Patent ID: 11946387
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
1. A turbine vane of a turbomachine, comprising:
a root carrying a blade extending along a span direction, said blade comprising a trailing edge provided with cooling vents, a first serpentine circuit, and a second serpentine circuit, wherein:
each serpentine circuit includes several ducts extending along the span direction by being connected to each other through bent portions;
each serpentine circuit is supplied with air by a mouth located at the root via its duct which is furthest from the trailing edge;
the first serpentine circuit has an even number of ducts and the second serpentine circuit has an odd number of ducts, or vice versa,
the first serpentine circuit and the second serpentine circuit are terminated by a first terminal duct and a second terminal duct respectively, the first and second terminal ducts running along the trailing edge as an extension of each other, and by being separated from each other by an inner partition wall of the blade, and
the vents are supplied with cooling air from the first serpentine circuit and from the second serpentine circuit.