{
  "$type": "site.standard.document",
  "description": "A gas turbine engine (20) includes compressor (30) and turbine (34) sections, and a turbine cooling air (TCA) system (54). The turbine section (34) has upstream (44A) and downstream (44B) rotor stages, and turbine sub-sections (47A,47B). The TCA system (54) includes a flow mixing device (70) and a…",
  "path": "/patents/1390126",
  "publishedAt": "2026-06-10T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D11/24",
    "RTX CORP [US]"
  ],
  "textContent": "A gas turbine engine (20) includes compressor (30) and turbine (34) sections, and a turbine cooling air (TCA) system (54). The turbine section (34) has upstream (44A) and downstream (44B) rotor stages, and turbine sub-sections (47A,47B). The TCA system (54) includes a flow mixing device (70) and a compressor bleed air flow valve (72), and is configured to receive first and second compressor bleed air flows. The compressor bleed air flow valve (72) may be in an open or a closed configuration. The TCA system (54) operates in a first or a second mode. In the first mode, the compressor bleed air flow valve (72) is closed and a conditioned air flow is from the first compressor bleed air flow. In the second mode, the compressor bleed air flow valve (72) is open and the conditioned air flow is a mixture of the first and second compressor bleed air flows. The conditioned air flow is directed to the downstream turbine subsection (47B).",
  "title": "GAS TURBINE ENGINE WITH ADAPTIVE TURBINE COOLING AIR SYSTEM AND METHOD"
}