Electric generator behind fan in turbine engine
A turbine engine includes a core section comprising at least one compressor and at least one turbine that both rotate about a longitudinal axis of the turbine engine; a core vane assembly coupled to the core section, wherein the core vane assembly comprises a plurality of core vanes configured to modify core fluid flow; a fan connected to the core section and configured to be rotated by the at least one turbine, rotation of the fan providing thrust to a vehicle that includes the turbine engine; and an electrical generator integrated into the core vane assembly and positioned in the core section aft of the fan and fore of the at least one compressor, wherein the electrical generator comprises: a rotor mechanically rotated via the fan or a shaft that is rotationally coupled to the fan, wherein the rotor rotates about the longitudinal axis; and a stator.
1. A turbine engine comprising:
a core section receiving a core fluid flow, the core section comprising one or more compressors and at least one turbine that both rotate about a longitudinal axis of the turbine engine;
a core vane assembly coupled to the core section, wherein the core vane assembly comprises a plurality of core vanes configured to modify the core fluid flow;
a fan connected to the core section and configured to be rotated by the at least one turbine, rotation of the fan providing thrust to a vehicle that includes the turbine engine;
a splitter ring that bifurcates a flow from the fan into the core fluid flow and a bypass airflow that passes into a bypass duct; and
an electrical generator integrated into the core vane assembly and positioned in the core section aft of the fan and fore of a most upstream stage of all the one or more compressors, the electrical generator having an upstream end fore of the splitter ring and a downstream end aft of the plurality of core vanes, wherein the electrical generator comprises:
a rotor including an armature mechanically rotated via the fan by a linkage, the linkage having a first end fixed to the armature at the upstream end of the electrical generator and a second end fixed to the fan, wherein the rotor rotates about the longitudinal axis at a same rate as the fan; and
a stator including a frame extending to the upstream end of the electrical generator and formed by an inner hub of the core vane assembly, the plurality of core vanes extending from the frame.
2. The turbine engine of claim 1 , wherein the stator of the electrical generator is integral to the inner hub of the core vane assembly.
3. The turbine engine of claim 2 , wherein the core vane assembly radiates heat emitted by the electrical generator into the core fluid flow.
4. The turbine engine of claim 1 , wherein the stator of the electrical generator comprises one or more windings that are mechanically supported by the frame.
5. The turbine engine of claim 4 , wherein the frame mechanically supports a pole of the stator.
6. The turbine engine of claim 1 , wherein the core vane assembly is non-structural.
7. The turbine engine of claim 1 , wherein the core vane assembly is structural.
8. The turbine engine of claim 1 , wherein the core vane assembly includes conductors configured to carry electrical power generated by the electrical generator.
9. The turbine engine of claim 1 , wherein the electrical generator is concentrically located with the plurality of core vanes.
10. The turbine engine of claim 9 , wherein the electrical generator is not axially overlapping with any of the one or more compressors.
11. The turbine engine of claim 1 , wherein the one or more compressors comprise intermediate pressure and high pressure compressors.
12. An airframe comprising:
a first turbine engine of one or more turbine engines, the first turbine engine comprising:
a core section receiving a core fluid flow, the core section comprising one or more compressors and at least one turbine that both rotate about a longitudinal axis of the turbine engine;
a core vane assembly coupled to the core section, wherein the core vane assembly comprises a plurality of core vanes configured to modify the core fluid flow;
a fan connected to the core section and configured to be rotated by the at least one turbine, rotation of the fan providing thrust to the airframe;
a splitter ring that bifurcates a flow from the fan into the core fluid flow and a bypass airflow that passes into a bypass duct; and
an electrical generator integrated into the core vane assembly and positioned in the core section aft of the fan and fore of a most upstream stage of all the one or more compressors, the electrical generator having an upstream end fore of the splitter ring and a downstream end aft of the plurality of core vanes, wherein the electrical generator comprises:
a rotor including an armature mechanically rotated via the fan by a linkage, the linkage having a first end fixed to the armature at the upstream end of the electrical generator and a second end fixed to the fan, wherein the rotor rotates about the longitudinal axis; and
a stator including a frame extending to the upstream end of the electrical generator and formed by an inner hub of the core vane assembly, the plurality of core vanes extending from the frame.
13. The airframe of claim 12 , wherein the stator of the electrical generator is integral to the inner hub of the core vane assembly.
14. The airframe of claim 13 , wherein the core vane assembly radiates heat emitted by the electrical generator into the core fluid flow.
15. The airframe of claim 12 , wherein the stator of the electrical generator comprises one or more windings that are mechanically supported by the frame.
16. The airframe of claim 12 , further comprising:
a second turbine engine of the one or more turbine engines; and
a load that receives electrical energy produced by electrical generators of the one or more turbine engines, the electrical generators of the one or more turbine engines including the electrical generator of the first turbine engine.
17. A turbine engine comprising:
a core section receiving a core fluid flow, the core section comprising one or more compressors and at least one turbine that both rotate about a longitudinal axis of the turbine engine;
a core vane assembly coupled to the core section, wherein the core vane assembly comprises a plurality of core vanes configured to modify the core fluid flow;
a fan connected to the core section and configured to be rotated by the at least one turbine, rotation of the fan providing thrust to a vehicle that includes the turbine engine;
a splitter ring that bifurcates a flow from the fan into the core fluid flow and a bypass airflow that passes into a bypass duct; and
an electrical generator integrated into the core vane assembly and positioned in the core section aft of the fan and fore of a most upstream stage of all the one or more compressors, the electrical generator having an upstream end fore of the splitter ring and a downstream end aft of the plurality of core vanes, wherein the electrical generator is not axially overlapping with any of the one or more compressors, and wherein the electrical generator comprises:
a rotor including an armature mechanically rotated via the fan by a linkage, the linkage having a first end fixed to the armature at the upstream end of the electrical generator and a second end fixed to the fan, wherein the rotor rotates about the longitudinal axis at a same rate as the fan; and
a stator including a frame extending to the upstream end of the electrical generator and formed by an inner hub of the core vane assembly, the plurality of core vanes extending from the frame.