NOZZLE SECTOR FOR TURBINE ENGINE WITH DIFFERENTIALLY COOLED BLADES Russian patent published in 2020 - IPC F01D9/04 F01D5/18 

FIELD: machine building.

SUBSTANCE: invention relates to nozzle sector (22) for turbine engine. Nozzle sector (22) for turbine (2) of turbomachine (1) comprises radially outer support flange (24) for blades, radial inner support flange (26) for blades, first end vane (81), second end vane (84) and at least one first central vane (82, 83) between end vanes (81, 84) along the circumferential direction (ZZ) of the flanges and means (37, 50, 44, 46, 54, 56) for cooling blades. Blades (81, 82, 83, 84) pass radially between flanges (24, 26) along direction XX of span of these blades. Cooling means (37, 50, 44, 46, 54, 56) for cooling of blades are made with possibility of cooling each of blades (81, 82, 83, 84) by means of passage of cooling air through them and with possibility of differential cooling of central blade or each central blade (82, 83) at least relative to first end blade (81, 84). Cooling facilities (37, 50, 44, 46, 54, 56) comprise cooling holes (44, 46, 54, 56) passing through outer wall of at least one of blades. Cooling means (37, 50, 44, 46, 54, 56) comprise first cooling holes (44, 46, 54, 56) passing through outer wall (40) of first end blades (81, 84), and second cooling holes (44, 46, 54, 56) passing through outer wall (40) of the first central blade (82, 83). Total area of the second cooling holes is larger than the total area of the first cooling holes.

EFFECT: invention is aimed at reduction of mechanical loads on blades.

11 cl, 6 dwg