FIELD: engines and pumps.
SUBSTANCE: gas turbine engine vane comprises the first blade, the second blade and at least one plate. Each of the first and second blade has inner and outer sides placed between the front and rear edges. The first and second blades are arranged near in such a manner that the inner side of the first blade is placed with its entire surface opposite to the inner side of the second blade. The plane connects the inner side of the first blade and the inner side of the second blade and is placed to the rear edge of the vane. The rear edge of the vane is formed with the rear edge of the first blade and the rear edge of the second blade. The rear edge of the first blade is levelled relative to the rear edge of the second blade and is arranged near. Other inventions of the group relate to a turbine wheel and a gas turbine engine, comprising the above vanes.
EFFECT: inventions make it possible to reduce aerodynamic losses on a vane.
14 cl, 5 dwg
