| 摘要 |
1,139,472. Gas turbine plant; axial flow compressors. GENERAL ELECTRIC CO. Nov. 21, 1966 [Feb. 1, 1966], No.51958/66. Headings F1C and F1G. [Also in Division B1] A gas turbine engine has at the inlet to the compressor a separator for removing extraneous matter from the airflow comprising an elastic diaphragm 42 inflatable into an extended position, shown, in which it deflects the matter away from the compressor inlet guide vanes 61 into an annular slot 35 leading to a collection chamber (55), Fig. 1 (not shown), from which it is drawn off to atmosphere by an extraction pump (57). In the deflated condition, Fig. 2 (not shown), diaphragm 42 is substantially contiguous with its cylindrical support 40 and a second elastic diaphragm 80 is inflated to close off slot 35 and form a smooth flow path with walls 30 and 31. Inflation and deflation of the individual diaphragms may be controlled independently or by a single system. Some extraneous matter is also collected in cavity 43 within support 40 from which it may be drawn off through pipe 60 by an extraction pump. Electric heating elements may be embedded in the diaphragms for de-icing. |
