Nuovo Pignone Tecnologie Srl

Simone Cubeda

Leonardo Tognarelli

Paolo Di Sisto

Girolamo Tripoli

Fabrizio Paone

Luca Andrei

Irene Cresci

Paolo Dl Sisto

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

A turbine, and particularly a low pressure turbine is disclosed, which comprises a plurality of rotor members and spacers for arranged between rotor members, to avoid that an ingested gas flow from the hot gas flow path channel reaches the wheel space. The rotor members each include a deflector. The deflector is placed in correspondence with each spacer and deflects the ingested gas flow over the upper surface of the spacer, thus preventing it to heat up the roots of the blades.

Turbine and blade for the protection of the root from flow path hot gases

A turbine, and particularly a low pressure turbine is disclosed, which comprises a plurality of rotor members and spacers for arranged between rotor members, to avoid that an ingested gas flow from the hot gas flow path channel reaches the wheel space. The rotor members each include a deflector. The deflector is placed in correspondence with each spacer and deflects the purging air pumped up from the wheel spaces by the rotor members, to prevent the ingested gas flow to heat up the roots of the blades.

Growing community of inventors

Florence, Italy

Simone Cubeda