The invention relates to a gas turbine, in particular an aircraft engine and to a method for generating electrical energy in a gas turbine. The gas turbine comprises at least one engine core (18), in which a shaft (19) produces a shaft output. The inventive turbine is equipped with means that generate electrical energy both from the shaft output produced by the engine core (18) and from the compressed air that is dissipated by the engine core (18).

Gas turbine, in particular aircraft engine and method for generating electrical energy in a gas turbine

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 blades (15). A stator has a housing (17) and fixed blades (18). A generator (19) has at least one stator (21) and at least one rotor (20). The electrical energy generated by the generator (19) serves, preferably serves to operate at least one add-on device or one ancillary unit of the gas turbine. According to the invention, the generator (19) is integrated inside the gas turbine in such a manner that the or each rotor (20) of the generator is assigned to the rotor and the or each stator (21) of the generator is assigned to the stator whereby enabling kinetic energy of the rotor to be converted into electrical energy by the generator (19).

Gas turbine, particularly an aircraft engine

The engine (10) has a core engine (11) with a compressor, a combustion chamber and a turbine, where the core engine is surrounded in sections over a core engine housing by a bypass channel (16) that is limited radially outside by a channel housing. A thermoelectric generator generates electrical energy from a temperature difference between hot current through the core engine and cold current through the channel. Thermocouple sections (26) are assigned to the hot core engine housing and thermocouple sections (27) are assigned to cold bypass channel housing.

Gas-turbine engine e.g. civilian aircraft engine or military aircraft engine, has thermoelectric generator generating electrical energy from temperature difference between hot current via core engine and cold current via bypass channel

A gas turbine, especially an aircraft engine is provided. The gas turbine comprises at least one compressor (15, 16), at least one combustion chamber (17), at least one turbine (18, 19), and at least one generator (20) for generating electrical energy, each generator (20) comprising at least one stator (25) and at least one rotor (22). Each rotor (22) of each generator (20) is embodied as a free-wheeling generator turbine that is driven by a gas flow in such a way that it rotates in relation to the respective stator (25) of the respective generator (20) and thus generates electrical energy from the kinetic energy of the gas flow.

Gas turbine with free-running generator driven by by-pass gas flow

Offenbart ist ein Luftfahrzeug mit zumindest einem Triebwerk 4, einem Flugwerk 16 und mindestens einem Nebenaggregat 18, 20 zur Umwandlung von mechanischer Wellenleistung des Triebwerks 4 in elektrische, hydraulische und/oder pneumatische Energie, wobei das zumindest eine Nebenaggregat 18, 20 am Flugwerk 16 befestigt und zur Versorgung mit mechanischer Wellenleistung uber mindestens eine Antriebsverbindung 26 mit dem Triebwerk 4 verbunden ist. Weiterhin offenbart ist eine Triebwerksanordnung 1 und ein Triebwerkstrager 12 fur ein derartiges Luftfahrzeug 2.

Luftfahrzeug, Triebwerksanordnung und Triebwerksträger

The turbo-fan engine has a fan rotor, a booster compressor located downstream of the fan rotor, and a drive section with a core compressor and turbine. A working turbine is connected to the fan rotor via a drive shaft. The booster compressor is formed as a precompressor stage (16), of the core compressor (9), and is removably connected to it. The fan engine (1) has two fan rotors (3, 4). These are driven via two coaxial drive shafts (5a, b) by an opposite working turbine (13). ADVANTAGE - Flexible variation of pressure ratio.

Uwe Schmidt-Eisenlohr

Papers

Booster compressor for turbo-fan engine with high by-pass ratio - is formed as precompressor stage, of core compressor, and connected to it