Engine synchronization method
This invention relates to an engine synchronization method for aircraft equipped with at least two gas-turbine engines, where the respective speeds N 1 of the low-pressure compressor spools of the gas-turbine engines are determined and a difference value N 1 is calculated and subsequently on the basis of this difference value at least one trim value is calculated, on the basis of which, at least on one gas-turbine engine, a change of the setting is made, with subsequently the respective speeds N 2 of the high-pressure compressor spools of the gas-turbine engines being determined and a difference value N 2 being calculated and subsequently on the basis of this difference value, at least on one gas-turbine engine, the inlet temperature value T 20 , which is fed to the engine controller, being changed for synchronization.
1. A method for synchronizing engines on an aircraft having at least two gas-turbine engines, comprising:
determining respective N 1 speeds of low-pressure compressor spools of the gas-turbine engines;
calculating a difference value N 1 ;
subsequently calculating at least one trim value based on the difference value N 1 ;
synchronizing the N 1 speeds by changing a setting on at least one of the gas-turbine engines based on the trim value;
subsequently determining respective N 2 speeds of high-pressure compressor spools of the gas-turbine engines;
calculating a difference value N 2 ;
further synchronizing the gas-turbine engines by subsequently changing an engine air inlet temperature value T 20 which is fed to an engine controller on at least one of the gas-turbine engines, based on the difference value N 2 .
2. The method in accordance with claim 1 , and further comprising synchronizing at least one chosen from N 1 speeds and N 2 speeds by adjusting both gas-turbine engines.
3. The method in accordance with claim 2 , and further comprising changing at least one thrust setting value for synchronizing the N 1 speeds.
4. The method in accordance with claim 2 , and further comprising changing the T 20 value which is fed to the engine controller on at least one of the gas-turbine engines for synchronizing the N 2 speeds.
5. The method in accordance with claim 2 , and further comprising limiting a change of the T 20 value to a measuring accuracy of at least one air data sensor determining the T 20 value when synchronizing the gas-turbine engines.
6. The method in accordance with claim 3 , and further comprising changing at least one speed setting value for synchronizing the N 1 .
7. The method in accordance with claim 6 , and further comprising changing the T 20 value which is fed to the engine controller on at least one of the gas-turbine engines for synchronizing the N 2 speeds.
8. The method in accordance with claim 7 , and further comprising limiting a change of the T 20 value to a measuring accuracy of at least one air data sensor determining the T 20 value when synchronizing the gas-turbine engines.
9. The method in accordance with claim 8 , wherein the engine air inlet temperature value T 20 is also based on at least one chosen from air pressure, inflow velocity and aircraft speed.
10. The method in accordance with claim 1 , and further comprising synchronizing at least one chosen from N 1 speeds and N 2 speeds by leaving one of the gas-turbine engines, provided as a master engine, in a non-adjusted condition while adjusting another of the gas-turbine engines, selected as a slave engine.
11. The method in accordance with claim 10 , and further comprising changing at least one thrust setting value for synchronizing the N 1 speeds.
12. The method in accordance with claim 10 , and further comprising changing the T 20 value which is fed to the engine controller on at least one of the gas-turbine engines for synchronizing the N 2 speeds.
13. The method in accordance with claim 10 , and further comprising limiting a change of the T 20 value to a measuring accuracy of at least one air data sensor determining the T 20 value when synchronizing the gas-turbine engines.
14. The method in accordance with claim 11 , and further comprising changing at least one speed setting value for synchronizing the N 1 .
15. The method in accordance with claim 14 , and further comprising changing the T 20 value which is fed to the engine controller on at least one of the gas-turbine engines for synchronizing the N 2 speeds.
16. The method in accordance with claim 15 , and further comprising limiting a change of the T 20 value to a measuring accuracy of at least one air data sensor determining the T 20 value when synchronizing the gas-turbine engines.
17. The method in accordance with claim 16 , wherein the engine air inlet temperature value T 20 is also based on at least one chosen from air pressure, inflow velocity and aircraft speed.
18. The method in accordance with claim 1 , and further comprising changing the T 20 value which is fed to the engine controller on at least one of the gas-turbine engines for synchronizing the N 2 speeds.
19. The method in accordance with claim 18 , and further comprising limiting a change of the T 20 value to a measuring accuracy of at least one air data sensor determining the T 20 value when synchronizing the gas-turbine engines.
20. The method in accordance with claim 1 , and further comprising limiting a change of the T 20 value to a measuring accuracy of at least one air data sensor determining the T 20 value when synchronizing the gas-turbine engines.