Nuovo Pignone Tecnologie Srl

General Electric Company

Nuovo Pignone Srl

Marco Boncinelli

Luciano Mei

Massimo Giannozzi

Iacopo Giovannetti

Nicola Banchi

Egidio Pucci

Girolamo Tripoli

Stefania Stramare

Carlo Giolli

Giovanni Salvestrini

Davide Lazzarato

Marcello Puggioni

Mirco Innocenti

Marco Pelella

Alessio Milani

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 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

The repair member includes an inner platform, an outer platform portion, and an airfoil portion connecting the inner and outer platform portions; the inner platform portion is configured so to reach an edge of a first ring or sector of ring of a vane assembly of the damaged vane, and the outer platform portion is configured so to reach an edge of a second ring or sector of ring of the a vane assembly of the damaged vane; the inner platform portion, the outer platform portion, and the airfoil portion are configured so to allow insertion of the repair member into the vane assembly by a pure translation movement being along an insertion direction and having a movement component parallel to an axes of the first and second rings or sectors of ring.

Repair member for a vane assembly of a gas turbine and method for repairing a damaged vane of a vane assembly of a gas turbine

Heat exchanger device for a gas seal () for centrifugal compressors equipped with a fluid heat exchanger () positioned between the gas seal () and the housing wall of the seal to keep the temperature of the seal () low in the case of high temperatures of the wall and/or compressed gas.

Heat exchanger for centrifugal compressor gas sealing

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Florence, Italy

Marco Boncinelli