Aircraft cabin air conditioning system with improved fresh air supply

• US 5,299,763 A
• Filed: 12/23/1991
• Issued: 04/05/1994
• Est. Priority Date: 12/23/1991
• Status: Expired due to Fees

• Current Assignee: Alliedsignal Inc. (Honeywell International Inc.)
• Original Assignee: Alliedsignal Inc. (Honeywell International Inc.)
• Inventors: Araki, Roy T., Bescoby, Frank A.
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US07/813,312
• Time in Patent Office: 834 Days
• Field of Search: 244/118.5, 454/70-76, 415/205
• US Class Current: 244/118.5
• CPC Class Codes: B64D 13/06 the air being conditioned pressurising B64D13/02
• CPC Class Codes: B64D 2013/0603 Environmental Control Systems
• 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

An improved air conditioning system is provided for an aircraft, particularly with respect to providing an enhanced supply of fresh air to the aircraft cabin or cockpit. The system includes a dual inlet turbine driven at least in part by pressurized bleed air from an aircraft engine, wherein the turbine expands and cools the air preparatory to supply thereof as conditioned air to the aircraft cabin. During relatively low altitude operation, the bleed air flow is supplemented by compressed fresh air discharged from a turbine-driven compressor and supplied to the dual inlet turbine. At relatively higher altitude operation, this fresh air flow is bypassed around the turbine for addition to the bleed air flow at a downstream side of the turbine, and the entire nozzle area of the turbine is opened to the bleed air flow.

Claims

1. In an aircraft having a cabin and a pressurized bleed air flow, a cabin air conditioning system, comprising:

a turbine having a rotatable turbine wheel mounted within a turbine housing with a full circle turbine scroll for admission of airflow into driving relation with said turbine wheel defining a pair of housing inlets which are generally diametrically opposed to each other, and further including a turbine scroll valve mounted within said turbine scroll at a position generally opposite said one inlet and upstream from said other inlet, said turbine scroll valve being closed during said first mode whereby the bleed and supplemental air flows each flow into and fill a generally semi-annular half of the turbine scroll, said turbine scroll valve being open during said second mode whereby the bleed air flow fills substantially the entire full circle turbine scroll;

a compressor mounted for rotation with said turbine to draw in and compress a supplemental air flow;

means for supplying the bleed air flow to one of said turbine housing inlets for rotatably driving said turbine wheel and said compressor;

means for supplying the bleed air flow to one of said turbine housing inlets for rotatably driving said turbine wheel and said compressor;

means for supplying the supplemental air flow to the other of said turbine housing inlets to supplementally drive said turbine wheel during a first mode of operation, and for mixing the supplemental airflow with the bleed air flow at a downstream side of said turbine during a second mode of operation wherein said supplemental air flow supply means comprises a flow conduit for normally supplying the supplemental air flow from said compressor to said other turbine housing inlet, a bypass conduit connected between said flow conduit and the discharge side of said turbine, and a bypass valve for preventing passage of the supplemental air flow through said bypass conduit during said first mode, and for permitting supplemental air flow passage through said bypass conduit during said second mode; and

means for supplying the bleed and supplemental air flow from the downstream side of said turbine to the aircraft cabin.

2. The cabin air conditioning system of claim 1 wherein said first mode of operation is relatively low altitude operation of the aircraft, and wherein said second mode of operation is relatively high altitude operation of the aircraft.

3. The aircraft cabin air conditioning system of claim 1 further including means for opening and closing said bypass valve.

4. The aircraft cabin air conditioning system of claim 1 wherein said supplemental air flow supply means further includes check valve means for preventing backflow of the bleed air flow from said turbine housing to said bypass conduit during said second mode.

5. In an aircraft having a cabin and a pressurized bleed airflow, a cabin air conditioning system, comprising:

a turbine having a rotatable turbine wheel mounted within a turbine housing defining a substantially full circle turbine scroll for substantially full circle admission of air flow from a pair of inlets into driving relation with said turbine wheel, said inlets being disposed on said housing in generally diametrically opposed relation, and further including scroll valve means for bifurcating the turbine scroll into a pair of substantially semi-annular halves associated respectively with said pair of inlets during a first mode of operation;

a compressor mounted for rotation with said turbine to draw in and compress a supplemental air flow;

means for supplying the bleed air flow to one of said turbine housing inlets for rotatably driving said turbine wheel and said compressor;

means for supplying the supplemental air flow to the other of said turbine housing inlets to supplementally drive said turbine wheel during the first mode of operation, and for mixing the supplemental air flow with the bleed air flow at a downstream side of said turbine during a second mode of operation; and

means for supplying the bleed and supplemental air flow from the downstream side of said turbine to the aircraft cabin.

6. The aircraft cabin air conditioning system of claim 5 wherein said scroll valve means includes means for opening the turbine scroll to substantially full circle flow of the bleed air flow during said second mode.

7. The aircraft cabin air conditioning system of claim 5 further including means for extracting water from the bleed and supplemental air flows.

8. The aircraft cabin air conditioning system of claim 5 wherein the bleed air flow is obtained from at least one aircraft engine.

9. The aircraft cabin air conditioning system of claim 5 wherein the bleed air flow is obtained from an auxiliary power unit.

10. In an aircraft having a cabin and a pressurized bleed air flow, a cabin air conditioning system, comprising:

an air cycle machine having a turbine with a turbine wheel rotatably mounted within a turbine housing, and a compressor rotatably driven by said turbine wheel for drawing in and compressing a supplemental air flow, said turbine housing defining a substantially full circle turbine scroll for substantially full circle admission of air flow into driving relation with said turbine wheel, and said turbine housing further defining a pair of generally diametrically opposed air flow inlets;

means for supplying the bleed air flow to said turbine scroll through one of said inlets for rotatably driving said turbine wheel and said compressor;

means for supplying the supplemental air flow to said turbine scroll through the other of said inlets during a first mode of operation whereby the supplemental air flow cooperates with the bleed air flow to rotatably drive said turbine wheel and said compressor;

said turbine housing further including a scroll valve mounted within the turbine scroll at a position generally opposite to said one inlet and upstream from said other inlet, said scroll valve being closed during said first mode to bifurcate the turbine scroll into two generally semi-annular halves adapted respectively to receive the bleed and supplemental air flows; and

bypass means including a bypass valve for bypassing the supplemental air flow from said other inlet directly to a discharge side of said turbine during a second mode of operation, said bypass valve preventing supplemental air flow bypass during said first mode;

said scroll valve being opened during said second mode to permit the bleed air flow to fill substantially the entire turbine scroll.

11. The aircraft cabin air conditioning system of claim 10 further including check valve means for preventing backflow of the bleed air flow from said turbine housing to said bypass means during said second mode.

12. The aircraft cabin air conditioning system of claim 10 further including means for extracting water from the bleed and supplemental air flows.

13. In an aircraft having a cabin and a pressurized bleed air flow, a method of providing conditioned air to the cabin, said method comprising the steps of:

rotatably driving a turbine with the bleed air flow to expand and control the bleed air flow prior to supply thereof as conditioned air to the aircraft cabin;

rotatably driving a compressor with the turbine to draw in and compress a supplemental air flow;

supplying the supplemental air flow to turbine during a first mode of operation to supplemental drive the turbine, and to expand and cool the supplemental air flow for supply thereof with the bleed air as conditioned air to the aircraft cabin;

bypassing the supplemental air flow from the turbine for mixture with the bleed air flow at a position downstream from the turbine during a second mode of operation, and for supply of the mixed bleed and supplemental sir flows as conditioned air to the aircraft cabin;

bifurcating a substantially full circle turbine housing scroll into a pair of generally semi-annular scroll halves, and supplying the bleed and supplemental air flow separately to the scroll halves during said first mode; and

opening the turbine housing scroll for substantially full circle admission of the bleed air flow during said second mode.

14. The method of claim 13 wherein the first mode of operation is relatively low altitude operation of the aircraft, and wherein said second mode of operation is relatively high altitude operation of the aircraft.