Aircraft engine and method for operating an aircraft engine
An aircraft engine includes at least one electrical apparatus, which can be driven by a driveshaft in order to generate electrical energy. A hydrodynamic torque converter, with guide blades, which can be adjusted via a mechanism, is arranged between the driveshaft and the electrical apparatus. The guide blades are adjusted as a function of a rotational speed of the driveshaft, wherein the rotational speed of a shaft of the electrical apparatus operated as a generator can be adjusted, essentially within a predefined rotational speed range, via the adjustment of the guide blades.
1. An aircraft engine comprising:
a driveshaft;
an electrical apparatus, driven by the driveshaft, to generate electrical energy,
a hydrodynamic torque converter with adjustable guide blades arranged between the driveshaft and the electrical apparatus;
an adjustment mechanism for adjusting a position of the guide blades;
a coupling mechanism arranged between the driveshaft and a shaft of the electrical apparatus, via which a drive torque generated by the electrical apparatus when operated as a motor can be supplied in a direction of the driveshaft;
wherein the coupling mechanism includes a switch element, via which the hydrodynamic torque converter can be bypassed during a starting sequence performed by the drive torque generated by the electrical apparatus.
2. The aircraft engine in accordance with claim 1 , wherein the electrical apparatus can be driven via an accessory generator with a drive train providing the torque.
3. The aircraft engine in accordance with claim 1 , and further comprising:
a transmission mechanism having an output shaft,
wherein the hydrodynamic torque converter further includes an impeller,
wherein the transmission mechanism is arranged between the driveshaft and the impeller,
wherein the impeller is connected to the output shaft.
4. The aircraft engine in accordance with claim 3 , wherein the hydrodynamic torque converter includes a turbine wheel and the turbine wheel is in operative connection with the shaft of the electrical apparatus.
5. The aircraft engine in accordance with claim 3 , wherein an oil circulation of the hydrodynamic torque converter is operatively connected to an oil circulation of the electrical apparatus.
6. The aircraft engine in accordance with claim 1 , wherein the switch element of the coupling mechanism is a freewheel arranged between the shaft of the electrical apparatus and the impeller, which connects the shaft and the impeller torque-proof to one another when there is a positive rotational speed difference between a rotational speed of the shaft of the electrical apparatus and a rotational speed of the impeller, while the shaft and the impeller in an area of the freewheel are decoupled from one another when there is a negative rotational speed difference.
7. The aircraft engine in accordance with claim 6 , wherein an oil circulation of the hydrodynamic torque converter is operatively connected to an oil circulation of the electrical apparatus.
8. The aircraft engine in accordance with claim 1 , wherein the switch element of the coupling mechanism is a torque converter lock-up clutch.
9. The aircraft engine in accordance with claim 1 , wherein an oil circulation of the hydrodynamic torque converter is connected to an oil circulation of the aircraft engine.
10. The aircraft engine in accordance with claim 1 , wherein an oil circulation of the hydrodynamic torque converter is operatively connected to an oil circulation of the electrical apparatus.
11. A method of operating an aircraft engine, comprising:
providing an aircraft engine comprising:
a driveshaft;
an electrical apparatus including a shaft, driven by the driveshaft, to generate electrical energy,
a hydrodynamic torque converter with adjustable guide blades arranged between the driveshaft and the shaft of the electrical apparatus,
an adjustment mechanism for adjusting a position of the guide blades,
adjusting the guide blades as a function of a rotational speed of the driveshaft, and
adjusting a rotational speed of the shaft of the electrical apparatus when operated as a generator within a predefined rotational speed range via the adjusting of the guide blades.
12. The method in accordance with claim 11 , and further comprising adjusting the guide blades to comply with a constant rotational speed of the shaft of the electrical apparatus operated as a generator as a function of an effective rotational speed of the driveshaft.
13. The method in accordance with claim 12 , and further comprising reducing the rotational speed of the driveshaft in an area between the driveshaft and the torque converter to a level of rotational speed at which the hydrodynamic torque converter and the electrical apparatus can be operated with a high level of efficiency.
14. The method in accordance with claim 11 , and further comprising reducing the rotational speed of the driveshaft in an area between the driveshaft and the torque converter to a level of rotational speed at which the hydrodynamic torque converter and the electrical apparatus can be operated with a high level of efficiency.
15. An aircraft engine comprising:
a driveshaft;
an electrical apparatus, driven by the driveshaft, to generate electrical energy,
a hydrodynamic torque converter with adjustable guide blades arranged between the driveshaft and the electrical apparatus;
an adjustment mechanism for adjusting a position of the guide blades;
wherein an oil circulation of the hydrodynamic torque converter is connected to an oil circulation of the aircraft engine.
16. An aircraft engine comprising:
a driveshaft;
an electrical apparatus, driven by the driveshaft, to generate electrical energy,
a hydrodynamic torque converter with adjustable guide blades arranged between the driveshaft and the electrical apparatus;
an adjustment mechanism for adjusting a position of the guide blades;
wherein an oil circulation of the hydrodynamic torque converter is operatively connected to an oil circulation of the electrical apparatus.