BLADE WITH IMPROVED COOLING CIRCUIT AND GAS TURBINE ENGINE CONTAINING SUCH A BLADE Russian patent published in 2022 - IPC F01D5/18 

FIELD: aviation.

SUBSTANCE: invention relates to a turbine blade containing a blade shank and feather (13) passing radially outward from blade shank (12), while feather (13) contains the first inner cooling circuit containing trough cavity (33, 36) passing radially along trough wall (16) and first inner wall (47, 45) located between trough wall (16) and back wall (18), back cavity (34, 37) passing radially along back wall (18) and second inner wall (47, 43) located between trough wall (16) and back wall (18). The first cooling circuit contains through inner cavity (35, 38) formed between two through walls (59, 57, 55, 53), each of which passes between trough wall (16) and back wall (18). Trough cavity (33, 36), back cavity (34, 37) and through inner cavity (35, 38) are sequentially connected via fluid.

EFFECT: inner structure of the blade becomes more flexible, which limits the occurrence of stresses in the blade and, consequently, increases its resistance to temperature drops and increases its service life.

10 cl, 13 dwg