Nuovo Pignone Srl

Nuovo Pignone Spa

Nuovo Pignone Tecnologie Srl

Nuovo Pignone Holding S.p.a.

General Electric Company

Nuovo Pignone Holdings, S.p.a.

Nuovo Pignone International S.r.l.

Luciano Mei

Manuele Bigi

Alessio Miliani

Massimiliano Mariotti

Massimo Pinzauti

Anthony John Dean

Giuseppe Sassanelli

Franco Frosini

Andrea Massini

Duccio Fioravanti

Dino Bianchi

Alberto Ceccherini

Craig Allen Bielek

Giuseppe Iurisci

Antonio Asti

Christian Aalburg

Massimo Camatti

Massimiliano Borghetti

Odd Marius Rosvold

Michele D'Ercole

Silvio Giachetti

Rajesh Mavuri

Giuseppe Vannini

Marco Formichini

Marco Romanelli

Marco Anselmi

Marco Boncinelli

Egidio Pucci

Simon Schoewel

Simone Marchetti

Giacomo Landi

Francesco Caratelli

Alessandro Russo

Stefano Falomi

Luca Lombardi

Giacomo Ragni

Marco M A Anselmi

Massimiliano Cirri

Fabrizio Franci

Riccardo Carta

Luca Innocenti

Marco Listori

Allesandro Giammarci Giammarchi

Francesco Bongini

Pawel Twarowski

Marek Watrobski

Benedetto Tozzi

Marco Listorti

Allessandro Giammarchi Giammarchi

Duccio Fioraventi

Marek Watróbski

Pawel Twardowski

A sealing system is described for effecting a seal of a gap (G; G) in a turbomachine () between a first structural member () and a second structural member (). The sealing system includes a sealing apparatus comprising a sealing member () comprising a first edge portion () and a second edge portion (). The two edge portions are parallel to one another and the first edge portion () forms a pivoting connection to the first structural member (). The first structural member () further comprises a seat () rotatably housing the first edge portion () of the sealing member (). The second edge portion () comprises a curved contact surface (), in sealing contact with a contact surface () of the second structural member (). Further disclosed herein is a gas turbine engine () with a combustor liner () and a sealing arrangement to seal a gap (G; G) between the combustor liner () and the turbine nozzles of the first turbine stage.

Turbomachine sealing system and turbomachine including the sealing system

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

Venting system for bearing sump

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.

Magnetic bearing assembly having inner ventilation

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.

Subsea assembly

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.

Operation method for improving partial load efficiency in a gas turbine and gas turbine with improved partial load efficiency

The invention relates to a method and apparatus for assembling nozzlesbetween bucketsof a turbine, particularly a gas turbine, in which a temporary fixing of the nozzlesto the bucketsduring the assembly is provided.

Method and apparatus for assembling nozzles between buckets of a turbine, particularly a gas turbine

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.

Drainage apparatus for a motorcompressor

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.

Centrifugal compressors with integrated intercooling

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.

Cooling system for cooling a motorcompressor unit

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.

Casing for a turbomachine

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.

Integrated turbomachine with an axial locking device

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.

Magnetic bearing and rotary machine comprising such a bearing

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.

Sealing clearance control in turbomachines

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.

Rotating machine with at least one active magnetic bearing and auxiliary rolling bearings

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.

Electro-magnetic bearing assembly with inner ventilation to cool the bearing

Growing community of inventors

Florence, Italy

Luciano Mei