Honeywell Aerospace was granted a patent for gas-turbine temperature control.

{
  "signal_id": "7a1970a6-f504-597e-8cd1-5a09ea462070",
  "signal_type": "patents-company",
  "signal_subtype": "patentGrant",
  "detected_at": "2026-09-20T17:47:05+00:00",
  "company": {
    "name": "Honeywell Aerospace",
    "domain": "honeywellaerospace.com"
  },
  "data": {
    "cpc": [
      {
        "code": "F02C 9/18"
      },
      {
        "code": "C02F 1/16"
      },
      {
        "code": "F02C 6/18"
      },
      {
        "code": "F05D 2270/303"
      }
    ],
    "tags": [
      "Intellectual Property",
      "Research & Development",
      "Award",
      "Engineering",
      "Automotive"
    ],
    "detail": "In September 2026 Honeywell Aerospace patented a bypass-air control system for managing temperatures in aircraft gas-turbine engines.",
    "summary": "Honeywell Aerospace was granted a patent for gas-turbine temperature control.",
    "event_at": "2026-09-15",
    "inventors": [
      {
        "name": "Kevin Dittmar",
        "status": "resolved",
        "is_primary": true,
        "linkedin_url": "https://www.linkedin.com/in/kevin-dittmar-035490"
      },
      {
        "name": "Eric Shepard",
        "status": "unresolved",
        "is_primary": false
      },
      {
        "name": "Jeffrey Maldonado",
        "status": "unresolved",
        "is_primary": false
      },
      {
        "name": "Matthew Dunn",
        "status": "unresolved",
        "is_primary": false
      }
    ],
    "event_kind": "grant_date",
    "grant_date": "2026-09-15",
    "source_url": "https://patents.google.com/patent/US12736011",
    "cpc_primary": {
      "code": "F02C 9/18"
    },
    "patent_title": "Distillation system temperature control system",
    "patent_number": "US12736011",
    "uspto_assignee": "Honeywell Aerospace US LLC",
    "patent_abstract": "A gas turbine engine system includes a gas turbine engine, a bypass duct, and a bypass control valve. The gas turbine engine includes at least a compressor section, a combustion section, and a turbine section. The bypass duct has a bypass duct inlet that is disposed between the compressor section and the combustion section, and a bypass duct outlet that is disposed downstream of the turbine section. The bypass control valve is disposed on the bypass duct and is moveable to a commanded valve position, which is one of a closed position, in which compressed air from the compressor section does not flow through the bypass duct, and a plurality of open positions, in which compressed air discharged from the compressor section flows through the bypass duct and mixes with exhaust gas discharged from the turbine section to form the discharge gas that is supplied to the main chamber.",
    "precision_class": "structural",
    "invention_explanation": "A controllable duct routes air around part of the engine, with a valve adjusting the bypass flow to help regulate operating temperature.",
    "technologies_mentioned": [
      "gas turbine engines",
      "bypass air systems",
      "temperature control"
    ]
  }
}

curl https://signals.autobound.ai/v1/signals/7a1970a6-f504-597e-8cd1-5a09ea462070 \
  -H "X-API-KEY: $AUTOBOUND_API_KEY"

curl -X POST https://signals.autobound.ai/v1/companies/enrich \
  -H "X-API-KEY: $AUTOBOUND_API_KEY" \
  -H "Content-Type: application/json" \
  -d '{"domain":"honeywellaerospace.com","limit":20}'