Method and apparatus for controlling thrust in a gas turbine engine
US4275557A · kind A · utility
40Cited by
8References
12Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jan 25, 1978 |
| Grant date | Jun 30, 1981 |
| Priority date | — |
| Expiry date | Jan 25, 1998 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Gas turbine engine thrust is controlled by automatically adjusting compressor rotational speed with novel functions of engine inlet temperature to hold thrust to rated values for varying engine inlet temperature conditions. Furthermore, compressor rotational speed is automatically adjusted as a function of inlet pressure to provide a thrust rating schedule which varies with altitude. Compressor corrected rotational speed is limited through a novel function of engine inlet temerature to protect against turbine overtemperature when the engine inlet temperature exceeds the flat thrust rating point.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.