Nuovo Pignone Tecnologie Srl

Nuovo Pignone Srl

Girolamo Tripoli

Massimo Giannozzi

Iacopo Giovannetti

Marco Boncinelli

Simone Cubeda

Irene Cresci

Fabrizio Paone

Giovanni Salvestrini

Luca Andrei

The nozzle segment for a gas turbine comprises an inner platform and an outer platform as well as a plurality of airfoils arranged between the inner platform and the outer platform. A set of platform film cooling holes are provided, including at least one inner platform film cooling hole on a surface of the inner platform or on a surface of the outer platform facing said hot gas flow passage. A ratio between a distance in tangential direction of the platform film cooling hole from the pressure side of the respective airfoil and a width of the hot gas flow passage in tangential direction at the platform film cooling hole is comprised between 0 and 0.5.

Gas turbine nozzles with cooling holes and turbine

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

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Florence, Italy

Girolamo Tripoli