Nuovo Pignone Srl

Other

Nuovo Pignone Tecnologie Srl

Nuovo Pignone Spa

General Electric Company

Baker Hughes, a Ge Compnay, LLC

Nuovo Pignone Holding S.p.a.

Sulzer Metco (us) Inc.

Nuovo Pignone Holdings, S.p.a.

Thermodyne Sas

Massimo Giannozzi

Iacopo Giovannetti

Andrea Massini

Leonardo Tognarelli

Pierluigi Tozzi

Gabriele Masi

Scott Roger Finn

Manuele Bigi

Bulent Aksel

Antonella Dimatteo

Federico Iozzelli

Julian O'Flynn

Dino Bianchi

Filippo Cappuccini

Wayne Charles Hasz

Farshad Ghasripoor

Dennis Michael Gray

Vittorio Michelassi

Christophe Lanaud

Krishnamurthy Anand

Mitchell R Dorfman

Warren Arthur Nelson

Lorenzo Cosi

Nicola Campo

Michelangelo Bellacci

Nuo Sheng

Marco Romanelli

Marco Anselmi

Luc Stephane Leblanc

Francesco Chiesi

Marco Boncinelli

Riccardo Paoletti

Paul Matthew Thomas

Andrew R Nicoll

Girolamo Tripoli

Nicole Barbara Piche

Dieter R Sporer

Ulrike Taeck

Eugenio Del Puglia

Massimiliano Buccioni

Domenico Di Pietro

Francesco Mastromatteo

Michelangelo Bellaci

Giovanni Salvestrini

Emanuele Pietrangeli

Lacopo Giovannetti

Dennis M Gray

Turbomachines, as well as their components, are disclosed being in the field of production and treatment of oil and gas containing e.g. hydrocarbon plus hydrogen sulfide, carbon dioxide, with or without other contaminants. The components are made of a high corrosion high temperature resistant alloy, capable of resisting to corrosion and/or stress at high temperature better than state of art martensitic stainless steels and behaving similarly to premium nickel base superalloys, and at the same time showing a very improved hardness value.

Process for making a component of a turbomachine, a component obtainable thereby and turbomachine comprising the same

A method for manufacturing a turbomachine component is disclosed, including the steps of producing, by additive manufacturing, a plurality of separate segments of the turbomachine component, having a skin surrounding an empty volume corresponding to a massive part of the turbomachine component; assembling the separate segments of the turbomachine component together forming a semi-finished component, with an empty cavity therein; filling cavity of the semi-finished component with a bulk flowable material; and densifying and solidifying the bulk flowable material in the cavity.

Method for manufacturing a turbomachine component

A silicide-based composite material is disclosed, comprising a silicide of Mo, B, W, Nb, Ta, Ti, Cr, Co, Y, or a combination thereof, Si3N4, and at least an oxide, as well as and a process for producing the same.

Silicide-based composite material and process for producing the same

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%.

Impeller with protection elements and centrifugal compressor

A method for manufacturing a component of a rotating machine comprises the steps of forming a structural inner portion by additive manufacturing from a first material; covering the structural inner portion with a protective outer portion made of a second material; the first material has a melting point higher than a second material.

Method for manufacturing a component of a rotating machine

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.

Method of manufacturing a component of a turbomachine, component of a turbomachine and turbomachine

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.

Method for manufacturing machine components by additive manufacturing

The method of protecting a component of a turbomachine from liquid droplets erosion provides covering at least one region of a component surface exposed to a flow of a fluid containing a liquid phase to be processed by the turbomachine with a protective layer. The protective layer consists of a plurality of adjacent sub-layers of different materials having high hardness in the range of 1000-3000 HV and low fracture toughness below 20 MPam. The materials are typically nitrides or carbides of titanium or aluminum or chromium or tungsten. In an embodiment, the covering is carried out by a PVD technique, in particular by Cathodic Arc PVD, or a CVD technique. The method may be applied to any component of turbomachines, but it may be particularly beneficial for parts of centrifugal compressors.

Method of protecting a component of a turbomachine from liquid droplets erosion, component and turbomachine

A method for preventing corrosion in a component of a turbo-machine having a metal substrate made of carbon steel, low alloy steel and stainless steel includes: a first deposition step of depositing a first metallic layer on the substrate by electroplating; a second deposition step of depositing at least a second layer of a nickel alloy on the first layer by electroless plating; at least one thermal treatment step after the deposition steps, said thermal treatment being applied at a temperature and for a time depending on the overall thickness of the layers, the value of said temperature being directly proportional to the thickness, the value of said time being inversely proportional to the temperature.

Method for preventing corrosion and component obtained by means of such

A centrifugal impeller for a turbomachine is provided. The centrifugal impeller comprises a plurality of aerodynamic vanes, each of the aerodynamic vanes having internal walls on which is associated a fabric element.

Centrifugal impeller and turbomachine

An impeller for a turbo-machine is provided. The impeller includes a metallic base having a back surface and a front surface opposite to the back surface; at least one blade extending on the front surface of the metallic base; a composite shroud attached to the at least one blade such that plural closed paths are formed by the front surface of the metallic base, the at least one blade and the composite shroud; and a connector configured to attach the composite shroud to the metallic base or the at least one blade.

Impeller for a turbomachine and method for attaching a shroud to an impeller

A mold for a centrifugal impeller for a turbomachine is provided. The mold comprises at least one annular insert, wherein the annular insert comprises a plurality of aerodynamic vane inserts configured to reproduce an annular assembly of aerodynamic vanes of a finished centrifugal impeller.

Mold for a centrifugal impeller, mold inserts and method for building a centrifugal impeller

A seal system, for an apparatus that includes a rotatable portion with airfoils coupled thereto and a stationary portion with an inner surface, includes an abradable portion including at least one abradable layer of an abradable material formed over the inner surface. The seal system also includes an abrading portion disposed over at least a portion of a substrate of the airfoil. The abrading portion includes at least one abrading layer formed on at least a portion of the substrate and a plurality of abrasive particles embedded within the abrading layer. The plurality of abrasive particles includes at least one of substantially all of one of tantalum carbide (TaC), aluminum oxide (AlO), and ziconia (ZrO), cubic boron nitride (cBN) and AlOin predetermined ratios, cBN, AlOand ZrOin predetermined ratios, AlOand ZrOfused together in predetermined ratios, and TaC and AlOin predetermined ratios.

Seal systems for use in turbomachines and methods of fabricating the same

An impeller for a turbo-machine and is provided. The impeller includes a metallic base having a central hole, a back surface and a front surface opposite to the back surface; at least one blade extending on the front surface of the metallic base; a composite shroud attached to the at least one blade such that plural closed paths or vanes are formed by the front surface of the metallic base, the at least one blade and the composite shroud; and a connector configured to attach the composite shroud to the metallic base or the at least one blade.

Composite shroud and methods for attaching the shroud to plural blades

Devices and methods provide for an impeller for use in a compressor. A method for manufacturing the impeller includes: attaching an intermediate layer to a base metal by placing a first metal powder into a gap between a first insert and the base metal; processing with hot isostatic pressing the base metal, the first metal powder and the first insert such that the intermediate layer is bonded to the base metal; attaching an external layer to the intermediate layer by placing a second powder into a gap between a second insert and the intermediate layer; processing the base metal, the intermediate layer, the second metal powder and the second insert via hot isostatic pressing such that the external layer is bonded to the intermediate layer; and removing the second insert to form the impeller, wherein the external layer is corrosion resistant.

Jacket impeller with functional graded material and method

Growing community of inventors

Florence, Italy

Massimo Giannozzi