Gas turbine, particularly an aircraft engine
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Abstract
The invention relates to a gas turbine, particularly an aircraft engine. The gas turbine comprises at least one stator, at least one rotor and at least one generator (19) for generating electrical energy. A rotor has a rotor shaft (11) and rotor disks (12, 13, 14), which are driven by the rotor shaft (11) and which have rotating rotor blades (15). A stator has a housing (17) and fixed guide vanes (18). A generator (19) has at least one stator (21) and at least one rotor (20). The electrical energy generated by the generator (19) preferably serves to operate at least one attachment device or one auxiliary unit of the gas turbine. According to the invention, the generator (19) is integrated in the interior of the gas turbine in such a manner that the or each rotor (20) of the generator is allocated to the rotor and the or each stator (21) of the generator is allocated to the stator, whereby kinetic energy of the rotor is convertible into electrical energy by the generator (19).
13 Citations
24 Claims
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1-15. -15. (canceled)
- 16. Gas turbine, especially aircraft engine, with at least one turbine stator, at least one turbine rotor, and at least one generator for producing electrical energy, whereby the turbine rotor comprises a rotor shaft and rotor discs with rotating rotor blades driven by the rotor shaft, whereby the turbine stator comprises a housing and stationary guide vanes, whereby the-generator comprises at least one generator stator and at least one generator rotor, and whereby the generator is integrated into the interior of the gas turbine in such a manner that the or each generator rotor is allocated to the turbine rotor and so that the or each generator stator is allocated to the turbine stator, whereby kinetic energy of the turbine rotor is convertible into electrical energy by the generator, characterized in that the or each generator rotor is allocated to the rotor blades of the turbine rotor, whereby pole pieces are integrated into the rotor blades or are allocated to the radially outwardly positioned ends of the rotor blades.
Specification