{
  "$type": "site.standard.document",
  "description": "Embodiments of a gas turbine engine cooling system (100) for deployment within a gas turbine engine (18) are provided, as are embodiment of a method for producing the same. In one embodiment, the gas turbine engine cooling system (100) includes an impeller (36) having a hub (52), a plurality of hub…",
  "path": "/patents/984966",
  "publishedAt": "2013-04-24T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D5/045",
    "HONEYWELL INT INC [US]"
  ],
  "textContent": "Embodiments of a gas turbine engine cooling system (100) for deployment within a gas turbine engine (18) are provided, as are embodiment of a method for producing the same. In one embodiment, the gas turbine engine cooling system (100) includes an impeller (36) having a hub (52), a plurality of hub bleed air passages (102), and a central bleed air conduit (104). Each hub bleed air passage (102) has an inlet (106) and an outlet (108) formed in outer and inner circumferential surfaces of the hub (52), respectively. The central bleed air conduit (104) is fluidly coupled to the outlets (108) of the plurality of hub bleed air passages (102) and is configured to conduct bleed air discharged by the plurality of hub bleed air passages (102) to a section of the gas turbine engine (18) downstream of the impeller (36) to provide cooling air thereto.",
  "title": "Gas turbine engine cooling systems having hub-bleed impellers"
}