| 摘要 |
<P>PROBLEM TO BE SOLVED: To execute efficient bleeding in a low-rotaion area and stop bleeding so that an effect on compressing performance is reduced in a constant rotation area in bleeding structure which is provided between a front stage compressor and a rear stage compressor in a multi-stage compressor for a gas turbine engine. <P>SOLUTION: The gas turbine engine having the multi-stage compressor includes: the a bleed valve structure including a shroud slope that is inclined in a direction in which compressed air flows and that forms one wall of an annular bleed hole at the front end of the shroud of the rear stage compressor, and a slope that is movable in the longitudinal direction along in the direction in which the compressed air flows and has the same angle as the shroud slope, and that forms the other wall of the bleed hole at the rear end of the shroud of the front stage compressor, and an annular bleed valve for closing the bleed hole in a position where the slope contacts with the shroud slope. <P>COPYRIGHT: (C)2013,JPO&INPIT |
