Honeywell Aerospace was granted a patent for self-cooling turbine seals.

{
  "signal_id": "02eb423b-3283-5552-bbcc-0d4251699e9e",
  "signal_type": "patents-company",
  "signal_subtype": "patentGrant",
  "detected_at": "2026-09-30T17:03:49+00:00",
  "company": {
    "name": "Honeywell Aerospace",
    "domain": "honeywellaerospace.com"
  },
  "data": {
    "cpc": [
      {
        "code": "F01D 11/003"
      },
      {
        "code": "F01D 11/005"
      },
      {
        "code": "F01D 25/12"
      },
      {
        "code": "F01D 11/08"
      },
      {
        "code": "F05D 2220/32"
      }
    ],
    "tags": [
      "Intellectual Property",
      "Research & Development",
      "Automotive",
      "Engineering"
    ],
    "detail": "In September 2026 Honeywell Aerospace patented seals for managing heat and pressure inside gas turbine engines used in aircraft and other power systems.",
    "summary": "Honeywell Aerospace was granted a patent for self-cooling turbine seals.",
    "event_at": "2026-09-29",
    "inventors": [
      {
        "name": "William Weiss",
        "status": "unresolved",
        "is_primary": true
      },
      {
        "name": "Timothy Darling",
        "status": "resolved",
        "is_primary": false,
        "linkedin_url": "https://www.linkedin.com/in/tim-darling-b0930413"
      },
      {
        "name": "Harry Kington",
        "status": "unresolved",
        "is_primary": false
      },
      {
        "name": "Jason Smoke",
        "status": "resolved",
        "is_primary": false,
        "linkedin_url": "https://www.linkedin.com/in/jason-smoke-739a48224"
      }
    ],
    "event_kind": "grant_date",
    "grant_date": "2026-09-29",
    "source_url": "https://patents.google.com/patent/US12747672",
    "cpc_primary": {
      "code": "F01D 11/003"
    },
    "patent_title": "Gas turbine engines having self-cooling seals and methods of operating the same",
    "patent_number": "US12747672",
    "uspto_assignee": "Honeywell Aerospace US LLC",
    "patent_abstract": "A gas turbine engine having self-cooling seals and methods thereof are provided. The engines include a first component exposed to a high temperature environment, a second component that is not exposed the high temperature environment, and a seal between and in contact with the first and second components to separate a cavity therebetween to define a higher pressure region and a lower pressure region. The seal includes an annular body encircling a longitudinal axis of the gas turbine engine. The annular body has an S-shaped cross-section biased to apply forces against the first and second components, a first and second contact portions in contact with the first and second components, respectively, and holes extending through the annular body that provide passage for fluid flow therethrough and direct the fluid flow toward the first contact portion for cooling thereof.",
    "precision_class": "structural",
    "invention_explanation": "A ring-shaped seal that uses pressure differences within the engine to help cool itself while separating hot and cooler engine sections.",
    "technologies_mentioned": [
      "gas turbine engines",
      "self-cooling seals",
      "thermal management",
      "pressure sealing"
    ]
  }
}

curl https://signals.autobound.ai/v1/signals/02eb423b-3283-5552-bbcc-0d4251699e9e \
  -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}'