Aircraft engine and method for operating an aircraft engine
AssigneeRolls-Royce Deutschland Ltd & Co KG
InventorGideon Venter
Life of this patent
Estimating the term…
Abstract
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.
Claims16
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.
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.
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.
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.
Dependencies are inferred from the claim text.