{
  "$type": "site.standard.document",
  "description": "A cooling system includes: a core casing (18) configured to house a compressor (12, 13), a combustion chamber (14), and a turbine (15, 16); a tail cone (28) configured to form at least part of an exhaust passage (23) of the turbine (15, 16) together with the core casing (18); struts (27) configured…",
  "path": "/patents/1414802",
  "publishedAt": "2024-05-15T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "B64D33/08",
    "IHI CORP [JP]"
  ],
  "textContent": "A cooling system includes: a core casing (18) configured to house a compressor (12, 13), a combustion chamber (14), and a turbine (15, 16); a tail cone (28) configured to form at least part of an exhaust passage (23) of the turbine (15, 16) together with the core casing (18); struts (27) configured to connect the core casing (18) with a support body (26) of the tail cone (28); a housing (31) installed in the tail cone (28), configured to house an electrical apparatus; and at least one primary duct (40) configured to connect between an internal space of the housing (31) and an outlet passage (12a) of the compressor (12) or a discharge port of a blower (34) installed in a gas turbine engine via at least one of the struts (27) and a radial outside of the core casing (18).",
  "title": "COOLING SYSTEM FOR AIRCRAFT GAS TURBINE ENGINE"
}