GAS TURBINE ENGINE LOW-PRESSURE COMPRESSOR ROTOR IMPELLER (VERSIONS) Russian patent published in 2017 - IPC F04D29/32 F01D5/06 

FIELD: engines and pumps.

SUBSTANCE: rotor shaft second-stage impeller of the gas turbine engine low-pressure compressor contains the disc comprising the hub with the central opening, the blade 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 with the disc blade with the formation of different-arm circular conical inclined flanges. The outer rim surface is made with the inclination angle of the generatrix relative to the axis of the rotor shaft, the radius of which varies monotonically in the direction of the working fluid flow with the radial extension gradient G_rim=(0.22÷0.32) [m/m]. The disc rim is provided with the system of grooves to secure the blades, uniformly spaced along the disc periphery. The longitudinal axis of each groove forms the pitch α angle of the blade butt, defined in the range of values α=(19÷27)°, with the rotor shaft axis in the axial projection of the arbitrary axial plane, normal to the blade root radial axis. The blade is formed with the pitch angle of the blade root profile, variable γ in the root height relative to the front line of the blade row profiles grate, decreasing with radial distance from the rotor axis with the gradient G_u.p.=(196.3÷282.2) [deg/m]. In addition, the blade root is made with the thickness variable in width and height of the root. The maximum thickness of the blade root profile is made the largest in the radical cross-section and decreasing in the blade root height towards the peripheral end face with the gradient G_u.t=(1.14÷1.63)⋅10^-2 [m/m].

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

19 cl, 6 dwg