GAS TURBINE COMPRESSOR ROTOR Russian patent published in 2023 - IPC F04D29/32 F01D5/08 

FIELD: gas turbine engines for aircraft and ground applications.

SUBSTANCE: invention relates to a rotary air bleed system for cooling the turbine from the flow path of the compressor. A gas turbine engine compressor rotor comprising impellers and an air bleed system for cooling the turbine from the compressor flow path, which includes air bleed windows and an annular air bleed cavity connected to the compressor flow path through an annular slot between the front and rear impellers and located in front of those located between the bolts fastening of impellers with air sampling windows. The shape of the annular cavity is, in cross section of the cavity, a shape similar to a triangle, without an annular cantilever protrusion on the rear impeller. The ratio of the height H of the annular cavity from the flow path to the width of the annular slot L is 1.5…5.5, and the ratio of the area of the conical surface in front of the air intake windows of the rear impeller F1 to the area of the air intake windows F2 is 1.5… 4.5.

EFFECT: invention makes it possible to reduce vibration stresses on compressor blades, eliminate their breakdowns, as well as reduce pulsations and losses in the air intake system for turbine cooling from the compressor flow path, increase compressor stability, which increases engine life and reliability.

1 cl, 3 dwg