FIELD: manufacturing technology; engine building.
SUBSTANCE: rotor blade of aerodynamic profile (70) of compressor for turbine engine. Aerodynamic profile (70) of the compressor comprises: base section (72) spaced from apex section (100) by section (102) of main part. Section (102) of main part is formed by wall (88) of sucking surface, having suction surface (89), and wall (90) of pressure surface, having pressure surface (91). Wall (88) of suction surface and wall (90) of pressure surface intersect on front edge (76) and trailing edge (78). Apex section (100) comprises arm (104) provided on wall (90) of pressure surface. Wall (106) of apex passes from front edge (76) of aerodynamic profile to trailing edge (78) of aerodynamic profile. Adapter region (108) of wall (90) of pressure surface tapers from arm (104) towards wall (106) of apex. Wall (106) of apex comprises recess (110) formed by first wall area (112) of apex wall, which extends from trailing edge (78) to wing (114).
EFFECT: aerodynamic profile of the compressor of the present invention provides a means of controlling losses by reducing leakage at the apex.
15 cl, 8 dwg
