| 摘要 |
<p>When a gas turbine is operated with inlet guide vanes (IGVs) closed during part load operation or the like, the degradation of aerodynamic performance and of reliability may potentially occur since the load on rear stage side vanes of a compressor increases. An object of the present invention is to suppress the degradation of the aerodynamic performance and of reliability of an axial compressor.
The axial compressor 1 includes a rotor 22; a plurality of rotor blade rows 31, 32 installed on the rotor 22; a casing 21 located outside of the rotor blade rows 31, 32; a plurality of stator vane rows 34, 35 installed on the casing 21; and exit guide vanes 36, 37 installed on the downstream side of a final stage stator vane row 35 among the stator vane rows 34, 35. An incidence angle of a flow toward the final stage stator vane row 35 is equal to or below a limit line of an incidence operating range 42.</p> |
