GAS TURBINE Russian patent published in 2014 - IPC F01D5/08 

FIELD: machine building.

SUBSTANCE: gas turbine with a rotor, in which a blade is installed, includes a body with an inlet edge and an outlet edge, which is located along longitudinal axis of the above blade from root part to the end part of the blade. In the root part of the body there is a shank installed in a removable manner in a rotor seat. In the body there is a central cavity located along the longitudinal axis from the blade shank to the end part of the blade and intended for passage of cooling fluid medium flow that enters the central cavity of the blade through an inlet hole made in the blade shank and leaves the central cavity of the blade at least through one outlet hole in the blade end part. Cooling fluid medium flow is supplied via a rotor channel that passes through the rotor and is interconnected with the blade inlet hole. At least in one direction, the cross-sectional area of the inlet hole of the blade is larger than the cross-sectional area of the above rotor passage. The outlet hole of the rotor passage has a shape of a diffuser, and in the boundary line of the outlet hole of the rotor passage and the inlet hole of the blade, the cross-sectional area of the outlet hole of the rotor passage covers the cross-sectional area of the blade inlet hole. In the boundary line of the above inlet hole of the blade and the outlet hole of the rotor passage there is an increased pressure cavity formed between the lower surface of the above blade shank and the rotor seat, in which the blade shank is located. The high pressure cavity has a configuration providing venting of cooling fluid medium flow to the outer side of the blade shank or to the inlet edge of the blade body, or to the outlet edge of the blade body.

EFFECT: creation of a cooled blade, in which a provision is made for a flexible configuration of cooling passages and flexible modes for their operation.

12 cl, 7 dwg