SYSTEM OF LIQUID COOLING OF POWER GAS TURBINE HIGH-TEMPERATURE STAGE BLADES Russian patent published in 2013 - IPC F01D5/18 

FIELD: engines and pumps.

SUBSTANCE: system of liquid cooling of blades in at least one high-temperature stage of a gas turbine, fixed with a tail part on a rim of a bearing disc of the specified stage of the turbine rotor, comprises at one of the sides of the bearing disc a circular chute that is axisymmetric to it and open downwards, at least two fixed nozzles, and also longitudinal cooling channels arranged along the perimeter of the blade profile in its sub-surface layer. Nozzles are directed symmetrically to the side for supply of cooling liquid into the chute. Inlet ends of longitudinal cooling channels are communicated by connection channels with a chute to form a loop-like cooling tract in each blade and free surface of liquid in the chute during rotor rotation. The chute is located in the zone of the disc with the average radius determined on the basis of the ratio defended in the invention. Outlet ends of the cooling channels are communicated in the same manner as the inlet ones, with the help of connection channels with the chute. Capacity of the chute is 100…110 times more than the capacity of the cooling tract of one blade. Total efficiency of all nozzles is selected to maintain stable level of free surface of cooling liquid within the chute during rotor rotation.

EFFECT: invention increases reliability of liquid cooling of entire profile part of blades, provides for thermal condition of a blade in accordance with heat resistance of selected material, and provides for the possibility of combination of with air cooling of blades in subsequent less thermally stressed stages of a turbine .

7 cl, 2 dwg