{"schema_version":"1.0","canonical_url":"https://patentable.app/patents/US-10539079","patent":{"patent_number":"US-10539079","title":"Bowed rotor start mitigation in a gas turbine engine using aircraft-derived parameters","assignee":null,"inventors":[],"filing_date":"2016-02-12T00:00:00.000Z","publication_date":"2020-01-21T00:00:00.000Z","cpc_codes":["G05B"],"num_claims":20,"abstract":"A bowed rotor start mitigation system for a gas turbine engine of an aircraft is provided. The bowed rotor start mitigation system includes a motoring system and a controller coupled to the motoring system and an aircraft communication bus. The controller is configured to determine at least one inferred engine operating thermal parameter from at least one aircraft-based parameter received on the aircraft communication bus. The motoring system is controlled to drive rotation of a starting spool of the gas turbine engine below an engine idle speed based on determining that the at least one inferred engine operating thermal parameter is within a preselected threshold."},"analysis":{"summary":null,"layman_explanation":null,"technical_analysis":null,"business_analysis":null,"faqs":null,"topics":[],"tech_cluster":null},"seo":{"title":"Bowed rotor start mitigation in a gas turbine engine using aircraft-derived parameters","description":"A bowed rotor start mitigation system for a gas turbine engine of an aircraft is provided. The bowed rotor start mitigation system includes a motoring system and a controller coupled to the motoring s","keywords":[]},"attribution":{"source":"Patentable","source_url":"https://patentable.app","canonical_url":"https://patentable.app/patents/US-10539079","license":"CC-BY-4.0-like","license_terms":"AI-generated analysis on this page (summary, layman_explanation, technical_analysis, business_analysis, faqs) may be reused with attribution and a visible link back to the canonical URL above. Patent abstracts, claims, and bibliographic data are USPTO public domain.","required_link":"https://patentable.app/patents/US-10539079","citation_suggestion":"Patentable. \"Bowed rotor start mitigation in a gas turbine engine using aircraft-derived parameters\" (US-10539079). https://patentable.app/patents/US-10539079","copyright_holder":"Nomic Interactive Technology LLC"},"links":{"html":"https://patentable.app/patents/US-10539079","json":"https://patentable.app/api/llm-context/US-10539079","site":"https://patentable.app","llms_txt":"https://patentable.app/llms.txt"},"generated_at":"2026-05-30T23:03:32.353Z"}