HIGH PRESSURE COMPRESSOR ROTOR AIR BLEEDING DEVICE Russian patent published in 2023 - IPC F04D29/32 

FIELD: mechanical engineering.

SUBSTANCE: invention relates to the design of the compressor rotor of an aircraft gas turbine engine (GTE), in particular to a rotary air bleed system for cooling the turbine from the flow path of the compressor. The device consists of air sampling pipes installed in the radial direction in a ring, made with ledges and with upper and lower bevels, the ring is located between the front impeller and the rear impeller with extraction slots. The ring is made C-shaped with round holes in the outer tier and oval holes in the inner tier, and the inner tier is made of sectors that are connected to each other by smooth transitions, and the oval holes are elongated in the circumferential direction with a ratio of the length L of the hole to the size E, equal to 2.69…2.73, and the ratio of the length L of the hole to the width H of the hole, equal to 1.34…1.38, and the ratio of the width B of the inner platform of the ring to the width H of the hole, equal to 1.7…1.8, where the sampling pipes are made with a rounding between the shelf with a diameter D, an oval plug and a rounding between the oval plug and the main body (15) of the pipe, whereas the ratio of the length L₁ of the oval plug to the size E₁ is equal to 2.69…2.73, and the ratio of the length L₁ of the oval plug to the width H₁ of the oval plug is equal to 1.34…1.37, as well as the ratio of the diameter D of the round shelf to the length L₁ of the plug is equal to 1.46…1.49, and the ratio of the bevels of the width S of the round shelf to the width H₁ of the oval plug is equal to 1.62…1.66.

EFFECT: invention makes it possible to increase the efficiency of the GTE high-pressure compressor rotor by improving its performance and increasing the overhaul period.

1 cl, 6 dwg