Gas turbine engine electrical generator
An aircraft gas turbine engine ( 10 ) comprises a main engine spool ( 22 ) and a bearing arrangement ( 36 ) configured to rotatably support the main engine spool ( 22 ). The bearing arrangement ( 36 ) includes a damper ( 41 ) comprising a static element ( 42 ) and a moveable element ( 39 ). The gas turbine engine further comprises an electric machine ( 30 ) comprising a rotor ( 34 ) and a stator ( 32 ). The rotor ( 34 ) is mounted to the main engine spool ( 22 ), and the stator ( 32 ) is mounted to the moveable element ( 39 ) of the damper to be moveable with the moveable element ( 39 ).
1. An aircraft gas turbine engine comprising:
a main engine spool;
an electric machine comprising:
a rotor mounted to the main engine spool; and
a stator; and
a bearing arrangement configured to rotatably support the main engine spool via the rotor, the bearing arrangement comprising a damper comprising:
a static element; and
a moveable element mounted to the stator such that the stator is moveable with the moveable element.
2. The gas turbine engine according to claim 1 , wherein the damper comprises one of a squeeze film damper, an elastomeric material, an electromagnetic damper, and a piston damper.
3. The gas turbine engine according to claim 1 , wherein the stator is cantilevered from the damper.
4. The gas turbine engine according to claim 1 , further comprising:
first and second bearing arrangements, each bearing arrangement comprising a respective damper comprising a static element and a moveable element,
wherein the stator is mounted to each moveable element.
5. The gas turbine engine according to claim 1 , wherein the bearing arrangement comprises a roller bearing.
6. The gas turbine engine according to claim 1 , wherein the electric machine comprises one or both of an electric motor configured to provide motive power to start the gas turbine engine in a starting mode, and a generator configured to generate electrical power when in a running mode.
7. The gas turbine engine according to claim 1 , wherein the electric machine comprises a radial flux electric machine.
8. The gas turbine engine according to claim 1 , wherein the electric machine comprises a permanent magnet electric machine.
9. The gas turbine according to claim 1 , wherein the main engine spool comprises:
a shaft arranged to couple a turbine to a compressor;
one or more compressor or turbine drive arms; and
one or more compressor or turbine discs,
wherein the drive arms are configured to couple one or more discs to the shaft, and the electric machine rotor is coupled to one of a drive arm and a disc.
10. The gas turbine engine according to claim 1 , further comprising:
a high pressure spool comprising a high pressure compressor coupled to a high pressure turbine by a high pressure shaft; and
a low pressure spool comprising a low pressure compressor coupled to a low pressure turbine by a low pressure shaft,
wherein the electric machine rotor is coupled to one of the high pressure spool and the low pressure spool.