Patent Application
20230021361
The present invention relates to the field of turbomachines, such as an aircraft turbojet engine or turboprop, and in particular auxiliary power units called, whose acronym is APU.
By auxiliary power units, it should be understood turbogenerators capable of producing electrical or also pneumatic energy on board the aircraft, by driving, inter alia, electric generators.
In general, APUs are used to supply electrical or pneumatic energy to different systems when the aircraft is on the ground or in flight. For example, an APU used only in a turbogenerator mode will exclusively output electrical energy to contribute to the power supply of the hybrid propulsion drive of an aircraft.
In general, APUs are positioned at the rear of the aircraft, in particular in the tail cone, and supplied with kerosene from the tanks of the aircraft.
Typically, a gas turbine type APU comprises a gas generator in which all available mechanical power is converted into electrical energy, an air compressor mounted on the main shaft of the gas generator and configured to supply the necessary pneumatic power to the aircraft. An APU further comprises an accessory box, known as an “accessory gearbox”, whose acronym is AGB, containing a gear train mechanism connected to different pieces of equipment or accessories, such as, for example, the electric generator, the fuel pumps, the lubrication unit, the starter, or other auxiliary accessories of the engine and of the power generation of the aircraft. The APU also comprises a generator to supply electrical power on board the aircraft.
Auxiliary power units could also provide pneumatic or mechanical energy according to specific needs.
It is known to position the accessory gearbox between the electric generator and the gas generator.
Nonetheless, the area interposed between the electric generator and the gas generator is difficult to exploit. In addition, such a solution requires an accessory gearbox with large dimensions.
Moreover, upon the passage of the motor shaft throughout the accessory gearbox to drive the electric generator, said electric generator could become centred on the axis of the gas generator, which then limits the space available for the accessories.
Reference may be made to the document U.S. Pat. No. 5,309,708 which describes an electric generator connected to a gas generator via an accessory gearbox.
Hence, there is a need to optimise, in terms of bulk, the integration of an accessory gearbox in an axillary power unit.
Hence, the present invention aims to overcome the drawbacks of the aforementioned auxiliary power units and to provide a compact auxiliary power unit having reduced lateral bulk.
Hence, an object of the invention is an auxiliary power unit, in particular for an aircraft, comprising a gas generator and an electric generator including an input shaft connected to an output shaft of the gas generator.
The auxiliary power unit comprises an accessory gearbox directly connected to a rotor shaft of the electric generator, the electric generator being mounted or interposed between the gas generator and said accessory gearbox.
In other words, the gas generator is directly coupled with the electric generator, without any intermediate element.
The positioning of the accessory gearbox allows limiting the radial bulk of the auxiliary power unit. Indeed, it is no longer necessary to offset the accessories.
According to an advantageous embodiment, the accessory gearbox comprises a casing.
For example, the casing is substantially disk-like shaped with a diameter smaller than or equal to the diameter of the electric generator.
According to one embodiment, the accessory gearbox comprises a central pinion mounted in the casing and coupled to the shaft of the rotor of the electric generator.
For example, the shaft of the central pinion is fitted onto the rotor shaft of the electric generator.
According to one embodiment, the accessory gearbox comprises at least two reduction mechanisms each coupled to the central pinion and to a drive shaft for the rotational drive of a corresponding accessory.
It should be noted that the present invention is not limited to the structure of the accessory gearbox.
For example, the accessory gearbox is made by machining a metal part.
According to one embodiment, the gas generator comprises a gas turbine and a main air compressor driven in rotation by said gas turbine.
The gas generator may comprise a load compressor mounted axially between the main air compressor and the electric generator.
For example, the input shaft of the electric generator is coaxial with the output shaft of the gas generator and secured in rotation with it.
In the case where the gas generator is devoid of any load compressor, the input shaft of the electric generator is directly connected to the output shaft of the gas generator, so that the electric generator is directly coupled with the gas generator.
According to a second aspect, the invention relates to a turbomachine for an aircraft comprising at least one auxiliary power unit as described before.
Other aims, features and advantages of the invention will appear upon reading the following description, given only as a non-limiting example, and made with reference to the indexed drawings wherein:
In the following description, the terms “upstream” and “downstream” are defined with respect to the direction of circulation of air in the auxiliary power unit.
In
In general, the auxiliary power unit 10 is used to supply electrical or pneumatic energy to different systems when the aircraft is on the ground or in flight. For example, an auxiliary power unit used in a turbogenerator mode will exclusively output electrical energy to contribute to the power supply of the hybrid propulsion drive of an aircraft.
For example, the auxiliary power unit is positioned at the rear of the aircraft, in particular in the tail cone, and supplied with kerosene from the tanks of the aircraft.
As illustrated, the auxiliary power unit 10 comprises, in the axial direction from downstream to upstream, a gas generator 12, an electric generator 20 coupled to the gas generator 12 to supply electrical energy on board the aircraft and an accessory box or gearbox 24, known as “accessory gearbox”, whose acronym is AGB, arranged upstream of the electric generator 20 and coupled to said electric generator 20.
The gas generator 12, the electric generator 20 and the accessory gearbox 24 are coaxial.
The accessory gearbox 24 comprises a reduction mechanism (not visible in
As could be seen in
As illustrated, the gas generator 12 comprises a gas turbine 14 comprising a main shaft 14a rotatably coupled to a main air compressor 16. The main air compressor 16 comprises an air inlet 16a. The gas generator 12 further comprises a combustion chamber section 12a and an exhaust nozzle 12b downstream of the gas turbine 14 to evacuate the combustion products according to the arrow represented in
In the illustrated example, the output shaft of the gas turbine 14 and the input shaft of the main air compressor 16 are a common shaft 14a. Alternatively, it is possible to provide for an output shaft of the gas turbine 14 that is distinct from the input shaft of the main air compressor 16 and coupled to said input shaft by a coupling system.
Without limitation, the gas generator 12 may also comprise a load compressor 19, represented in dotted lines in
As illustrated, the gas generator 12 comprises an air outlet 16b upstream of the load compressor 19 in the case where a load compressor is present.
In the case where the load compressor 19 is not present, the shaft 14a of the gas turbine 14 is directly coupled to the input shaft 20a of the electric generator 20, using a second coupling system 22. The latter may consist, for example, of a system for coupling by splines between the two shafts 14a and 20a or else of a flexible connection system allowing damping the vibrations transmitted from the shaft 14a towards the input shaft 20a. Thus, the gas generator 12 is directly coupled with the electric generator 20, without any intermediate element for taking up mechanical energy from the gas generator such as a load compressor or an accessory gearbox.
The electric generator 20 further comprises an output shaft 20b or rotor shaft directly connected to the accessory gearbox 24.
As illustrated in
The shaft of the central pinion 24b could be fitted, for example using splines, onto the rotor shaft 20b of the electric generator 20.
Such an accessory gearbox is no longer intended to serve as an oil tank which could then be shifted. Hence, the only function of the accessory gearbox 24 is to drive the accessories and could thus be made by machining a metal part, without resorting to costly foundry processes.
The positioning of the accessory gearbox 24 at the rear of the electric generator 20 allows retaining the rotor of the electric generator inside its stator in the event of failure. Indeed, in the event of mechanical breakage of a rotor at high speed, the rear flange of the electric machine is generally pulled off, which could lead to the ejection of the rotor. Hence, the accessory gearbox 24 allows avoiding the axial ejection of the rotor by ensuring the function of locking the rotor.
Thanks to the invention, the accessory gearbox 24 could be particularly compact radially. It could support accessories relatively slightly offset with respect to a central axis of the box 24, in comparison with the prior art.
The positioning at the rear of hydraulic pumps on the accessories box 24 allows making the flows, in particular oil and fuel, transit through the electrical and electronic equipment of the electric generator 20, in order to ensure cooling of the equipment that are sensitive to high temperatures.
The positioning of the accessory gearbox 24 also has the advantage of being able to drive a cooling fan for example for a heat exchanger.
Finally, in contrast with the accessory gearboxes known from the prior art, the accessory gearbox according to the invention no longer ensures the function of mechanically holding the auxiliary power unit on the aircraft, which is now ensured by means of the casing of the electric generator.
| Number | Date | Country | Kind |
|---|---|---|---|
| 1914417 | Dec 2019 | FR | national |
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/EP2020/084826 | 12/7/2020 | WO |
