Gas turbine engine rotor lock prevention system and method
US7902999B2 · kind B2 · utility
1Cited by
18References
20Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Apr 18, 2008 |
| Grant date | Mar 8, 2011 |
| Priority date | — |
| Expiry date | Oct 9, 2029 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/092
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A system and method of at least reducing the likelihood of a rotor lock in an aircraft gas turbine engine is provided. A determination is made that each propulsion gas turbine engine on an aircraft has experienced a flameout. The rotational speed of each propulsion gas turbine engine is compared to a predetermined threshold rotational speed and, if the rotational speed of each propulsion gas turbine engine is below the predetermined threshold rotational speed, a warning is supplied to a flight crew.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.