{
  "$type": "site.standard.document",
  "description": "A gas turbine engine (101) includes a main compressor section (102) having a downstream most location (104), and a turbine section (108), with both the main compressor section (102) and the turbine section (108) housing rotatable components. A first tap (110) taps air compressed by the main…",
  "path": "/patents/1401842",
  "publishedAt": "2025-11-05T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02C6/08",
    "RTX CORP [US]"
  ],
  "textContent": "A gas turbine engine (101) includes a main compressor section (102) having a downstream most location (104), and a turbine section (108), with both the main compressor section (102) and the turbine section (108) housing rotatable components. A first tap (110) taps air compressed by the main compressor section (102) at an upstream location upstream of the downstream most location (104). The first tap (110) passes through a heat exchanger (112) and to a cooling compressor (114). Air downstream of the cooling compressor (114) is selectively connected to reach at least one of the rotatable components. The cooling compressor (114) is connected to rotate at a speed proportional to a rotational speed in one of the main compressor section (102) and the turbine section (108). A valve system (128,130) includes a check valve (130) for selectively blocking flow downstream of the cooling compressor (114) from reaching the at least one rotatable component. A dump valve (128) selectively dumps air downstream of the cooling compressor (114).",
  "title": "INTERCOOLED COOLING AIR WITH SELECTIVE PRESSURE DUMP"
}