Control of a gas turbine engine
An engine that has, in axial flow series, booster compressor, core compressor, combustion equipment, core turbine, and low-pressure turbine. Core turbine drives core compressor via an interconnecting high-pressure shaft. Low-pressure turbine drives booster compressor via an interconnecting low-pressure shaft. Low-pressure turbine also drives external load having a defined speed characteristic that dictates speed of the low-pressure turbine and booster compressor. Booster compressor has one or more rows of variable stator vanes. The method includes: scheduling variation in the angle of variable stator vanes as a function of speed of the booster compressor wherein the vanes open as booster compressor speed increases; measuring or setting one or more operational parameters which are determinative of temperature at entry to core turbine; and biasing scheduling of angle variation of variable stator vanes as a function of operational parameter(s) to reduce variation in temperature at entry to core turbine.
1. A method of controlling a gas turbine engine having in axial flow series, a booster compressor, a core compressor, combustion equipment, a core turbine, and a low-pressure turbine, the core turbine driving the core compressor via an interconnecting high-pressure shaft, the low-pressure turbine driving the booster compressor via an interconnecting low pressure shaft, and the low-pressure turbine also driving an external load having a defined speed characteristic that dictates the speed of the low-pressure turbine and the booster compressor, the booster compressor having one or more rows of variable stator vanes, wherein the method includes:
scheduling variation in the angle of the variable stator vanes as a function of the speed of the booster compressor such that the vanes open as the booster compressor speed increases;
measuring one or more operational parameters that are determinative of the temperature at an entry to the core turbine; and
biasing the scheduling of the angle variation of the variable stator vanes as a function of the one or more operational parameters to reduce variation in temperature at the entry to the core turbine.
2. The method according to claim 1 , wherein the variation in the angle of the variable stator vanes is scheduled as a function of N/√T, where N is the booster compressor speed and T is the temperature of the inlet air to the fan or the temperature of the inlet air to the booster compressor.
3. The method according to claim 1 , wherein the one or more operational parameters include a power demand parameter setting the power output of the engine, and an air temperature measured at a position upstream of the combustion equipment.
4. The method according to claim 1 , wherein the one or more operational parameters include a measure of the temperature at an entry to the low-pressure turbine.
5. The method according to claim 4 , wherein the one or more operational parameters further include a measure of the temperature of the air exiting the core compressor.
6. The method according to claim 5 , further including calculating an error between the measured temperature at the entry to the core turbine and a desired temperature at the entry to the core turbine, the scheduling of the angle variation of the variable stator vanes being biased as a function of the calculated error.
7. The method according to claim 1 , wherein the engine further has a cooled cooling air system that cools a flow of cooling air extracted from the core compressor and that is used to cool the combustion equipment and/or the core turbine, the method further including varying the amount of cooling performed by the cooled cooling air system to compensate for variation in the temperature of the flow of cooling air extracted from the core compressor.
8. The method according to claim 1 , wherein the gas turbine engine is a turbofan, and the external load is a propulsive fan.
9. The method according to claim 8 , wherein the turbofan is a geared turbofan, the propulsive fan being operatively connected to the low-pressure shaft via a gearbox.
10. The method according to claim 1 , wherein the gas turbine engine is a static power generating engine, the external load being an electricity generator.
11. A control system for controlling a gas turbine engine having in axial flow series a booster compressor, a core compressor, combustion equipment, a core turbine, and a low-pressure turbine, the core turbine driving the core compressor via an interconnecting high-pressure shaft, the low-pressure turbine driving the booster compressor via an interconnecting low pressure shaft, and the low-pressure turbine also driving an external load having a defined speed characteristic that dictates the speed of the low-pressure turbine and booster compressor, the booster compressor having one or more rows of variable stator vanes, wherein the control system is configured to perform the method of claim 1 .
12. A gas turbine engine having in axial flow series, a booster compressor, a core compressor, combustion equipment, a core turbine, and a low-pressure turbine, the core turbine driving the core compressor via an interconnecting high-pressure shaft, the low-pressure turbine driving the booster compressor via an interconnecting low pressure shaft, and the low-pressure turbine also driving an external load having a defined speed characteristic that dictates the speed of the low-pressure turbine and booster compressor, wherein the engine further has the control system of claim 11 .
13. A computer program comprising code which, when run on a computer, causes the computer to perform the method of claim 1 .
14. A computer readable medium storing a computer program comprising code which, when run on a computer, causes the computer to perform the method of claim 1 .