{
  "$type": "site.standard.document",
  "description": "A bleed valve module (144;244) for mounting to a support structure (31) within an aircraft includes a pipe (152;252), a plurality of bleed valves (156a-156c; 256a-256c) connected to the pipe, a plurality of pneumatic actuators (158a-158c; 258a-258c) connected to the plurality of bleed valves, and a…",
  "path": "/patents/1000216",
  "publishedAt": "2012-07-18T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "B64D13/08",
    "HAMILTON SUNDSTRAND CORP [US]"
  ],
  "textContent": "A bleed valve module (144;244) for mounting to a support structure (31) within an aircraft includes a pipe (152;252), a plurality of bleed valves (156a-156c; 256a-256c) connected to the pipe, a plurality of pneumatic actuators (158a-158c; 258a-258c) connected to the plurality of bleed valves, and a vibration isolating element (154;254). The pipe contains a flow of bleed air and includes a plurality of inlets (160a,160b; 260a,260b) and an outlet (160c;260c). The plurality of bleed valves (156a-156c; 256a-256c) controls the flow of bleed air in the pipe. The plurality of pneumatic actuators (158a-158c; 258a-258c) actuate the plurality of bleed valves. The vibration isolating element (154;254) connects the bleed valve module (144;244), to the support structure (31) within the aircraft and isolates the bleed valve module from vibration.",
  "title": "Bleed valve module"
}