Low pressure compressor control for a gas turbine engine
A gas turbine engine includes a low speed spool mechanically interconnecting a low pressure turbine and at least one of a fan and a prop, a high speed spool mechanically interconnecting a high pressure turbine and a high pressure compressor, and an epicyclic gear system mechanically coupled to the high speed spool. The gas turbine engine also includes a low pressure compressor mechanically coupled to the high speed spool via the epicyclic gear system. The low pressure compressor may be mechanically independent of the low speed spool. The gas turbine engine may include a plurality of motor-generators for transferring power between the high speed spool and the low pressure compressor.
1. A gas turbine engine comprising:
a low speed spool mechanically interconnecting a low pressure turbine and at least one of a fan and a prop;
a high speed spool mechanically interconnecting a high pressure turbine and a high pressure compressor;
an epicyclic gear system mechanically coupled to the high speed spool, the epicyclic gear system comprising a sun gear, a ring gear, a plurality of planet gears, and a gear carrier coupled to the plurality of planet gears, wherein the plurality of planet gears are disposed between the sun gear and the ring gear;
a low pressure compressor mechanically coupled to the high speed spool via the epicyclic gear system; and
a plurality of motor-generators comprising: a first motor-generator mechanically coupled to the sun gear; a second motor-generator mechanically coupled to the gear carrier; and a third motor-generator mechanically coupled to the high speed spool.
2. The gas turbine engine of claim 1 , wherein the low pressure compressor is mechanically independent of the low speed spool.
3. The gas turbine engine of claim 1 , wherein the high speed spool is mechanically coupled to the ring gear.
4. The gas turbine engine of claim 3 , wherein the low pressure compressor is mechanically coupled to the gear carrier.
5. The gas turbine engine of claim 1 , wherein:
the first motor-generator comprises a first rotor winding and a first stator winding;
the third motor-generator comprises a third rotor winding and a third stator winding; and
the first stator winding and the third stator winding are radially adjacent to each other such that the first stator winding and the third stator winding are electromagnetically synced.
6. The gas turbine engine of claim 5 , wherein the first stator winding and the third stator winding are integrated into a single stator winding.
7. The gas turbine engine of claim 1 , wherein:
the first motor-generator comprises a first rotor winding and a first stator winding;
the second motor-generator comprises a second rotor winding and a second stator winding; and
the first stator winding and the second stator winding are radially adjacent to each other such that the first stator winding and the second stator winding are electromagnetically synced.
8. The gas turbine engine of claim 7 , wherein the first stator winding and the second stator winding are integrated into a single stator winding.
9. The gas turbine engine of claim 1 , wherein the plurality of motor-generators are electronically coupled to a controller.
10. The gas turbine engine of claim 1 , wherein the epicyclic gear system is forward of a bearing of a vane that is disposed between the low pressure compressor and the high pressure compressor.
11. The gas turbine engine of claim 10 , wherein the plurality of motor-generators are mechanically coupled forward of the epicyclic gear system to at least one of the high speed spool and the epicyclic gear system.
12. An aircraft electrical network of a gas turbine engine, the aircraft electrical network comprising:
a first motor-generator mechanically coupled to a sun gear of an epicyclic gear system;
a second motor-generator mechanically coupled to a gear carrier of the epicyclic gear system;
a third motor-generator mechanically coupled to a high speed spool of the gas turbine engine; and
a controller in electronic control communication with the first motor-generator, the second motor-generator, and the third motor-generator.
13. The aircraft electrical network of claim 12 , wherein a low pressure compressor of the gas turbine engine is mechanically coupled to the high speed spool of the gas turbine engine via the epicyclic gear system.
14. The aircraft electrical network of claim 13 , wherein the controller comprises a first motor-generator controller electronically coupled to the first motor-generator, a second motor-generator controller electronically coupled to the second motor-generator, and a third motor-generator controller electronically coupled to the third motor-generator.