Pressure-ratio control of gas turbine engine
US5305599A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Apr 10, 1991 |
| Grant date | Apr 26, 1994 |
| Priority date | — |
| Expiry date | Apr 10, 2011 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K1/15
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Control of a gas turbine engine, suitable for powering an aircraft, is accomplished by varying outlet nozzle cross section and/or a mixing of bypass air with exhaust gas at an inlet to the nozzle. The engine includes a core engine having a combustion chamber and high and low pressure turbines followed by an exhaust plenum. High and low pressure compressors driven by the turbine assembly direct air into the combustion chamber and into a bypass duct. The bypass duct extends from an outlet of the low pressure compressor. Pressure of fluid (air or exhaust) is measured at an inlet to the high pressure compressor, in the bypass duct, and in the exhaust plenum. Ratios of the pressure of the duct pressure or of the pressure at the inlet of the high-pressure compressor, to the plenum pressure are employed in a feedback loop for control of nozzle size, and also of mixing valve position in an alternate embodiment of the invention. The feedback loop includes computation of a desired pressure ratio based on desired power and inlet temperature to the low-pressure compressor.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.