Fuel control system for gas turbine engine
US5076048A · kind A · utility
3Cited by
4References
6Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Nov 7, 1990 |
| Grant date | Dec 31, 1991 |
| Priority date | — |
| Expiry date | Nov 7, 2010 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C9/32
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The throttle fuel flow of an aircraft jet engine is controlled by measuring the actual value of an engine parameter demand and measuring the error between the actual value and a value of the parameter demand calculated from a number of engine operating data. The error is then used to drive an integrating fuel throttle value until the error is substantially zero. The engine parameter chosen is the high pressure compressor delivery mach number.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.