Aircraft gas turbine engine control
US5285634A · kind A · utility
9Cited by
6References
11Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 9, 1991 |
| Grant date | Feb 15, 1994 |
| Priority date | — |
| Expiry date | Dec 9, 2011 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/042
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A normal acceleration schedule limits the rate of engine acceleration A second acceleration schedule permits a higher acceleration, which causes higher thermal stress in the hot engine parts. The higher schedule is enabled only during a landing approach, thus limiting the number of such stress cycles, while achieving improved performance for the selected mode.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.