| 摘要 |
<p>1,119,479. Axial-flow compressors; gas turbine plant; compressor blades. GENERAL ELECTRIC CO. Nov. 16, 1966 [Feb.21, 1966], No.51289/66. Headings F1C, F1G and F1T. In a multi-stage axial-flow compressor, e.g. for aircraft gas turbine power plants, at least some of the stator vanes in at least one stage are hollow and have, in their pressure faces, substantially rectangular air bleed openings 26, Fig. 1, adjacent the rotor hub 20. Air bled through the openings passes through a collecting manifold to a point of use, e.g. cabin pressurization, air conditioning or anti-icing. The openings may be tall and narrow, but preferably are as shown so as to communicate with the region of the main flow passage which contains the cleanest air due to centrifugal effects on entrained dirt, oil and foreign particles. The cross-sectional area of each opening is at least equal to the minimum aerofoil cross-sectional area. The hollow vanes are of sheet metal and are strengthened by an internal corrugated member (34), Fig. 3 (not shown), forming passages for the bled air.</p> |
