TURBINE UNIT, WHICH CORRESPONDS TO TUBE FOR COLLISION COOLING AND GAS TURBINE ENGINE Russian patent published in 2016 - IPC F01D5/18 F01D9/04 

FIELD: machine building.

SUBSTANCE: turbine assembly comprises hollow aerodynamic part, having at least one cavity with at least one tube of impact cooling to be fitted inside cavity of hollow aerodynamic part and used for impact cooling, at least cavity inner surface, and at least one platform located at radial end of hollow aerodynamic part, and at least one refrigerating chamber, used for cooling of at least one platform, and which is located on opposite hollow aerodynamic part side of platform. Cooling chamber is restricted at first radial end of platform, and on opposite radial second end, with help of at least one cover plate. Impact cooling tube is made of front and rear elements inserted both in at least one cavity. Front element is located in direction of front edge of hollow aerodynamic part. Rear element is arranged, when viewed in direction from front edge to trailing edge, downstream of front element. Front element of the impact cooling tube passes along span, at least through cooling chamber from platform to cover plate, and rear impact cooling tube ends in span direction on platform.

EFFECT: invention is aimed at improving cooling efficiency of aerodynamic part with minimum losses.

11 cl, 8 dwg