Secondary power integrated cabin energy system for a pressurized aircraft

• US 6,283,410 B1
• Filed: 11/04/1999
• Issued: 09/04/2001
• Est. Priority Date: 11/04/1999
• Status: Expired due to Fees

• Current Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Thompson, Robert George
• Primary Examiner(s): Jordan, Charles T.
• Assistant Examiner(s): Steele, George L.
• Application Number:
  US09/434,054
• Time in Patent Office: 670 Days
• Field of Search: 244/59, 454/71, 454/72, 454/70, 454/238, 165/235, 165/234, 128/200.24
• US Class Current: 244/59
• CPC Class Codes: B64D 2013/0611 combined with auxiliary power units (APU's)
• CPC Class Codes: B64D 41/00 Power installations for auxiliary purposes
• CPC Class Codes: F05B 2220/50 for auxiliary power units (APU's)
• CPC Class Codes: Y02T 50/50 On board measures aiming to increase energy efficiency

Abstract

Increased efficiency of operation in pressurized aircraft may be obtained by employing pressurized air to be discharged from an aircraft cabin 10 as combustion air by applying it to the inlet 42 of a cycle compressor 40 whereat it is compressed before being fed to a combustor 52. Fuel from a source 64 is combusted within the combustor 52 and drives a high pressure turbine 48 as well as a low pressure turbine 30, either one of which may drive a load 56, 58 to provide electrical power for the aircraft. In addition, a load compressor 20 provides air to an environmental control system including an ECS turbo machine 88 and a bypass 110 for delivering conditioned air to the cabin 10.

Claims

1. A secondary power integrated cabin energy system for an aircraft, comprising:

an aircraft cabin;

a low pressure rotary turbo machine including a rotary load compressor connected by a first shaft to a rotary, low pressure turbine wheel;

a high pressure rotary turbo machine including a rotary cycle compressor connected by a second shaft to a rotary high pressure turbine wheel;

a combustor connected to an outlet of said cycle compressor and a source of fuel for combusting fuel to generate combustion gases and direct them to said high pressure turbine wheel to cause rotation of the same;

an ambient air inlet for said load compressor

first ducting connecting an outlet of said load compressor to said cabin to provide compressed air to pressurize said cabin;

second ducting connecting said cabin to an inlet of said cycle compressor; and

third ducting connecting an outlet of said high pressure turbine wheel to an inlet for said low pressure turbine wheel.

2. The secondary power integrated cabin energy system of claim 1 wherein said shafts are coaxial.

3. The secondary power integrated cabin energy system of claim 2 wherein said first shaft is rotatable within said second shaft.

4. The secondary power integrated cabin energy system of claim 1 further including at least one heat exchanger in said first ducting, said heat exchanger including a coolant flow path in heat exchange relation with said first ducting.

5. The secondary power integrated cabin energy system of claim 4 wherein said coolant flow path includes an inlet connected to receive ambient air.

6. The secondary power integrated cabin energy system of claim 4 wherein said coolant flow path includes an inlet connected to said cabin to receive cabin air.

7. The secondary power integrated cabin energy system of claim 4 wherein said first ducting further includes an environmental control system (ECS) rotary turbo machine including an ECS compressor connected to an ECS turbine wheel;

said at least one heat exchanger being located in said first ducting between said load compressor outlet and said ECS turbo machine and connected to an inlet of said ECS compressor, and a further heat exchanger having a first flow path interconnecting an outlet of said ECS compressor to an inlet of said ECS turbine wheel, said first ducting further interconnecting an outlet of said ECS turbine wheel to said cabin, said further heat exchanger further including a second flow path for coolant and in heat exchange relation with said first flow path.

8. The secondary power integrated cabin energy system of claim 7 wherein said second flow path has an inlet connected to receive ambient air.

9. The secondary power integrated cabin energy system of claim 7 wherein said second flow path has an inlet connected to said cabin to receive cabin air.

10. The secondary power integrated cabin energy system of claim 1 further including a load to be driven connected to said first shaft.

11. The secondary power integrated cabin energy system of claim 1 further including an ambient air inlet for said cycle compressor.

12. The secondary power integrated cabin energy system of claim 11 including a check valve in said cycle compressor ambient air inlet.

13. The secondary power integrated cabin energy system of claim 1 wherein said inlet of said cycle compressor includes an inlet area varying device at the point of connection of said cycle compressor and said second ducting.

14. The secondary power integrated cabin energy system of claim 13 wherein said inlet area varying device comprises variable inlet guide vanes.

15. A secondary power integrated cabin energy system for an aircraft, comprising:

a low pressure rotary turbo machine including a rotary load compressor connected by a first shaft to a rotary, low pressure turbine wheel;

a high pressure rotary turbo machine including a rotary cycle compressor connected by a second shaft to a rotary high pressure turbine wheel, said second shaft being concentric about said first shaft;

a combustor connected to an outlet of said cycle compressor and a source of fuel for combusting fuel to generate combustion gases and direct them to said high pressure turbine wheel to cause rotation of the same;

an ambient air inlet for said load compressor

a first ducting adapted to connect an outlet of said load compressor to an aircraft cabin to provide compressed air to pressurize the cabin;

second ducting adapted to connect an aircraft cabin to an inlet of said cycle compressor; and

third ducting connecting an outlet of said high pressure turbine wheel to an inlet for said low pressure turbine wheel.

16. A secondary power integrated cabin energy system for an aircraft, comprising:

a turbomachine including a rotary compressor connected by a shaft to a rotary turbine wheel and a combustor connected to an outlet of said compressor, to a source of fuel to be combusted to provide gases of combustion and to an inlet to said turbine wheel so that said gases of combustion may drive said turbine wheel to, in turn, drive said compressors;

an inlet to said compressor;

ducting adapted to be connected to an aircraft cabin and to said compressor inlet to provide air from said cabin to said compressor to be compressed thereby and delivered to said combustor to combust fuel therein;

a load to be driven connected to said turbomachine; and

a source of air under pressure adapted to be connected to an aircraft cabin, said source of air under pressure including a second rotary compressor coupled by a second shaft to a second rotary turbine wheel.

17. The secondary power integrated cabin energy system of claim 16 wherein said second compressor, second shaft and second turbine wheel form part of said turbo machine, and said shafts are coaxial.