Selective power distribution for an aircraft propulsion system
AssigneeRtx Corporation
InventorPaul R. Hanrahan
Life of this patent
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Abstract
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 turbine rotor, a propulsor rotor and an auxiliary turbine. The turbine rotor is within the turbine section. The turbine rotor is configured to rotatably drive the propulsor rotor. The auxiliary turbine includes an auxiliary turbine rotor. The auxiliary turbine rotor is configured to rotatably drive the propulsor rotor with the turbine rotor. The auxiliary turbine is configured to receive bleed gas from the flowpath.
Claims20
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, the turbine rotor within the turbine section;
- a propulsor rotor, the turbine rotor configured to rotatably drive the propulsor rotor;
- a geartrain, the rotating structure coupled to the propulsor rotor through the geartrain;
- and
- an auxiliary turbine comprising an auxiliary turbine rotor, the auxiliary turbine rotor configured to rotatably drive the propulsor rotor with the turbine rotor, the auxiliary turbine configured to receive bleed gas from the flowpath, and the auxiliary turbine rotor operatively coupled to the propulsor rotor independent of the geartrain.
An assembly for an aircraft propulsion system, comprising:
- a compressor section, a combustor section, a turbine section and a flowpath extending through the compressor section, the combustor section and the turbine section;
- a turbine rotor within the turbine section, the turbine rotor configured to rotate about an axis;
- a geartrain;
- a propulsor rotor, the turbine rotor configured to rotatably drive the propulsor rotor through the geartrain;
- an auxiliary turbine comprising an auxiliary turbine rotor, the auxiliary turbine rotor configured to rotatably drive the propulsor rotor, the auxiliary turbine disposed to a first side of the geartrain, and the turbine section disposed to a second side of the geartrain that is axially opposite the first side of the geartrain along the axis;
- and
- a brake configured to brake rotation of the propulsor rotor.
An assembly for an aircraft propulsion system, comprising:
- a compressor section, a combustor section, a turbine section and a flowpath extending 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 first propulsor rotor coupled to the geartrain;
- a second propulsor rotor coupled to the geartrain;
- and
- a control system configured to switch between a first mode and a second mode, the rotating structure configured to drive rotation of the first propulsor rotor through the geartrain during the first mode, the rotating structure configured to drive rotation of the second propulsor rotor through the geartrain during the second mode, and the control system including an air turbine and a brake.
Dependencies are inferred from the claim text.