HIGH-PRESSURE GAS TURBINE ENGINE COMPRESSOR Russian patent published in 2020 - IPC F04D29/60 F04D29/66 

FIELD: machine building.

SUBSTANCE: invention relates to high-pressure multistage compressors of gas turbine engines, including for aviation application. High-pressure gas turbine engine compressor comprising steps arranged in the flow part of the compressor with impellers comprising working blades, the first high-pressure stage, the low-pressure steps following it, Ratio F₁ of flow part of compressor at inlet of working blade of first high-pressure impeller to area F₂ of flow part at outlet of first high-pressure stage makes 1.6–2.2. In the flow part of the compressor, the diffusion coefficient D_L1 of the first high-pressure impeller does not exceed 0.6, the diffusion coefficient D_L2 of the second impeller does not exceed 0.55, Diffusion coefficient D_L3 with the third to eighth working blades does not exceed 0.5, the total number of stages of the compressor is equal to 8.

EFFECT: proposed invention allows increasing gas-dynamic stability, degree of increase of total pressure in compressor, reliability of high-pressure compressor of gas-turbine engine.

1 cl, 3 dwg