Electric-based secondary power system architectures for aircraft
Methods and systems for providing secondary power to aircraft systems. In one embodiment, an aircraft system architecture for providing power to an environmental control system includes an electric generator operably coupled to a jet engine. The jet engine can be configured to provide propulsive thrust to the aircraft, and the electric generator can be configured to receive shaft power from the jet engine. The environmental control system can be configured to provide outside air to a passenger cabin of the aircraft in the absence of bleed air from the jet engine.
1. A method for providing conditioned air to a fuselage of an aircraft, the aircraft including a jet engine configured to provide propulsive thrust to the aircraft, the method comprising:
operably coupling an electric generator to the jet engine, the electric generator configured to receive shaft power from the jet engine;
operably coupling an electric motor to a compressor fan to drive the compressor fan, the compressor fan being positioned in flow communication with the fuselage; and
providing electric power from the electric generator to the electric motor to drive the compressor fan and flow air from outside the fuselage into the fuselage in the absence of bleed air from the jet engine.
2. The method of claim 1 , further comprising:
positioning a resistive heater downstream of the compressor fan; and
conducting electric power from the electric generator to the resistive heater to warm the outside air before the outside air flows into the fuselage.
3. The method of claim 1 wherein operably coupling an electric motor to the compressor fan includes operably coupling an adjustable speed electric motor to the compressor fan, wherein the method further comprises modulating the speed of the electric motor in response to changes in the pressurization requirements of the fuselage.
4. The method of claim 1 wherein operably coupling an electric motor to the compressor fan includes operably coupling an adjustable speed electric motor to the compressor fan, wherein the method further comprises modulating the speed of the electric motor in response to changes in the temperature requirements of the fuselage.
5. On a transport aircraft having a fuselage, a wing extending outwardly from the fuselage, and a jet engine for providing propulsive thrust, a method for providing secondary power from the jet engine to a plurality of aircraft systems including an environmental control system, a wing ice protection system, and a landing gear system, the method for providing secondary power comprising:
operably coupling an electric generator to the jet engine, the electric generator configured to receive shaft power from the jet engine;
providing electric power from the electric generator to a fan motor of the environmental control system, the environmental control system configured to provide conditioned air to at least a portion of the fuselage in the absence of bleed air from the jet engine;
providing electric power from the electric generator to a heating element of the wing ice protection system, the wing ice protection system configured to at least reduce the formation of ice on a portion of the wing in the absence of bleed air from the jet engine; and
providing electric power from the electric generator to an electric-motor driven hydraulic pump of the landing gear system, the hydraulic pump configured to operate a landing gear in the absence of bleed air from the jet engine.
6. The method of claim 5 wherein the electric generator operably coupled to the jet engine is a first electric generator, and wherein the method further comprises:
installing an auxiliary power unit on the aircraft;
operably coupling a second electric generator to the auxiliary power unit, wherein the second electric generator is configured to receive shaft power from the auxiliary power unit; and
providing electric power from the second electric generator to the fan motor of the environmental control system, the environmental control system configured to provide conditioned air to at least a portion of the fuselage in the absence of compressed air from the auxiliary power unit.
7. The method of claim 5 wherein the electric generator operably coupled to the jet engine is a first electric generator, and wherein the method comprises:
installing an auxiliary power unit on the aircraft;
operably coupling a second electric generator to the auxiliary power unit, wherein the second electric generator is configured to receive shaft power from the auxiliary power unit; and
providing electric power from the electric generator to the electric motor-driven hydraulic pump of the landing gear system, the hydraulic pump configured to operate a landing gear in the absence of pneumatic power from the auxiliary power unit.