Integrated air conditioning and power unit

• US 5,899,085 A
• Filed: 08/01/1997
• Issued: 05/04/1999
• Est. Priority Date: 08/01/1997
• Status: Expired due to Term

• Current Assignee: Mcdonnell Douglas Corporation (The Boeing Co.)
• Original Assignee: Mcdonnell Douglas Corporation (The Boeing Co.)
• Inventors: Williams, Kenneth R.
• Primary Examiner(s): Tapolcai, William E.
• Application Number:
  US08/905,303
• Time in Patent Office: 641 Days
• Field of Search: 62/DIG. 5, 62/236, 62/239, 62/331, 60/39.07, 60/39.183
• US Class Current: 62/236
• CPC Class Codes: B64D 13/06 the air being conditioned pressurising B64D13/02
• CPC Class Codes: B64D 2013/0611 combined with auxiliary power units (APU's)
• CPC Class Codes: F02C 6/08 the gas being bled from the gas-turbine compressor
• CPC Class Codes: F05D 2220/50 for auxiliary power units (APU's)
• CPC Class Codes: F25B 29/003 of the compression type system
• CPC Class Codes: F25B 5/02 arranged in parallel
• CPC Class Codes: F25B 9/004 the refrigerant being air
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10S 62/05 Aircraft cooling

Abstract

An integrated air conditioning and power unit is provided for use with an aircraft. The system includes an air turbine 42 having air passages connected to an engine 10 of the aircraft for receiving bleed air and/or ram air for driving the air turbine 42. A motor/generator 104 is drivingly connected to the air turbine 42. The motor/generator 104 is capable of drawing electricity from an aircraft primary power system for driving the motor or generating electricity which is delivered to the primary power system 108. An air compressor 54 is drivingly connected to the motor/generator 104 and is provided with an air passage which receives bleed air 32 and/or ram air 30 from the aircraft engine 10. A cooling system 71 is provided including a system compressor 81 drivingly connected to the motor/generator 104. A cooling system evaporator 70 and a condenser 92 are connected to the system compressor by fluid passages. The air compressor 54 includes an air outlet for providing pressurized air which is cooled by the cooling system.

Claims

1. An integrated air conditioning and power unit for use with an engine of an aircraft, comprising:

an air turbine having an inlet air passage connected to the engine;

a motor/generator drivingly attached to said air turbine;

a primary power system capable of supplying electricity to said motor/generator for operation in a motor mode and capable of receiving electricity which is generated by said motor/generator in a generator mode;

an air compressor drivingly attached to said air turbine and said motor/generator;

a ram air duct for receiving ambient air under pressure;

a cooling system including a system compressor drivingly attached to said motor/generator, a first evaporator in fluid communication with said system compressor to enable cooling air exiting at least one of said air compressor and said air turbine, and a condenser in fluid communication with said system compressor and said first evaporator;

ducting for communicating said ambient air under pressure to said air turbine and said air compressor; and

a valve system for controlling the application of said ambient air selectively to said air turbine and said air compressor depending on operational conditions affecting said aircraft.

2. The integrated air conditioning and power unit according to claim 1, wherein said cooling system further includes a second evaporator fluidly connected to said system compressor and a recirculation fan for drawing air from inside an enclosed space through said second evaporator.

3. The integrated air conditioning and power unit according to claim 1, wherein said condenser of said cooling system transfers heat to a heat sink.

4. The integrated air conditioning and power unit according to claim 1, wherein said air turbine is provided with an exhaust outlet which provides heated air for an aircraft anti-ice mechanism.

5. The integrated air conditioning and power unit according to claim 1, further comprising a mixing valve connected to receive air from an outlet of said air compressor and an outlet of said air turbine, said mixing valve being adjustable to alter an amount of air to be cooled by said first evaporator of said cooling system.

6. The integrated air conditioning and power unit according to claim 1, wherein said inlet air passage provides compressor bleed air from a compressor associated with said aircraft engine to said air turbine.

7. An integrated air conditioning and power unit for use with an aircraft engine including an air inlet and a compressor, comprising:

an air turbine in fluid communication with one of the air inlet and the compressor of the engine;

an air compressor drivingly attached to said air turbine, said air compressor being in fluid communication with one of the air inlet and the compressor of the engine;

a ram air duct for receiving pressurized ambient air;

a motor/generator drivingly attached to said air compressor;

a primary power system capable of supplying electricity to said motor/generator for operation in a motor mode and capable of receiving electricity which is generated by said motor/generator in a generator mode;

a cooling system including a system compressor drivingly attached to said motor/generator, a first evaporator in fluid communication with said system compressor, and a condenser in fluid communication with said system compressor and said first evaporator by fluid passages;

ducting for providing pressurized ambient air to said air turbine and said air compressor;

a valve system for selectively directing said pressurized ambient air as needed to said air turbine and said air compressor; and

wherein said air compressor includes an air outlet for providing pressurized air to said first evaporator of said cooling system.

8. The integrated air conditioning and power unit according to claim 7, wherein said cooling system further includes a second evaporator fluidly connected to said system compressor and a recirculation fan for drawing air from inside an enclosed space through said second evaporator.

9. The integrated air conditioning and power unit according to claim 7, wherein said condenser of said cooling system transfers heat to a heat sink.

10. The integrated air conditioning and power unit according to claim 7, wherein said air turbine is provided with an exhaust outlet which provides heated air for an aircraft anti-ice mechanism.

11. The integrated air conditioning and power unit according to claim 7, further comprising a mixing valve connected to receive air from said air outlet of said air compressor and an outlet of said air turbine, said mixing valve being adjustable to alter an amount of air to be cooled by said first evaporator of said cooling system.

12. The integrated air conditioning and power unit according to claim 7, wherein said air turbine is selectively provided with compressor bleed air from the compressor of the engine.

13. A power unit for an aircraft having an engine, comprising:

an air turbine having an air passage connected to a bleed air port of said engine;

a motor/generator drivingly attached to said air turbine;

a primary power system capable of supplying electricity to said motor/generator for operation in a motor mode and capable of receiving electricity which is generated by said motor/generator in a generator mode;

an air compressor drivingly attached to said motor/generator and said air turbine;

a cooling system including a system compressor drivingly attached to said motor/generator, a first evaporator in fluid communication with said system compressor, and a condenser in fluid communication with said system compressor and said first evaporator;

wherein said air compressor includes an air outlet for providing pressurized air which is capable of being cooled by said first evaporator of said cooling system;

a ram air duct for receiving pressurized ambient air and supplying said air to said air compressor and said air turbine as needed; and

a first valve for applying said pressurized ambient air selectively to said air turbine to supplement said bleed air received from said engine, to thereby assist in driving said air turbine, and a second valve for permitting said pressurized ambient air to assist in driving said air compressor.

14. The power unit according to claim 13, wherein said condenser of said cooling system transfers heat to a heat sink.