DEVICE FOR AERODYNAMIC SEALING OF CLEARANCE BETWEEN BUTT ENDS OF AXIAL-FLOW COMPRESSOR ROTOR BLADES AND TURBINE SHELL Russian patent published in 2005 - IPC

FIELD: gas-turbine engines.

SUBSTANCE: proposed device that can be used for high-pressure axial-flow compressors of aircraft turbojet engines and/or for backup stages, and/or for ground-based turbines, primarily those of power installations and gas-transfer stations has annular track wall of shell and one or more rotor blading rims; radial clearance is provided between ends of rotor blades and track wall of shell; at least one section of track wall above ends of rotor blades is provided with three annular grooves. Depth of each annular groove is found from equation R_in + Δ_max ≤ T_i ≤ D_in - Δ_max, where T_i is depth of respective annular groove; R_in is radius of inscribed circle in meridian section of annular groove; D_in is diameter of inscribed circle in meridian section of annular groove; Δ_max is maximal radial clearance between compressor rotor blade ends and shell; ratio of each annular groove width to maximal radial clearance between compressor rotor blade ends and shell equals (0.855 - 1.155) √10, where √10 is aerodynamic parameter of rotor stage and/or compressor corresponding to logarithmic scale of 5 dB.

EFFECT: enhanced compressor efficiency and gas-dynamic stability, reduced aerodynamic noise of turbojet engine fan.

1 cl, 4 dwg