| 摘要 |
PURPOSE: To reduce aerodynamic loss and improve axial efficiency by forming a leading edge of a nominal section into a shape allowing airflow to be incident at separate angles such that maximum velocities of airflow flowing over a pressure surface and a suction surface are equal to each other. CONSTITUTION: An aerofoil members such as stator vanes 16 and rotor blades 18 used in an axial flow compressor 12 of a gas turbine engine 10 has an aerodynamic profile defined by a plurality of nominal sections 30 stacked in a plane normal to a longitudinal axis of the engine 10. Each of the nominal sections 30 has a pressure surface 26 and a suction surface 28. In this case, a leading edge 19 of the nominal section 30 is formed into a shape allowing airflow to be incident at separate angles such, in a proportion portion of an air flow incident on a circle 20 at a leading edge 19 at a predetermined operation speed, the maximum velocity of the leading edge circle 20 flowing over the pressure surface 26 is equal to the maximum velocity of the leading edge circle 20 flowing over the suction surface 28. |
