Rotary wing aircraft with a hybrid power plant

Patent metadata

Field	Value
Publication number	US-9447734-B2
Application number	US-201414220618-A
Country	US
Kind code	B2
Filing date	Mar 20, 2014
Priority date	Mar 25, 2013
Publication date	Sep 20, 2016
Grant date	Sep 20, 2016

Abstract

An aircraft ( 1 ) having at least one rotor ( 2 ) driven by a main gearbox ( 3 ), at least one fuel-burning engine ( 4 ), an on-board electricity network ( 7 ), and at least one electrical machine ( 10 ) corresponding to the engine ( 4 ) and capable of operating both in electric motor mode and also in electricity generator mode, each electrical machine ( 10 ) being mechanically connected to said main gearbox ( 3 ) by first connection means ( 20 ) and being electrically connected to said on-board electricity network ( 7 ). Second mechanical connection means ( 40 ) connect each electrical machine ( 10 ) mechanically to a gas generator ( 5 ) of an engine.

First claim

What is claimed is:

1. A rotary wing aircraft comprising:
at least one rotor driven in rotation by a main gearbox;
at least one fuel-burning engine comprising a gas generator and a free turbine in order to drive the main gearbox;
an on-board electricity network and with at least one electrical machine operating in electric motor mode and in electricity generator mode, each electrical machine being mechanically connected to the main gearbox via first connection means and electrically connected to the on-board electricity network, wherein the electrical machine is suitable for driving the main gearbox and for generating electricity energy, the aircraft is provided with second mechanical connection means for mechanically connecting each electrical machine to a gas generator, each first connection means comprising an upstream portion situated between a first mechanical member and an electrical machine, together with a downstream portion situated between the main gearbox and the first mechanical member, the first mechanical member being provided with two rotary parts and with constraining means to constrain said two rotary parts to rotate together in flight permanently except in the event of the electrical machine jamming, and for separating said two rotary parts from rotating together on the ground when the upstream portion rotates at an upstream speed of rotation (Vmr) faster than a downstream speed of rotation (Vbtp) of the downstream portion.

2. An aircraft according to claim 1 , wherein the first mechanical member comprises a clutch.

3. An aircraft according to claim 1 , wherein the first mechanical member comprises a blockable freewheel provided with a driving rotary part connected to the main gearbox and a driven rotary part connected to a reversible machine and to a constraining system for constraining the driving rotary part to rotate together with the driven rotary part so as to operate:
either in an interpenetrating mode in flight during which the driving rotary part and the driven rotary part are constrained to rotate together; or else
in a freewheel mode on the ground during which the driving rotary part drives rotation of the driven rotary part when the driving rotary part possesses a speed of rotation faster than the speed of rotation of the driven rotary part.

4. An aircraft according to claim 1 , wherein at least one electrical machine is mechanically connected only to the main gearbox and to a gas generator.

5. An aircraft according to claim 1 , wherein at least one electrical machine is mechanically connected to the main gearbox, and also to a gas generator and to the free turbine of a gas generator, by being interposed between the free turbine and the main gearbox.

6. An aircraft according to claim 4 , wherein the aircraft has a freewheel provided with a driving portion connected to a free turbine and a driven portion connected to a drive shaft of first connection means, the drive shaft co-operating with an electrical machine and leading to the first mechanical member of the first connection means, a rotor brake being arranged between the first mechanical member and the main gearbox.

7. An aircraft according to claim 1 , wherein each electrical machine is connected to electrical energy storage means.

8. An aircraft according to claim 1 , wherein each electrical machine is connected to the on-board electricity network via a power converter.

9. An aircraft according to claim 1 , wherein at least one second connection means comprises mechanical means presenting a transmission ratio (α) greater than the quotient of the maximum speed of rotation of the gas generator divided by the maximum speed of rotation of the free turbine of the given engine.

10. An aircraft according to claim 1 , wherein at least second connection means include a separator member for separating an electrical machine from a gas generator in predetermined situations.

11. An aircraft according to claim 1 , wherein the aircraft has one electric motor per engine, each electric motor being mechanically connected to a gas generator and electrically connected to the on-board electricity network.

12. An aircraft according to claim 1 , wherein the aircraft includes a power converter arranged between the electric motor and the on-board electricity network.

13. An aircraft according to claim 12 , wherein at least one second connection means includes a freewheel having a driving portion connected to a gas generator of a given engine and a driven portion connected to mechanical means presenting a predetermined transmission ratio (α), the transmission ratio (α) being greater than the quotient of the maximum speed of rotation of the gas generator divided by the maximum speed of rotation of the free turbine of the given engine.

14. An aircraft according to claim 1 , wherein at least one second connection means includes a freewheel comprising a first driving portion connected to a gas generator of a given engine and a first driven portion connected to first mechanical means presenting a first predetermined transmission ratio (α), the second connection means including a second freewheel comprising a second driven portion connected to the gas generator of a given engine and a second driving portion connected to second mechanical means presenting a second predetermined transmission ratio (β), the first transmission ratio (α) being greater than the quotient of the maximum speed of rotation of the first gas generator divided by the maximum speed of rotation of the free turbine of the given engine, and the second transmission ratio (β) being less than the quotient of the maximum speed of rotation of the gas generator divided by the maximum speed of rotation of the free turbine of the given engine.

15. An aircraft according to claim 14 , wherein the first mechanical means and the second mechanical means are connected to the electric machine via an intermediate shaft, and a breakable section is interposed between the second mechanical means and the intermediate shaft.

16. An aircraft according to claim 1 , wherein at least one second connection means includes a second mechanical member having two movable parts capable of being constrained reversibly to rotate together with each other on request, namely a driving movable part connected to a gas generator of a given engine, and a driven movable part connected to mechanical means presenting a predetermined transmission ratio (α), the transmission ratio (α) being greater than the quotient of the maximum speed of rotation of the gas generator divided by the maximum speed of rotation of the free turbine of the given engine.

17. An aircraft according to claim 16 , wherein the second mechanical member comprises a blockable freewheel having the driving movable part connected to a gas generator and the driven movable part connected to the mechanical means together with a device for constraining the driving movable part in rotation with the driven movable part to operate:
either, on the ground, in an interpenetrating mode during which the driving movable part of the second mechanical member and the driven movable part of the second mechanical member are constrained to rotate together; or else
in flight, in a freewheel mode during which the driving movable part of the second mechanical member drives rotation of the driven movable part of the second mechanical member when the driving movable part of the second mechanical member possesses a speed of rotation faster than the speed of rotation of the driven movable part of the second mechanical member.

18. An aircraft according

Assignees

• Airbus Helicopters

Inventors

• Mariotto Damien
• Connaulte Matthieu

Classifications

• B64D35/025

  of parallel type · CPC title

• B64D35/024

  of series type · CPC title

• B64D35/023

  of series-parallel type · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• F02C7/36 Primary

  Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) · CPC title