-surge valve and the suction side of the compressor.

Abstract: A method is described for providing antisurge control in a system comprising a compressor having at least an upstream compressor stage, a downstream compressor stage and a side stream bringing flow into a flow passage between the upstream compressor stage and the downstream compressor stage. The method provides for estimating a temperature of a flow delivered by the upstream compressor stage using a non-dimensional performance map of the upstream compressor stage and further estimating a temperature of a flow entering the downstream compressor stage based on the mass flow and flow temperature of the flow delivered by the downstream compressor stage and the mass flow and the flow temperature of the side stream. The method further provides for performing antisurge control of the downstream compressor stage based on the temperature of the flow entering the downstream compressor stage.

Abstract: A power converting system is described, comprising a source of waste heat and an organic Rankine cycle system. The organic Rankine cycle system in turn comprises at least a turboexpander, at least a rotating load mechanically coupled to the turboexpander and driven thereby, and a variable-speed mechanical coupling between the turboexpander and the rotating load.