Abstract: The gas turbine engine comprises a gas generator (66), comprised of a compressor section (11), and a power turbine section (65). The power turbine section (65) comprises a power turbine rotor (81) supported by a power turbine shaft (93), which is mechanically uncoupled from the gas generator (66). The power turbine shaft (93) has an axial cavity (511) therein, fluidly coupled to a bearing sump (521) fluidly coupled to the compressor section (11) and housing at least one bearing (106) supporting a shaft of the gas generator (66). An air venting path (527) extends from said axial cavity (511) and leads in a combustion gas flow path (515) downstream of the power turbine rotor (81).

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: A subsea assembly comprising an electric subsea machine having an electric motor driving an operator, and a coolant circuit at least partially located in thermal contact with the electric motor, the coolant circuit including a cooling assembly located externally from the subsea machine, the cooling assembly comprising at least a heat transfer element, the subsea machine and the cooling assembly being supported by a common supporting frame; at least a part of the heat transfer element is integrated in the frame.

Abstract: The gas turbine engine comprises a gas generator (66), comprised of a compressor section (11), and a power turbine section (65). The power turbine section (65) comprises a power turbine rotor (81) supported by a power turbine shaft (93), which is mechanically uncoupled from the gas generator (66). The power turbine shaft (93) has an axial cavity (511) therein, fluidly coupled to a bearing sump (521) fluidly coupled to the compressor section (11) and housing at least one bearing (106) supporting a shaft of the gas generator (66). An air venting path (527) extends from said axial cavity (511) and leads in a combustion gas flow path (515) downstream of the power turbine rotor (81).

Abstract: A sealing system is described for effecting a seal of a gap (G1; G2) in a turbomachine (1) between a first structural member (21; 23) and a second structural member (31). The sealing system includes a sealing apparatus comprising a sealing member (47; 77) comprising a first edge portion (49; 79) and a second edge portion (51; 81). The two edge portions are parallel to one another and the first edge portion (49; 79) forms a pivoting connection to the first structural member (21; 23). The first structural member (21; 23) further comprises a seat (55; 85) rotatably housing the first edge portion (49; 79) of the sealing member (47; 77). The second edge portion (51; 81) comprises a curved contact surface (51.1; 81.1), in sealing contact with a contact surface (67; 97) of the second structural member (31).

Abstract: A method for improving partial load efficiency in a gas turbine engine including a compressor, burners, a high pressure turbine and a low pressure turbine; including the step of operating the gas turbine engine by regulating at least: air mass flow rate and flame temperature; regulation is carried out by controlling at least: the air mass flow rate supplied to the combustion chamber from the compressor, and the number of operating burners, and the change in enthalpy drop between the high and low pressure turbine to control the air mass flow rate.

Abstract: The invention relates to a method and apparatus for assembling nozzles 31 between buckets 41,42 of a turbine, particularly a gas turbine, in which a temporary fixing of the nozzles 31 to the buckets 41,42 during the assembly is provided.

Abstract: A drainage apparatus for a motorcompressor comprises a first pipe with a first end configured to be inserted in a drainage sump of a motorcompressor; a second end configured to be connected to a duct of a stage of the motorcompressor; a device for generating a pressure difference between said second and said first end so that liquid is taken from said drainage sump and delivered into said duct.

Abstract: A compressor comprising: a casing; an upstream impeller and a downstream impeller for rotation in the casing; a diaphragm comprised of an internal portion and an external portion; an upstream diffuser fluidly coupled to an outlet of the upstream impeller; a return channel fluidly coupled to the upstream diffuser and to an inlet of the downstream impeller, the return channel has a plurality of return-channel blades connecting the internal and external diaphragm portions; and a downstream diffuser fluidly coupled to an outlet of the downstream impeller is disclosed. A first coolant passage is in the internal diaphragm portion and extends around an inner core, the first coolant passage being in heat-exchange relationship with the upstream diffuser and the return channel. A second coolant passage and third coolant passage are separated by a second inner core in the external diaphragm portion and in a heat-exchange relationship with the return channel and the downstream diffuser.

Abstract: A cooling system for cooling an integrated, high pressure, motorcompressor unit, the cooling system including a second motorcompressor unit and at least a first duct fluidly connecting a process fluid connection point located at the second motorcompressor unit to at least one process fluid injection point located at the first motor area of the first motorcompressor unit.

Abstract: An integrated turbomachine is described, comprising: a casing; an electric motor and a driven turbomachine component housed in the casing; a rotating shaft drivingly connecting the electric motor and the driven turbomachine component; a thrust bearing and a radial bearing rotatingly supporting the shaft; an axial locking device housed inside the casing, for applying a thrust to the shaft, parallel to the rotation axis (A-A) of the shaft, and comprised of an actuator member, configured to selectively activate and/or deactivate the axial locking device.

Abstract: A casing for a subsea compressor comprises a main body having a central axis; a plurality of interconnection flanges attached to the main body; wherein the main body comprises an inner layer made of corrosion resistant material; an outer layer applied over the inner layer and made of a composite material; wherein the outer layer extends along the entire length of said main body.

Abstract: A magnetic bearing comprising a stator magnetic circuit secured to a stationary support device, the stator magnetic circuit comprising at least one coil and a ferromagnetic body placed in a protective annular support, the protective annular support leaving uncovered a surface of the ferromagnetic body and a surface of the at least one coil. The bearing also comprises at least one annular plug placed on the surface of the at least one coil which is left uncovered by the protective annular support, and the annular plug and the surface of the ferromagnetic body which is left uncovered by the protective annular support are coated by a protective layer.

Abstract: The turbomachine comprises a stationary component, a rotary component, rotatingly supported in the stationary component, and a sealing arrangement between the rotary component and the stationary component. A cooling arrangement is further provided, which is configured and designed for delivering a cooling fluid to the sealing arrangement and removing heat therefrom.

Abstract: A subsea assembly comprising an electric subsea machine having an electric motor driving an operator, and a coolant circuit at least partially located in thermal contact with the electric motor, the coolant circuit including a cooling assembly located externally from the subsea machine, the cooling assembly comprising at least a heat transfer element, the subsea machine and the cooling assembly being supported by a common supporting frame; at least a part of the heat transfer element is integrated in the frame.

Abstract: A drainage apparatus for a motorcompressor comprises a first pipe with a first end configured to be inserted in a drainage sump of a motorcompressor; a second end configured to be connected to a duct of a stage of the motorcompressor; a device for generating a pressure difference between said second and said first end so that liquid is taken from said drainage sump and delivered into said duct.

Abstract: A rotating machine comprises a shaft, a casing, at least one main magnetic bearing connected to the shaft for rotatably supporting the shaft inside the casing, at least one auxiliary radial rolling bearing and at least one auxiliary axial rolling bearing which are disposed between the shaft and the casing to respectively support radial loads only and axial loads only.

Abstract: A magnetic bearing assembly for a rotary machine, having a rotor circuit and a stator magnetic circuit secured to a stationary support element having 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 facing a surface of revolution of the rotor circuit. The bearing assembly comprises at least one row of blades secured on the rotor circuit.

Abstract: A rotating machine comprises a shaft, a casing, at least one main magnetic bearing connected to the shaft for rotatably supporting said shaft inside the casing, at least one first and one second auxiliary rolling bearings positioned between the shaft and the casing to support axial and radial loads, and first and second axial abutment means positioned on the shaft to transmit axial loads to inner rings of the rolling bearings. The machine further comprises a spacer axially positioned between facing faces of the inner rings of said rolling bearings for the transmission of the axial loads between said inner rings, and at least a first axial retaining means positioned on the casing and located axially between facing faces of the outer rings for the transmission of the axial loads between at least one of said outer rings and the casing.

Abstract: The gas turbine system comprises an aeroderivative gas turbine engine and a load having a shaft line drivingly coupled to the gas turbine engine. The gas turbine engine comprises a high-pressure turbine section and a high-pressure compressor section, drivingly coupled to one another by a first turbine shaft. The gas turbine engine further comprises an intermediate-pressure turbine section and a low-pressure compressor section, drivingly coupled to one another by a second turbine shaft, coaxial to the first turbine shaft (91). Furthermore, a combustor section is provided, fluidly coupled to the high-pressure compressor section and to the high-pressure turbine section. A free power turbine, supported by a third turbine shaft which is mechanically uncoupled from the first turbine shaft and the second turbine shaft, and is directly coupled to the shaft line, such that the shaft line and the third turbine shaft rotate at the same rotational speed.