Generator embedded in turbine engines
View Patent ↗Various aspects of the techniques are directed to a turbine engine comprising a core section, a fan, and an electrical generator. The core section comprises at least one compressor and at least one turbine that both rotate about a longitudinal axis of the turbine engine, wherein the at least one turbine drives at least one spool, and an oil sump positioned to collect oil used to lubricate rotational elements for one or more of the at least one compressor and the at least one turbine. The fan rotated by the at least one spool. The electrical generator integrated into the core section and positioned outside of the oil sump, wherein the electrical generator comprises a rotor rotated via the at least one spool about the longitudinal axis, and a stator configured to electromagnetically interact with the rotor to generate power.
1. A turbine engine comprising:
a core section comprising:
at least one compressor and at least one turbine that both rotate about a longitudinal axis of the turbine engine, wherein the at least one turbine drives at least one spool; and
an oil sump positioned to collect oil used to lubricate rotational elements for one or more of the at least one compressor and the at least one turbine;
a fan comprising a plurality of radially distributed blades and rotated by the at least one spool, the fan connected to the core section and configured to be rotated by the at least one spool, rotation of the plurality of radially distributed blades providing thrust to a vehicle that includes the turbine engine; and
an electrical generator integrated into the core section and positioned outside of the oil sump, wherein the electrical generator comprises:
a rotor rotated via the at least one spool, the rotor configured to rotate about the longitudinal axis; and
a stator configured to electromagnetically interact with the rotor to generate power.
2. The turbine engine of claim 1 , wherein rotor includes a rotor arm that is mechanically coupled to a blade retainer that retains at least one of the plurality of radially distributed blades and is angled less than 90 degrees relative to the blade retainer.
3. The turbine engine of claim 1 , wherein the electrical generator is positioned between the fan and the compressor.
4. The turbine engine of claim 1 , wherein the electrical generator is positioned adjacent to a cool air intake for the core section.
5. The turbine engine of claim 1 ,
wherein the at least one spool includes a low pressure spool,
wherein the at least one turbine includes a low pressure turbine and a high pressure turbine,
wherein the low pressure turbine drives the low pressure spool,
wherein the high pressure turbine drives a high pressure spool,
wherein the low pressure spool is configured to rotate at a slower speed than the high pressure spool, and
wherein the rotor is rotationally coupled to the low pressure spool such that the rotor rotates at the slower speed than the high pressure spool.
6. The turbine engine of claim 1 , wherein the electrical generator is not attached to an auxiliary gearbox mechanically coupled to the core section.
7. The turbine engine of claim 1 , wherein the electrical generator is a permanent magnet electrical generator in which permanent magnets are attached to the rotor.
8. The turbine engine of claim 1 , wherein the turbine engine provides the thrust to an airframe.
9. The turbine engine of claim 1 , wherein the rotor is positioned radially outside of the stator.
10. A method comprising:
operating a turbine engine to provide thrust to a vehicle that includes the turbine engine,
wherein the turbine engine comprises:
a core section including:
at least one compressor and at least one turbine that both rotate about a longitudinal axis of the turbine engine, wherein the at least one turbine drives at least one spool; and
an oil sump positioned to collect oil used to lubricate rotational elements for one or more of the at least one compressor and the at least one turbine;
a fan comprising a plurality of radially distributed blades and rotated by the at least one spool, the fan configured to be rotated by the at least one spool, rotation of the plurality of radially distributed blades providing thrust to a vehicle that includes the turbine engine; and
an electrical generator integrated into the core section and positioned radially outside of the oil sump, wherein the electrical generator comprises:
a rotor rotated by the at least one spool, the rotor configured to rotate about the longitudinal axis; and
a stator configured to electromagnetically interact with the rotor to generate power; and
operating the electrical generator via a mechanical connection to the turbine engine to output power.
11. The method of claim 10 , wherein rotor includes a rotor arm that is mechanically coupled to a blade retainer that retains at least one of the plurality of radially distributed blades and is angled less than 90 degrees relative to the blade retainer.
12. The method of claim 10 , wherein the electrical generator is positioned between the fan and the compressor.
13. The method of claim 10 , wherein the electrical generator is positioned adjacent to a cool air intake for the core section.
14. The method of claim 10 ,
wherein the at least one spool includes a low pressure spool,
wherein the at least one turbine includes a low pressure turbine and a high pressure turbine,
wherein the low pressure turbine drives the low pressure spool,
wherein the high pressure turbine drives a high pressure spool,
wherein the low pressure spool is configured to rotate at a slower speed than the high pressure spool, and
wherein the rotor is rotationally coupled to the low pressure spool such that the rotor rotates at the slower speed than the high pressure spool.
15. The method of claim 10 , wherein the electrical generator is not attached to an auxiliary gearbox mechanically coupled to the core section.
16. The method of claim 10 , wherein the electrical generator is a permanent magnet electrical generator in which permanent magnets are attached to the rotor.
17. The method of claim 10 , wherein the turbine engine provides the thrust to an airframe.
18. The method of claim 10 , wherein the rotor is positioned radially outside of the stator.
19. An aircraft comprising:
an airframe; and
a turbine engine comprising:
a core section including:
at least one compressor and at least one turbine that both rotate about a longitudinal axis of the turbine engine, wherein the at least one turbine drives at least one spool; and
an oil sump positioned to collect oil used to lubricate rotational elements for one or more of the at least one compressor and the at least one turbine;
a fan comprising a plurality of radially distributed blades and rotated by the at least one spool, the fan connected to the core section and configured to be rotated by the at least one spool, rotation of the plurality of radially distributed blades providing thrust to a vehicle that includes the turbine engine; and
an electrical generator integrated into the core section and positioned radially outside of the oil sump, wherein the electrical generator comprises:
a rotor rotated via the at least one spool, the rotor configured to rotate about the longitudinal axis; and
a stator configured to electromagnetically interact with the rotor to generate power.
20. The aircraft of claim 19 , wherein rotor includes a rotor arm that is mechanically coupled to a blade retainer that retains at least one of the plurality of radially distributed blades and is angled less than 90 degrees relative to the blade retainer.