公开(公告)号：US6112523A

公开(公告)日：2000-09-05

申请号：US299629

申请日：1999-04-27

申请人： Keisuke Kamo ,  Iwao Murata ,  Tatsuya Itonaga ,  Akira Yagawa ,  Masaru Kurihara

发明人： Keisuke Kamo ,  Iwao Murata ,  Tatsuya Itonaga ,  Akira Yagawa ,  Masaru Kurihara

IPC分类号： F02B37/013 ,  F02B37/16 ,  F02B37/18 ,  F02B33/44

CPC分类号： F02B37/16 ,  F02B37/013 ,  F02B37/18 ,  Y02T10/144

摘要： A multistage supercharging system for a reciprocating engine, which is suitable for use in an aircraft capable of flying at high altitude, includes plural stage turbochargers connected in series to each other. A control unit controls operation of these turbochargers. The turbocharger at each stage includes a turbine side bypass passage bypassing the turbine, a compressor side bypass passage bypassing the compressor, a wastegate valve for controlling the flow rate of exhaust flowing through the turbine side bypass passage, a bleed valve for controlling the flow rate of intake air flowing through the compressor side bypass passage, and a pressure sensor disposed at the downstream side of the compressor. The control unit receives a signal from the pressure sensor, and controls the respective valves to selectively operate the turbochargers.

摘要翻译： 适用于能够在高空飞行的飞机的往复式发动机的多级增压系统包括彼此串联连接的多级涡轮增压器。 控制单元控制这些涡轮增压器的运行。 涡轮增压器在每个阶段包括绕过涡轮机的涡轮旁路通道，旁通压缩机的压缩机侧旁通通道，用于控制流经涡轮机旁通通道的排气流量的废气门阀，用于控制流量的排气阀 通过压缩机侧旁路通路的吸入空气和设置在压缩机的下游侧的压力传感器。 控制单元接收来自压力传感器的信号，并且控制各阀选择性地操作涡轮增压器。