Method and device to avoid turbo instability in a gas turbine engine
US8313280B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Oct 12, 2006 |
| Grant date | Nov 20, 2012 |
| Priority date | — |
| Expiry date | Oct 5, 2028 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/304
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
(A1) A turbofan engine control system is provided for managing a fan operating line. The engine (10) includes a spool having a turbine housed in a core nacelle (12). A turbofan (20) is coupled to the spool (14). A fan nacelle (34) surrounds the turbofan and core nacelle and provides a bypass flow path having a nozzle exit area (40). A controller (50) is programmed to effectively change the nozzle exit area in response to an undesired turbofan stability margin which may result in a stall or flutter condition. In one example, the physical nozzle exit area is increased at the undesired stability condition in which the airflow into the engine creates a destabilizing pressure gradient at the inlet side of the turbofan. A turbofan pressure ratio, turbofan pressure gradient, low spool speed and throttle position are monitored to determine the undesired turbofan stability margin.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.