{
  "$type": "site.standard.document",
  "description": "Gas turbine engine (20) including a fan (28), compressor, combustion (32), and turbine sections, a fan bypass air path (38), a lubrication system (70), and a turbine active clearance control system (54). The turbine section has a rotor stage and a turbine case clearance control segment (46A). The…",
  "path": "/patents/1390135",
  "publishedAt": "2026-06-10T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F01D11/24",
    "RTX CORP [US]"
  ],
  "textContent": "Gas turbine engine (20) including a fan (28), compressor, combustion (32), and turbine sections, a fan bypass air path (38), a lubrication system (70), and a turbine active clearance control system (54). The turbine section has a rotor stage and a turbine case clearance control segment (46A). The turbine ACC system includes first (60) and second (64) valves and a heat exchanger (58). The heat exchanger may receive a first fan bypass air flow and a lubricant flow and permits heat transfer therebetween to produce a flow of conditioned air. The first valve receives conditioned air from the heat exchanger. The second valve may receive conditioned air and a second fan bypass air flow. The turbine ACC system may operate in a heating mode in which conditioned air flow, or a combination of conditioned air flow and the second fan bypass air flow is passed to the clearance control segment.",
  "title": "GAS TURBINE ENGINE WITH ADAPTIVE TURBINE CLEARANCE CONTROL SYSTEM AND METHOD"
}