Fuel control for controlling helicopter rotor/turbine acceleration
US4423593A · kind A · utility
24Cited by
5References
2Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 16, 1982 |
| Grant date | Jan 3, 1984 |
| Priority date | — |
| Expiry date | Apr 16, 2002 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/022
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The difference in the speed (54, 56) of a helicopter gas engine (20), free turbine (40) from a reference speed (62, 64) generates (80) a desired acceleration signal (81). The difference (82) in actual turbine acceleration (84, 86) from desired acceleration is integrated (100) to provide an engine fuel command signal (67-73) whenever (88) the speed error signal exceeds (90) a predetermined threshold magnitude.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.