COOLED DESIGN OF A BLADE OR BLADES OF A GAS TURBINE AND METHOD OF ITS ASSEMBLY Russian patent published in 2020 - IPC F01D5/18 

FIELD: turbines or turbomachines.

SUBSTANCE: present invention relates to a cooled structure of a gas turbine blade or blade and a method for its assembly. Cooled structure comprises, mainly, hollow aerodynamic profile (12), injection pipe (15) and injection pipe sleeve (200). Insertion (200) of injection pipe includes at least one segment (201) of injection pipe bushing, hollow aerodynamic profile (12), having on its inner surface (210) longitudinal ribs (211) extending from front edge (16) to rear edge (20) of hollow aerofoil (12). First segment (202) of injection pipe bushing at least from one segment (201) of injection pipe bushing provides cooling air flow blocker (204) provided with slits on surface (205) of first segment (202) of injection pipe bushing, first segment (202) of injection pipe bushing is inserted into hollow aerodynamic profile (12) so, that ribs (211) of hollow aerodynamic profile (12) are engaged with corresponding slots (208) of cooling air flow blocker (204) provided with slots, and so that surface (205) of first segment (202) of injection pipe bushing rests on ribs (211). Injection pipe (15) is inserted into hollow aerodynamic profile (12) so that at least one segment (201) of the injection pipe sleeve is located between inner surface (210) of the hollow aerofoil profile (12) and outer surface (220) of injection pipe (15).

EFFECT: invention improves control of cooling flow distribution, reduces cooling flow rate, thereby improving engine efficiency and increasing service life.

11 cl, 17 dwg