AXIAL COMPRESSOR STAGE Russian patent published in 2009 - IPC F04D27/02 

FIELD: engines and pumps.

SUBSTANCE: invention is related to compressors of gas turbine engines and makes it possible to increase efficiency and gas-dynamic stability of compressor by improvement of air circulation in cavity above rotor blade. Stage of axial compressor comprises guide and rotor (9) blades. Above rotor blades (9) in body (11) annular cavity (10) is arranged, which is connected to air-gas channel (12) of compressor by inclined slots (14) arranged in stator ring (13) and located above inlet part of rotor blades (9). Easy-wear coating (26) is arranged above remaining part of rotor blades (9) on stator ring (13). End walls (17) and (19) of slots (14) are arranged in the form of arcs (20) and (21) of circumference, which are inverted to annular cavity (10). Stator ring (13) from the side of guide blades (4) has berm (25) into compressor air-gas channel (12). Ratio of height (δ₁) of berm (25) in stator ring (13) to mounting fit (δ₂) between peripheral end of rotor blade (9) and easy wear coating (26) lies within range of 0.3...2. Ratio of height (H) of airfoil portion (28) of rotor blade (9) under back end wall (19) of slot (14) to radial height (h) of annular cavity (10) above back end wall (19) of slot (14) lies within range of 10...30.

EFFECT: higher efficiency and gas-dynamic stability of compressor by improvement of air circulation in cavity above rotor blade.

2 dwg