Gas-turbine engine control
US4344141A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Jun 24, 1980 |
| Grant date | Aug 10, 1982 |
| Priority date | — |
| Expiry date | Jun 24, 2000 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/04
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A control system for an aircraft gas-turbine engine has positive and negative acceleration control units. Each control unit has a memory storing values of the maximum or minimum desired rate of change of fuel flow at different speeds beyond which surge or extinction will occur. The control units produce output signals, in accordance with the engine speed and acceleration, for controlling fuel flow so that it follows closely within the surge or extinction curves. The system also has amplitude gates that pass one or the other of these output signals to the engine if the speed of engine demanded by the pilot is such as to cause surge or extinction.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.