Abstract: A stator aerodynamic component is disclosed to be placed inside a flow path of a working fluid of a turbomachine; the component has one or more nozzles for ejecting a liquid into the flow path; the liquid to be ejected comes from a duct internal to the component and in fluid communication with a pipe that is external to the component. Also disclosed is a method for cleaning a turbomachine by ejecting a washing liquid from one or more one stator aerodynamic components.

Abstract: A method for monitoring and controlling a hybrid gas turbine system is disclosed, which is performed by a control logic unit. The method is implemented by executing an optimization among operating variables, so as to obtain control signals to control the operation of the hybrid gas turbine system. The hybrid gas turbine system is also disclosed, which includes at least one gas turbine, to be operated by fuel, and at least one electric motor/generator, capable of operating as a generator or as a motor. The hybrid gas turbine system comprises the control logic unit operatively connected to the fuel controller module and to the electric motor/generator controller.

Abstract: A blade for fluid catalytic cracking (FCC) flue hot gas expander with a layer of hard abrasive material localized on the blade tip that contributes to reducing the accumulation of FCC catalyst residuals in the expander.

Abstract: Method for the additive production of three-dimensional articles is disclosed. A powder layer of nickel-based metal alloy having a specific composition is scanned with an energy source so as to melt the powder in at least one point of the layer. Afterwards the energy source is removed from this point so as to solidify the metal alloy and form a layer with a desired shape. Also disclosed are articles obtainable by this method.

Abstract: The sealing system (1) for a machine comprises: a sealing element (4) that is movable back and forth along a direction (D) and that comprises a first recess (41) with first and second surfaces (42, 43), a component (2) of an assembly of the machine that comprises a second recess (21) with first and second surfaces (22, 23), and an elastic element (5). The first and second recesses (41, 21) face each other. The elastic element (5) is partially housed inside the first recess (41) and partially housed inside the second recess (21) so to apply forces on the first and second surfaces (42, 22, 43, 23) depending on where the sealing element (4) is positioned with respect to the component (2).

Abstract: The bundle compressor to a bundle motor for compressor unit compressor unit includes one at fastening device configured to fasten the compressor bundle to a motor casing of the motor compressor unit, and also includes at least one opening sized to couple a motor rotor and a compressor rotor through the at least one opening.

Abstract: The centrifugal compressor comprises a casing and a rotor arranged in the casing and configured to rotate around a vertical rotation axis. The rotor comprises at least one impeller having an impeller suction side and an impeller delivery side. The compressor includes a gas inlet and a gas outlet, as well as a gas flow path extending from the gas inlet to the gas outlet. An inlet plenum extends from the gas inlet towards the impeller suction side. At least one suction tube having a lower suction end and an upper discharge end is arranged such that the lower suction end thereof is arranged at a bottom of the inlet plenum. The suction tube extends upwardly towards the impeller suction side.

Abstract: A gas (or steam) turbine is disclosed including: a rotor with at least one array of rotor blades, a stator with a casing and a shroud ring; the shroud ring extends around the array of blades rotor and the casing extends around the shroud ring. The shroud ring has radial size independent from temperature due to its material and is movably coupled with the casing so to allow the casing of the stator to thermally expand and contract during operation of the turbine while maintaining the shroud ring radial size. Also, the rotor thermally expands and contracts during operation of the turbine, and, at working temperature, tip regions of the rotor blades are in close proximity to an inner region of the shroud ring so that clearance is small or zero at working condition.

Abstract: A compression system comprises a compressor, an inlet duct, a throttling valve installed in the inlet duct, an outlet duct, an anti-surge valve fluidly coupling the outlet duct with a portion of the inlet duct downstream of the throttling valve and a recycle valve fluidly coupling the outlet duct with a portion of the inlet duct upstream of the throttling valve. Keeping the recycle valve open, the anti-surge valve closed and the throttling valve partially closed allows lowering the pressure of the flow entering the compressor during its start-up.

Abstract: The composite seal structure includes a carrier ring and a seal element housed in an annular groove formed between a circumferential outer wall and two side walls of the carrier ring. The seal element has a first region in surface-to-surface contact with the annular groove and a second, seal-ing region protruding from the annular groove. A fastening arrangement couples the seal element and the carrier ring to one another. The fastening arrangement comprises a plurality of fastening pins circumferentially arranged around the axis of the carrier ring. Also disclosed is a method for manufacturing the seal structure.

Abstract: A thermodynamic system containing a working fluid is disclosed. The thermodynamic system comprises at least a working fluid collection vessel (11) adapted to contain a liquid phase and a gaseous phase of the working fluid in thermodynamic equilibrium. A chilling arrangement (51) is functionally coupled to the fluid collection vessel (11) and adapted to remove heat from the working fluid collected in the working fluid collection vessel (11) and thereby reduce pressure in said thermodynamic system. Also disclosed are methods for depressurizing a thermodynamic system containing a working fluid in liquid/gas equilibrium.

Abstract: A method of making hollow turbomachine components is disclosed. The method provides for an additive manufacturing step, wherein on a substrate the following are manufactured in sequence: a first terminal portion of a semi-finished component, said first terminal portion adhering to said substrate, an intermediate portion adjoining the first terminal portion, and a second terminal portion adjoining the intermediate portion. After cooling of the component, at least one of said first terminal portion and second terminal portion is removed. The removed terminal portion includes sacrificial features, where thermally induced deformations of the component are concentrated, or which are aimed at stiffening the component, such that deformations are reduced or prevented.

Abstract: A valve for a reciprocating machine is disclosed. The valve includes a seat provided with flow apertures therein. A valve closing member is adapted to co-act with the seat for selectively closing and opening the flow apertures. A cage is connected to the seat and forms a guide, in which the actuation stem of a valve closing member is slidingly engaged and guided.

Abstract: The pump comprises a casing; a statoric part stationarily housed in the casing; at least one impeller arranged for rotation in the casing. A process fluid path extends though the statoric part and the impeller. A bearing rotatingly supports the impeller in the casing and a bearing lubrication path is provided, to circulate a fluid flow through the bearing. A rotary screw integral with the impeller and rotating therewith when the pump is operating provides a pumping action on process fluid such that rotation of the impeller promotes process fluid circulation by means of said rotary screw through the bearing lubrication path.

Abstract: The bearing has a housing and a plurality of pads coupled with the housing. The pads form bearing surfaces facing a shaft receiving space. The pads are provided with cooling micro-channels formed therein, adapted to circulate lubrication fluid and improve heat removal.

Abstract: A method for operating start-up of a compressor train is disclosed. The train includes a driver machine and at least a centrifugal compressor drivingly coupled to the driver machine. The centrifugal compressor in turn includes a plurality of compressor stages and at least a first set of variable inlet guide vanes at an inlet of one of the compressor stages. The method includes at least partly closing the first set of variable inlet guide vanes; when the first set of variable inlet guide vanes is at least partly closed, starting rotation of the centrifugal compressor and accelerating the centrifugal compressor up to a minimum operating speed; opening the at least one set of variable inlet guide vanes to increase the gas flow through the centrifugal compressor once the minimum operating speed has been achieved.

Abstract: It is disclosed a method for reducing the pulsation level in a multi-compressor plant where each compressor of a plurality of compressors is driven by a respective motor. The method manages to reduce the pulsation level by starting a first motor of a first compressor and then starting in succession each one of the other motors in a way to synchronize all motors between each other with a specified phase shift.

Abstract: The combined radial-axial turboexpander (1) comprises a casing (3) and a shaft (5) arranged in the casing (3) for rotation therein. A radial impeller (25) and an axial expansion wheel (43) are mounted on the shaft (5). The axial expansion wheel (43) is arranged downstream of the radial impeller (25). A working fluid expands sequentially in the radial impeller and in the axial expansion wheel.

Abstract: According to one aspect of the present disclosure, a turbo-compressor (100) is provided. The turbo-compressor (100) includes: a rotor assembly (110) extending in an axial direction A and comprising at least one impeller (112) configured for pressurizing a gas; a magnetic bearing (120) supporting the rotor assembly (110) on a high-pressure side (113) of the at least one impeller (112); and a cooling passage (130) configured for directing a first portion of the pressurized gas (P1) through a bearing gap (132) of the magnetic bearing (120) for cooling the magnetic bearing (120). According to a further aspect, a method of operating a turbo-compressor is described.

Abstract: A method for manufacturing a turbine blade 1, is provided. The method comprises the following steps: producing a shell and core assembly by additive manufacturing process, the shell and core assembly defining at least one internal cavity and having an internal structure corresponding to at least one internal cooling circuit of the turbine blade; pouring molten metal in the internal cavity of the shell and core assembly; solidifying the metal; removing the shell and core assembly.