Selective power distribution for an aircraft propulsion system
An assembly is provided for an aircraft propulsion system. This assembly includes a compressor section, a combustor section, a turbine section and a flowpath extending sequentially through the compressor section, the combustor section and the turbine section. The assembly also includes a rotating structure, a geartrain, a propulsor rotor and a turbine. The rotating structure includes a turbine rotor within the turbine section. The geartrain is coupled to the rotating structure. The propulsor rotor is coupled to the geartrain. The rotating structure is configured to drive rotation of the propulsor rotor through the geartrain. The turbine is coupled to the geartrain. The turbine is configured to receive bleed gas from the flowpath.
1. An assembly for an aircraft propulsion system, comprising:
a compressor section, a combustor section, a turbine section and a flowpath extending sequentially through the compressor section, the combustor section and the turbine section;
a rotating structure comprising a turbine rotor within the turbine section;
a geartrain coupled to the rotating structure;
a propulsor rotor coupled to the geartrain, the rotating structure configured to drive rotation of the propulsor rotor through the geartrain;
a turbine coupled to the geartrain, the turbine configured to receive bleed gas from the flowpath; and
the geartrain comprising:
a sun gear coupled to the propulsor rotor;
a ring gear coupled to the turbine;
a plurality of intermediate gears, each of the plurality of intermediate gears between and meshed with the sun gear and the ring gear; and
a carrier coupled to the rotating structure, each of the plurality of intermediate gears rotatably mounted to the carrier.
2. The assembly of claim 1 , wherein the turbine comprises an air turbine.
3. The assembly of claim 1 , wherein the bleed gas comprises bleed air from the compressor section.
4. The assembly of claim 1 , wherein
the compressor section includes a low pressure compressor section and a high pressure compressor section; and
the turbine is configured to receive the bleed gas from the high pressure compressor section.
5. The assembly of claim 1 , further comprising:
a power transmission device coupling the geartrain to the propulsor rotor;
the turbine configured to drive rotation of the power transmission device through the geartrain.
6. The assembly of claim 5 , wherein the turbine is configured to drive rotation of the power transmission device down to a zero rotational speed.
7. The assembly of claim 6 , further comprising a lock device configured to lock rotation of the power transmission device when the power transmission device is at the zero rotational speed.
8. The assembly of claim 7 , wherein the lock device comprises a splined coupling.
9. The assembly of claim 1 , wherein the turbine is configured to drive rotation of the sun gear down to a zero rotational speed.
10. The assembly of claim 9 , further comprising a lock device configured to lock rotation of the sun gear when the sun gear is at the zero rotational speed.
11. The assembly of claim 1 , further comprising a lock device configured to lock rotation of the ring gear when the ring gear is at a zero rotational speed.
12. The assembly of claim 1 , further comprising:
a first propulsor rotor;
the rotating structure configured to drive rotation of the first propulsor rotor through the geartrain; and
the propulsor rotor is a second propulsor rotor.
13. The assembly of claim 12 , wherein the turbine is configured to stop rotation of the second propulsor rotor while the first propulsor rotor continues to rotate.
14. The assembly of claim 12 , wherein a rotational axis of the first propulsor rotor is angularly offset from a rotational axis of the second propulsor rotor.
15. The assembly of claim 1 , further comprising a flex joint connecting the geartrain to the propulsor rotor.
16. An assembly for an aircraft propulsion system, comprising:
a first propulsor rotor;
a second propulsor rotor;
a geartrain;
an engine core including a compressor section, a combustor section, a turbine section, a flowpath and a rotating structure, the flowpath extending through the compressor section, the combustor section and the turbine section, the rotating structure comprising a turbine rotor within the turbine section, and the rotating structure configured to drive rotation of the first propulsor rotor and the second propulsor rotor through the geartrain;
a turbine configured to drive rotation of the second propulsor rotor through the geartrain, the turbine configured to receive bleed gas from the flowpath; and
the geartrain comprising:
a sun gear coupled to the second propulsor rotor;
a ring gear coupled to the turbine;
a plurality of intermediate gears, each of the plurality of intermediate gears between and meshed with the sun gear and the ring gear; and
a carrier coupled to the rotating structure and the first propulsor rotor,
each of the plurality of intermediate gears rotatably mounted to the carrier.
17. An assembly for an aircraft propulsion system, comprising:
a propulsor rotor;
an engine core including a compressor section, a combustor section, a turbine section, a flowpath and a rotating structure, the flowpath extending through the compressor section, the combustor section and the turbine section, the rotating structure comprising a turbine rotor within the turbine section, and the rotating structure configured to drive rotation of the propulsor rotor;
an air turbine configured to receive bleed air from the compressor section, the air turbine configured to drive rotation of the propulsor rotor; and
an epicyclic geartrain comprising:
a sun gear coupled to the propulsor rotor;
a ring gear coupled to the air turbine;
a plurality of intermediate gears, each of the plurality of intermediate gears between and meshed with the sun gear and the ring gear; and
a carrier coupled to the rotating structure, each of the plurality of intermediate gears rotatably mounted to the carrier.