AUXILIARY POWER UNIT COMPRISING A GAS GENERATOR IN DIRECT-DRIVE CONNECTION WITH AN ELECTRIC GENERATOR AND AN ACCESSORY GEARBOX

Abstract

An auxiliary power unit, in particular for an aircraft, includes a gas generator and an electric generator. The electric generator has an input shaft that is connected to an output shaft of the gas generator. The auxiliary power unit also has an accessories housing directly connected to a rotor shaft of the electric generator, wherein the electric generator is interposed between the gas generator and the accessories housing.

Claims

1. An auxiliary power unit, comprising: a gas generator; an electric generator including an input shaft connected to an output shaft of the gas generator; and an accessory gearbox directly connected to a rotor shaft of the electric generator, wherein the electric generator is mounted between the gas generator and said accessory gearbox.

2. The auxiliary power unit according to claim 1, wherein the accessory gearbox comprises a casing.

3. The auxiliary power unit according to claim 2, wherein the casing has radial dimensions smaller than or equal to radial dimensions of the electric generator.

4. The auxiliary power unit according to claim 2, wherein the accessory gearbox comprises a central pinion mounted in the casing and coupled to the shaft of the rotor of the electric generator.

5. The auxiliary power unit according to claim 4, wherein the shaft of the central pinion is fitted onto the rotor shaft of the electric generator.

6. The auxiliary power unit according to claim 4, wherein 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.

7. The auxiliary power unit according to claim 1, wherein the accessory gearbox is made by machining a metal part.

8. The auxiliary power unit according to claim 1, wherein the gas generator comprises a gas turbine and a main air compressor driven in rotation by said gas turbine.

9. The auxiliary power unit according to claim 8, wherein the gas generator comprises a load compressor mounted axially between the main air compressor and the electric generator.

10. The auxiliary power unit according to claim 1, wherein the input shaft of the electric generator is coaxial with the output shaft of the gas generator and secured in rotation with it.

11. The auxiliary power unit according to claim 1, wherein 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.

12. A turbomachine for an aircraft comprising at least one auxiliary power unit according to claim 1.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0029] 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:

[0030] FIG. 1 illustrates, very schematically, an auxiliary power unit according to an embodiment of the invention;

[0031] FIG. 2 is a side view of the auxiliary power unit of FIG. 1;

[0032] FIG. 3 illustrates in details an auxiliary power unit according to an embodiment of the invention; and

[0033] FIG. 4 is a side view of the auxiliary power unit of FIG. 2.

[0034] 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.

DETAILED DISCLOSURE OF AT LEAST ONE EMBODIMENT

[0035] In FIG. 1, an auxiliary power unit 10 for an aircraft turbomachine is represented, very schematically.

[0036] 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.

[0037] 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.

[0038] 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.

[0039] The gas generator 12, the electric generator 20 and the accessory gearbox 24 are coaxial.

[0040] The accessory gearbox 24 comprises a reduction mechanism (not visible in FIGS. 1 and 2) connected to different pieces of equipment or accessories 26a, 26b, such as, for example, an electric generator, fuel pumps, a lubrication unit, a starter, or other auxiliary accessories of the engine and of the power generation of the aircraft.

[0041] As could be seen in FIG. 2, the accessory gearbox 24 comprises a casing having a simple geometric shape, whose bulk in radial section is substantially the same as that of the electric generator 20. For example, this casing may be disk-like shaped with a diameter substantially equal to the diameter of the electric generator 20. Thus, the radial bulk of the accessory gearbox 24 is limited.

[0042] FIG. 3 represents in details an example of a gas generator 12 and an accessory gearbox 24 used in the auxiliary power unit 10. It should be noted that the invention is not limited to such an example.

[0043] 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 FIG. 3.

[0044] 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.

[0045] Without limitation, the gas generator 12 may also comprise a load compressor 19, represented in dotted lines in FIG. 3, coupled to the shaft 14a of the gas turbine 14. The load compressor 19 is configured to supply pressurised air on board the aircraft.

[0046] 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.

[0047] 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.

[0048] The electric generator 20 further comprises an output shaft 20b or rotor shaft directly connected to the accessory gearbox 24.

[0049] As illustrated in FIGS. 3 and 4, the accessory gearbox 24 comprises a casing 24a in which is mounted a central pinion 24b coupled to the shaft of the rotor 20b of the electric generator 20 and for example four reduction mechanisms 25a, 25b, 25c, 25d only two of which are visible in FIG. 3. Each of the reduction mechanisms 25a, 25b, 25c, 25d is coupled to the central pinion 24b and to a drive shaft for driving in rotation a corresponding accessory 26a, 26b, 26c, 26d. The contours of the bodies of the accessories 26a, 26b, 26c, 26d are represented by dotted lines in FIG. 4, which shows an example of an optimisation of the space occupied by these accessories. The number of reduction mechanisms is linked to the number of accessories to be driven, and could of course be other than four.

[0050] The shaft of the central pinion 24b could be fitted, for example using splines, onto the rotor shaft 20b of the electric generator 20.

[0051] 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.

[0052] 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.

[0053] 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.

[0054] 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.

[0055] 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.

[0056] 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.