{
  "$type": "site.standard.document",
  "description": "A precooler (20) for an aircraft engine system includes a precooler core (38) and a precooler inlet (28) to direct a compressor bleed flow (18) into the precooler core (38) to cool the compressor bleed flow (18). The precooler (20) further includes a precooler outlet (30) to direct the compressor…",
  "path": "/patents/969002",
  "publishedAt": "2014-10-08T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "B64D13/08",
    "HAMILTON SUNDSTRAND CORP [US]"
  ],
  "textContent": "A precooler (20) for an aircraft engine system includes a precooler core (38) and a precooler inlet (28) to direct a compressor bleed flow (18) into the precooler core (38) to cool the compressor bleed flow (18). The precooler (20) further includes a precooler outlet (30) to direct the compressor bleed flow (18) from the precooler (20) to a selected component of the aircraft engine system and a precooler bleed port (42) through which a portion of the compressor bleed flow (18) is diverted to a secondary component of the aircraft engine system. The precooler bleed port (42) is oriented such that flow entering the precooler bleed port (42) must substantially reverse direction from a direction of the compressor bleed flow (18) through the precooler (20).",
  "title": "Precooler for an aircraft engine with a contamination free reverse flow bleed port"
}