{
  "$type": "site.standard.document",
  "description": "A gas turbine engine (20) includes a compressor section (24), a combustor (56), and a turbine section (28). The combustor (56) has a radially outer surface that defines a diffuser chamber (112) radially outwardly of the combustor (56). The turbine section (28) has a high pressure turbine first…",
  "path": "/patents/1424289",
  "publishedAt": "2023-08-02T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D11/20",
    "RAYTHEON TECH CORP [US]"
  ],
  "textContent": "A gas turbine engine (20) includes a compressor section (24), a combustor (56), and a turbine section (28). The combustor (56) has a radially outer surface that defines a diffuser chamber (112) radially outwardly of the combustor (56). The turbine section (28) has a high pressure turbine first stage blade (118) that has an outer tip, and a blade outer air seal (126) positioned radially outwardly of the outer tip. A tap (102) for tapping air has been compressed by the compressor (56) and is passed through a heat exchanger (104). The air downstream of the heat exchanger (104) passes through at least one pipe (120) and into a manifold (122) radially outward of the blade outer air seal (126), and then passes across the blade outer air seal (126) to cool the blade outer air seal (126).",
  "title": "COOLED COOLING AIR FOR BLADE AIR SEAL THROUGH OUTER CHAMBER"
}