{
  "$type": "site.standard.document",
  "description": "A gas turbine engine, has: a compressor; a turbine having a rotor; and an inertial particle separator (30) located upstream of the turbine downstream of the compressor, the inertial particle separator (30) having: an intake conduit (31) in fluid flow communication with the compressor and defining…",
  "path": "/patents/1406799",
  "publishedAt": "2024-01-31T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D25/14",
    "PRATT & WHITNEY CANADA [CA]"
  ],
  "textContent": "A gas turbine engine, has: a compressor; a turbine having a rotor; and an inertial particle separator (30) located upstream of the turbine downstream of the compressor, the inertial particle separator (30) having: an intake conduit (31) in fluid flow communication with the compressor and defining an elbow (31b), a splitter (34), a leading edge of the splitter (34) located downstream of the elbow (31b), the splitter (34) located to divide a flow (F1) into a particle flow (F2) and an air flow (F3), and an inlet conduit (32) and a bypass conduit (33) located on respective opposite sides of the splitter (34), the inlet conduit (32) receiving the air flow (F3), the inlet conduit (32) in fluid flow communication with a cavity (28a) containing the rotor for cooling the rotor of the turbine section, the bypass conduit (33) receiving the particle flow (F2), the bypass conduit (33) in fluid flow communication with an environment outside the gas turbine engine while bypassing the cavity (28a) containing the rotor.",
  "title": "INERTIAL PARTICLE SEPARATOR FOR A TURBINE SECTION OF A GAS TURBINE ENGINE"
}