TURBOJET LOW-PRESSURE COMPRESSOR ROTOR FOURTH-STAGE IMPELLER Russian patent published in 2017 - IPC F04D29/32 F01D5/06 

FIELD: engines and pumps.

SUBSTANCE: turbojet low-pressure compressor rotor shaft fourth-stage impeller contains the disc comprising the hub with a central bore, the web and the rim, as well as the blades, each having a butt and a root with a profile formed by a concave trough and a convex back. The disc rim is connected to the web with the formation of annular flanges separated along the rim periphery by the annular groove for disposing the impeller blade butts. The hub is made symmetrically developed relative to the middle arbitrary web plane normal to the rotor shaft axis, with the axial width exceeding 5.5÷7.3 times the root web portion thickness. The blade is made with the γ root profile pitch angle, variable in the root height with respect to the front line of the blade row profiles grate, decreasing with the radial distance from the rotor axis with the gradient G_p.a.=152.3÷218.9 [deg/m]. The blade root is made with the thickness variable in the blade root width and height, defined in cross-section as the difference between the back and trough heights relative to the chord connecting the inlet and the outlet edges of the blade root.

EFFECT: higher efficiency and increased gasodynamic stability reserve in all operation modes of the compressor, and longer life of the low-pressure compressor last fourth stage impeller without increase in material input.

10 cl, 4 dwg