Method of starting a gas turbine engine
US11162428B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 18, 2017 |
| Grant date | Nov 2, 2021 |
| Priority date | — |
| Expiry date | Aug 24, 2038 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/304
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method of starting a gas turbine engine is generally provided. The engine includes a rotor assembly including a compressor rotor and a turbine rotor each coupled to a shaft. The rotor assembly is coupled to a bearing assembly within a casing enabling rotation of the rotor assembly. The method includes determining, based on a lubricant parameter, a period of time within which a rotational speed of the rotor assembly is maintained within a bowed rotor mitigation speed range; rotating the rotor assembly for the period of time within the bowed rotor mitigation speed range; and accelerating the rotor assembly to the combustion speed to ignite a fuel-oxidizer mixture for combustion.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.