COOLED TURBINE OF GAS TURBINE ENGINE Russian patent published in 2021 - IPC F01D5/08 F01D25/12 F01D11/08 F02C7/18 

FIELD: engine building.

SUBSTANCE: invention relates to the field of aircraft engine building, namely, to cooled turbines for gas turbine units. In a cooled GTE turbine containing an external body with a distributing collector and nozzle blades with external shrouds installed in the external body, an impeller with rotor blades, each whereof is equipped with a shroud with a front and a rear teeth, above-rotor inserts installed in the external body in the area above the rotor blades, forming a first annular cavity between the external body and the above-rotor inserts and contacting with sections of the inner surfaces thereof with sections of the outer surfaces of the outer shrouds of the nozzle blades, wherein a protrusion is made at the ends of each above-rotor insert facing the outer shrouds of the nozzle blades, wherein a split elastic ring is installed above said protrusions in an annular groove made in the external body, moreover, between the outer surfaces of the shrouds with teeth, the inner surfaces of the above-rotor inserts and the ends of the outer shrouds of the nozzle blades, a second annular cavity is formed, according to the present invention for of a double-circuit gas turbine engine, a third annular cavity is made between the outer shrouds of the nozzle blades and the above-rotor inserts under said axial protrusions of the above-rotor inserts, and a fourth annular cavity is made between the external body and the outer shrouds of the nozzle blades, communicated with the distributing collector by means of channels made in the external body and with the second annular cavity by means of channels made in the outer shrouds of the nozzle blades, wherein a screen is installed in the first annular cavity, dividing said cavity into a fifth and a sixth annular cavities, wherein the fifth annular cavity is communicated with the flow part of the second circuit of the gas turbine engine by means of channels made in the external body, and with the second annular cavity by means of channels made in the above-rotor inserts and directed to the area behind the rear teeth of the shrouds, and the sixth annular cavity is communicated with the fourth annular cavity via sequentially communicated channels made in the above-rotor inserts, the third annular cavity and additional channels made in the outer shrouds of the nozzle blades, and with the second annular cavity by means of additional channels made in the above-rotor inserts and directed to the area between the front and rear teeth of the shrouds.

EFFECT: increased efficiency of cooling of the entire surface of the impeller blade shrouds and, thus, an increase in the reliability and operating life of the GTE turbine impeller as a whole, are achieved.

3 cl, 2 dwg