HYBRID POWER SYSTEM ARCHITECTURE FOR AN AIRCRAFT

• US 20130036730A1
• Filed: 08/10/2011
• Published: 02/14/2013
• Est. Priority Date: 08/10/2011
• Status: Active Grant

• Current Assignee: Hamilton Sundstrand Corporation (Rtx Corporation)
• Original Assignee: Hamilton Sundstrand Corporation (Rtx Corporation)
• Inventors: Bruno, Louis J., Jones, Anthony C., Spierling, Todd A., DeFrancesco, Gregory L.
• Granted Patent: US 8,500,064 B2
• Time in Patent Office: Days
• US Class Current: 60/486
• CPC Class Codes: B64C 13/40 using fluid pressure
• CPC Class Codes: B64C 13/42 having duplication or stand-by provisions
• CPC Class Codes: B64D 2221/00 Electric power distribution systems onboard aircraft
• CPC Class Codes: B64D 41/00 Power installations for auxiliary purposes

Abstract

A hybrid power distribution system for an aircraft generates hydraulic power from one of a plurality of power sources based on which power source provides energy most efficiently. Power sources includes an electric power distribution bus that distributes electrical energy onboard the aircraft, a pneumatic distribution channel that distributes pneumatic energy onboard the aircraft, and mechanical power provided by one or more engines associated with the aircraft.

Claims

1. A hybrid power distribution system for an aircraft having at least one aircraft engine, the hybrid power distribution system comprising:

a plurality of power sources connected to supply energy to a hydraulic distribution channel that provides power to hydraulic loads on the aircraft, wherein the plurality of power sources includes an electric power distribution bus that distributes electrical energy onboard the aircraft, a pneumatic distribution channel that distributes pneumatic energy onboard the aircraft, and mechanical energy derived from the aircraft engine;

an engine driven pump for converting mechanical energy provided by at least one aircraft engine to hydraulic energy in the hydraulic distribution channel;

an alternating current (AC) motor pump for converting electrical energy provided by the electrical power distribution bus to hydraulic energy in the hydraulic distribution channel;

an air driven pump for converting pneumatic energy provided by the pneumatic distribution channel to hydraulic energy in the hydraulic distribution channel, wherein the engine driven pump, the AC motor pump, or the air driven pump are selectively operated based on operating conditions of the aircraft to supply energy to the hydraulic distribution circuit.

2. The hybrid power distribution system of claim 1, further including:

a controller that monitors operating parameters of the aircraft and provides control instructions to selectively activate the engine driven pump, the AC motor pump and the air driven pump based on the monitored operating parameters.

3. The hybrid power distribution system of claim 1, wherein the electrical power distribution bus is supplied with energy from starter-driver/generator associated with an engine on-board the aircraft.

4. The hybrid power distribution system of claim 3, wherein the starter-driver/generator operates in a motor mode to convert electrical energy provided by an auxiliary power unit (APU) to mechanical energy for supply to the engine on-board the aircraft.

5. The hybrid power distribution system of claim 1, wherein the pneumatic distribution channel is supplied with energy from low-pressure bleed air extracted from an engine onboard the aircraft.

6. The hybrid power distributions system of claim 5, further including:

an environmental control system (ECS) connected to receive low-pressure bleed air from the pneumatic distribution channel, wherein the ECS includes temperature control components supplied with power from the electrical power distribution bus to provide cooling and heating to the low-pressure bleed air provided from the pneumatic distribution channel.

7. The hybrid power distribution system claim 6, wherein the temperature control components include an electric heater system to provide heating to the low-pressure bleed air provided from the pneumatic distribution channel.

8. The hybrid power distribution system of claim 6, wherein the ECS includes electric drive fans for supplying ambient air through the temperature control components when no low-pressure bleed air is available via the pneumatic distribution channel.

9. A hybrid power distribution system for use in an aircraft having at least one engine, the hybrid power distribution system comprising:

a starter drive/generator that converts mechanical energy provided by the at least one engine to electrical energy for distribution via an electrical distribution bus;

a pneumatic distribution channel for extracting low-pressure bleed air from the at least one engine; and

an environmental control system (ECS) connected to receive low-pressure bleed air from the pneumatic distribution circuit, wherein the ECS includes temperature control components supplied with power from the electrical power distribution bus to provide cooling and heating to the low-pressure bleed air provided from the pneumatic distribution channel.

10. The hybrid power distribution system of claim 9, further including:

an auxiliary power unit (APU) that includes a starter/generator for converting mechanical energy provided by the APU to electrical energy for supply to the electrical distribution bus, wherein the electrical energy provided by the starter/generator of the APU is supplied to the starter drive/generator for conversion to mechanical power for starting the at least one engine without pneumatic energy being supplied to aid in starting of the least one engine.

11. The hybrid power distribution system of claim 9, wherein the temperature control components include an electric driven vapor cycle system to provide cooling to the low-pressure bleed air provided from the pneumatic distribution circuit.

12. The hybrid power distribution system of claim 9, wherein the temperature control components include an electric heater system to provide heating to the low-pressure bleed air provided from the pneumatic distribution circuit.

13. The hybrid power distribution system of claim 9, wherein the ECS includes electric drive fans for supplying ambient air through the temperature control components when no low-pressure bleed air is available via the pneumatic distribution circuit.

14. The hybrid power distribution system of claim 9, further including:

a hydraulic distribution channel for providing hydraulic power to loads on the aircraft;

an engine-driven pump connected to convert mechanical energy provided by the at least one engine to hydraulic energy in the hydraulic distribution channel;

an electric-driven motor pump for converting electric energy provided by the electrical distribution bus to hydraulic energy for distribution by the hydraulic distribution circuit; and

an air-driven pump for converting pneumatic energy provided by the pneumatic distribution circuit to hydraulic energy for distribution by the hydraulic distribution circuit, wherein hydraulic power is generated in the hydraulic distribution circuit by one of the engine-driven pump, the electric-driven motor pump, and air-driven pump during various flight segments based on which supplies the hydraulic power most efficiently.