This invention relates to an engine synchronization method for aircraft equipped with at least two gas-turbine engines, where the respective speeds N1 of the low-pressure compressor spools of the gas-turbine engines are determined and a difference value N1 is calculated and subsequently on the basis
This invention relates to an engine synchronization method for aircraft equipped with at least two gas-turbine engines, where the respective speeds N1 of the low-pressure compressor spools of the gas-turbine engines are determined and a difference value N1 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 N2 of the high-pressure compressor spools of the gas-turbine engines being determined and a difference value N2 being calculated and subsequently on the basis of this difference value, at least on one gas-turbine engine, the inlet temperature value T20, which is fed to the engine controller, being changed for synchronization.
대표청구항▼
1. A method for synchronizing engines on an aircraft having at least two gas-turbine engines, comprising: determining respective N1 speeds of low-pressure compressor spools of the gas-turbine engines;calculating a difference value N1;subsequently calculating at least one trim value based on the diff
1. A method for synchronizing engines on an aircraft having at least two gas-turbine engines, comprising: determining respective N1 speeds of low-pressure compressor spools of the gas-turbine engines;calculating a difference value N1;subsequently calculating at least one trim value based on the difference value N1;synchronizing the N1 speeds by changing a setting on at least one of the gas-turbine engines based on the trim value;subsequently determining respective N2 speeds of high-pressure compressor spools of the gas-turbine engines;calculating a difference value N2;further synchronizing the gas-turbine engines by subsequently changing an engine air inlet temperature value T20 which is fed to an engine controller on at least one of the gas-turbine engines, based on the difference value N2. 2. The method in accordance with claim 1, and further comprising synchronizing at least one chosen from N1 speeds and N2 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 N1 speeds. 4. The method in accordance with claim 2, and further comprising changing the T20 value which is fed to the engine controller on at least one of the gas-turbine engines for synchronizing the N2 speeds. 5. The method in accordance with claim 2, and further comprising limiting a change of the T20 value to a measuring accuracy of at least one air data sensor determining the T20 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 N1. 7. The method in accordance with claim 6, and further comprising changing the T20 value which is fed to the engine controller on at least one of the gas-turbine engines for synchronizing the N2 speeds. 8. The method in accordance with claim 7, and further comprising limiting a change of the T20 value to a measuring accuracy of at least one air data sensor determining the T20 value when synchronizing the gas-turbine engines. 9. The method in accordance with claim 8, wherein the engine air inlet temperature value T20 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 N1 speeds and N2 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 N1 speeds. 12. The method in accordance with claim 10, and further comprising changing the T20 value which is fed to the engine controller on at least one of the gas-turbine engines for synchronizing the N2 speeds. 13. The method in accordance with claim 10, and further comprising limiting a change of the T20 value to a measuring accuracy of at least one air data sensor determining the T20 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 N1. 15. The method in accordance with claim 14, and further comprising changing the T20 value which is fed to the engine controller on at least one of the gas-turbine engines for synchronizing the N2 speeds. 16. The method in accordance with claim 15, and further comprising limiting a change of the T20 value to a measuring accuracy of at least one air data sensor determining the T20 value when synchronizing the gas-turbine engines. 17. The method in accordance with claim 16, wherein the engine air inlet temperature value T20 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 T20 value which is fed to the engine controller on at least one of the gas-turbine engines for synchronizing the N2 speeds. 19. The method in accordance with claim 18, and further comprising limiting a change of the T20 value to a measuring accuracy of at least one air data sensor determining the T20 value when synchronizing the gas-turbine engines. 20. The method in accordance with claim 1, and further comprising limiting a change of the T20 value to a measuring accuracy of at least one air data sensor determining the T20 value when synchronizing the gas-turbine engines.
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이 특허에 인용된 특허 (7)
Pollak Robert R. (North Palm Beach FL) Khalid Syed J. (Palm Beach Gardens FL) Marcos Juan A. (Jupiter FL), Active geometry control system for gas turbine engines.
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