| 摘要 |
A turbojet double-flow engine with blades of front fan in the supports and, further, guide rotary blades in the shell of its outer cowl where in continuation of the section of the fan, with formation of a bypass channel, a hollow circular split body is placed, at that under the split body an inner channel with inlet guide blades after the fan at inlet of the compressor is formed, and the devices of control of position of the blades are connected to split body, at that the guide blades at the inlet of the compressor are connected each with hinged cylinder supports as pins with inner shell of the split body in the cavity between the holder of the fan and the guide blades. The guide blades are installed in the cowl round the split body with the inner cylindrical hinged supports as pins in the opposite outer wall. The stages of the blades, directing and guide ones, each, with the cylindrical hinged supports as pins, are additionally connected to the devices of control of position of some or others blades. |
