(19)
(11)EP 3 248 878 B1

(12)EUROPEAN PATENT SPECIFICATION

(45)Mention of the grant of the patent:
06.05.2020 Bulletin 2020/19

(21)Application number: 17172834.8

(22)Date of filing:  24.05.2017
(51)Int. Cl.: 
B64D 13/06  (2006.01)

(54)

MIXING BLEED AND RAM AIR USING A DUAL USE TURBINE SYSTEM

MISCHEN VON ZAPF- UND STAU-LUFT UNTER VERWENDUNG EINES TURBINENSYSTEMS MIT DOPPELTER VERWENDUNG

MÉLANGE D'AIR DYNAMIQUE ET D'AIR DE PURGE À L'AIDE D'UN SYSTÈME DE TURBINE À DOUBLE UTILISATION


(84)Designated Contracting States:
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

(30)Priority: 26.05.2016 US 201662341878 P

(43)Date of publication of application:
29.11.2017 Bulletin 2017/48

(73)Proprietor: Hamilton Sundstrand Corporation
Charlotte, NC 28217 (US)

(72)Inventors:
  • BRUNO, Louis J.
    Ellington, CT 06029 (US)
  • HIPSKY, Harold W.
    deceased (US)

(74)Representative: Dehns 
St. Bride's House 10 Salisbury Square
London EC4Y 8JD
London EC4Y 8JD (GB)


(56)References cited: : 
EP-A1- 2 937 287
US-A1- 2003 051 500
US-A- 5 299 763
  
      
    Note: Within nine months from the publication of the mention of the grant of the European patent, any person may give notice to the European Patent Office of opposition to the European patent granted. Notice of opposition shall be filed in a written reasoned statement. It shall not be deemed to have been filed until the opposition fee has been paid. (Art. 99(1) European Patent Convention).


    Description

    BACKGROUND



    [0001] In general, contemporary air condition systems are supplied a pressure at cruise that is approximately 0.21 Mpa (30 psig) to 0.34 Mpa (50 psig). The trend in the aerospace industry today is towards systems with higher efficiency. One approach to improve airplane efficiency is to eliminate the bleed air entirely and use electrical power to compress outside air. A second approach is to use lower engine pressure. The third approach is to use the energy in the bleed air to compress outside air and bring it into the cabin.

    [0002] EP 2937287, US 5,299,763 and US 2003/0051500 relate to air conditioning systems.

    BRIEF DESCRIPTION



    [0003] According to the invention, an airplane according to claim 1 and an airplane according to claim 2 are provided.

    BRIEF DESCRIPTION OF THE DRAWINGS



    [0004] The subject matter is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The forgoing and other features, and advantages thereof are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:

    FIG. 1 is a diagram of an schematic of an environmental control system according to an example;

    FIG. 2 is operation example of an environmental control system that mixes fresh air with bleed air according to an example;

    FIG. 3 is operation example of an environmental control system that mixes fresh air with bleed air, where the environmental control system includes a bleed air driven fan, according to an example;

    FIG. 4 is operation example of an environmental control system that mixes fresh air with bleed air, where the environmental control system includes an electrically driven fan, according to an example;

    FIG. 5 is operation example of an environmental control system that mixes fresh air with bleed air, where the environmental control system includes a fresh air driven fan, according to an example;

    FIG. 6 is operation example of an environmental control system that mixes fresh air with bleed air according to another embodiment;

    FIG. 7 is operation example of an environmental control system that mixes fresh air with bleed air, where the environmental control system includes a bleed air driven fan, according to another embodiment;

    FIG. 8 is operation example of an environmental control system that mixes fresh air with bleed air, where the environmental control system includes an electrically driven fan, according to another embodiment;

    FIG. 9 is operation example of an environmental control system that mixes fresh air with bleed air, where the environmental control system includes a fresh air driven fan, according to another example.


    DETAILED DESCRIPTION



    [0005] A detailed description of one or more examples of the disclosed apparatus are presented herein by way of exemplification and not limitation with reference to the FIGS.

    [0006] Examples herein provide an environmental control system of an aircraft that mixes mediums from different sources and uses the different energy sources to power the environmental control system and to provide cabin pressurization and cooling at a high fuel burn efficiency. The medium can generally be air, while other examples include gases, liquids, fluidized solids, or slurries.

    [0007] Turning to FIG. 1, a system 100 that receives a medium from an inlet 101 and provides a conditioned form of the medium to a chamber 102 is illustrated. The system 100 comprises a compressing device 110. As shown, the compressing device 110 comprises a compressor 112, a turbine 113, a fan 116, and a shaft 118. The system 100 also comprises a primary heat exchanger 120, a secondary heat exchanger 130, a condenser 160, a water extractor 162, and a reheater 164.

    [0008] The compressing device 110 is a mechanical device that includes components for performing thermodynamic work on the medium (e.g., extracts work from or works on the medium by raising and/or lowering pressure and by raising and/or lowering temperature). Examples of the compressing device 110 include an air cycle machine, a three-wheel air cycle machine, a four-wheel air cycle machine, etc.

    [0009] The compressor 112 is a mechanical device that raises the pressure of the medium received from the inlet 101. Examples of compressor types include centrifugal, diagonal or mixed-flow, axial-flow, reciprocating, ionic liquid piston, rotary screw, rotary vane, scroll, diaphragm, air bubble, etc. Further, compressors can be driven by a motor or the medium via the turbine 113.

    [0010] The turbine 113 is mechanical device that drives the compressor 112 and the fan 116 via the shaft 118. The fan 116 (e.g., a ram air fan) is a mechanical device that can force via push or pull methods air through the shell 119 across the heat exchangers 120 and 130 at a variable cooling to control temperatures. The shell 119 receives and directs a medium (such as ram air) through the system 100. In general, ram air is outside air used as a heat sink by the system 100.

    [0011] The heat exchangers 120 and 130 are devices built for efficient heat transfer from one medium to another. Examples of heat exchangers include double pipe, shell and tube, plate, plate and shell, adiabatic wheel, plate fin, pillow plate, and fluid heat exchangers.

    [0012] The condenser 160 and the reheater 164 are particular types of heat exchangers. The water extractor 162 is a mechanical device that performs a process of taking water from the medium. Together, the condenser 160, the water extractor 162, and/or the reheater 164 can combine to be a high pressure water separator.

    [0013] The elements of the system 100 are connected via valves, tubes, pipes, and the like. Valves (e.g., flow regulation device or mass flow valve) are devices that regulate, direct, and/or control a flow of a medium by opening, closing, or partially obstructing various passageways within the tubes, pipes, etc. of the system 100. Valves can be operated by actuators, such that flow rates of the medium in any portion of the system 100 can be regulated to a desired value.

    [0014] As shown in FIG. 1, the medium can flow from an inlet 101 through the system 100 to a chamber 102, as indicated by solid-lined arrows. A vale V1 (e.g., a mass flow control valve) controls the flow of the medium from the inlet 101 to the system 100. Further, a vale V2 controls whether the flow of the medium from the secondary heat exchanger 130 bypasses the condenser 160 in accordance with a mode of the system 100. A combination of components of the system 100 can be referred to as an air conditioning pack or a pack. The pack can begin at a vale V1 and conclude as air exits the condenser 162.

    [0015] The system 100 will now be described in view of the above aircraft example. In the aircraft example, the medium can be air and the system 100 can be an environmental control system. The air supplied to the environmental control system at the inlet 101 can be said to be "bled" from a turbine engine or an auxiliary power unit. When the air is being provided by the turbine engine or the auxiliary power unit connected to the environmental control system, such as from the inlet 101, the air can be referred to as bleed air (e.g., pressurized air that comes from an engine or an auxiliary power unit). The temperature, humidity, and pressure of the bleed air vary widely depending upon a compressor stage and a revolutions per minute of the turbine engine.

    [0016] Turning now to FIG. 2, a schematic of an environmental control system 200 (e.g., an example of system 100), as it could be installed on an aircraft, where in operation the environmental control system 200 mixes fresh air with bleed air, is depicted according to an example. Components of the system 100 that are similar to the environmental control system 200 have been reused for ease of explanation, by using the same identifiers, and are not re-introduced. Alternative components of the environmental control system 200 include a compressing device 210 (that comprises a compressor 212, a turbine 213, a turbine 214, a fan 116, and a shaft 118), an inlet 201, an outlet 202, an outflow valve heat exchanger 230, a water collector 271, and a water collector 272, along with a path for the medium denoted by the dot-dashed line F2 (where the medium can be provided from the chamber 102 into the environmental control system 200).

    [0017] In view of the above aircraft example, when a medium is being provided from the chamber 102 (e.g., air leaving a pressurized volume, cabin of the aircraft, or cabin and flight deck of the aircraft), the medium can be referred as chamber discharge air (also known as pressured air or cabin discharge air). Note that in one or more examples, an exhaust from the environmental control system 200 can be released to ambient air through the shell 119 or sent to the outlet 202 (e.g., a cabin pressure control system).

    [0018] Further, when a medium is being provided from the inlet 201, the medium can be referred to as fresh outside air (also known as fresh air or outside air destined to enter the pressurized volume or chamber 102). The fresh outside air can be procured by one or more scooping mechanisms, such as an impact scoop or a flush scoop. Thus, the inlet 201 can be considered a fresh air inlet.

    [0019] In low altitude operation of the environmental control system 200, high-pressure high-temperature air from either the turbine engine or the auxiliary power unit via inlet 101 through the valve V1 enters the primary heat exchanger 120. The primary heat exchanger 120 cools the pressure high-temperature air to nearly ambient temperature to produce cool high pressure air. This cool high pressure air enters the condenser 160, where it is further cooled by air from the turbines 213 and 214 of the compressing device 210. Upon exiting the condenser 160, the cool high pressure air enters the water extractor 272 so that moisture in the air is removed.

    [0020] The cool high pressure air enters the turbine 213 through a nozzle. The cool high pressure air is expanded across the turbine 213 and work extracted from the cool high pressure air. This extracted work drives the compressor 212 used to compress fresh outside air. This extracted work also drives the fan 216, which is used to move air through the primary heat exchanger 120 and the secondary heat exchanger 130 (also known as ram air heat exchangers).

    [0021] The act of compressing the fresh outside air, heats the fresh outside air. The compressed fresh outside air enters the outflow valve heat exchanger 230 and is cooled by the chamber discharge air to produce cooled compressed fresh outside air. The cooled compressed fresh outside air then enters the secondary heat exchanger 130 and is further cooled to nearly ambient temperature. The air exiting the secondary heat exchanger 130 then enters the water extractor 271, where any free moisture is removed, to produce cool medium pressure air. This cool medium pressure air then enters the turbine 214 through a nozzle. The cool medium pressure air is expanded across the turbine 214 and work extracted from the cool medium pressure air. Note that the chamber discharge air exiting from the outflow valve heat exchanger 230 can then be sent to an outlet 202. The outlet 202 can be a cabin pressure control system that utilized the energy of the chamber discharge air.

    [0022] The two air flows (e.g., the fresh outside air sourcing from 201 and the bleed air sourcing from inlet 101) are mixed downstream of the turbine 213 to produce mixed air. This downstream location can be considered a first mixing point of the environmental control system 200. The mixed air leaves then enters the condenser 160 to cool the bleed air leaving the primary heat exchanger 120. The mixed air is then sent to condition the chamber 102.

    [0023] This low altitude operation can be consider a low altitude mode. The low altitude mode can be used for ground and low altitude flight conditions, such as ground idle, taxi, take-off, and hold conditions.

    [0024] In high altitude operation of the environmental control system 200, the fresh outside air can be mixed downstream of the condenser 160 (rather than downstream of the turbine 213 or at the first mixing point). In this situation, the air exiting the water extractor 271 is the cool medium pressure air. This cool medium pressure air is directed by the valve V2 to downstream of the condenser 160. The location at which this cool medium pressure air mixes with the bleed air, which is sourced from the inlet 101 and exiting the condenser 160, can be considered a second mixing point of the environmental control system 200.

    [0025] This high altitude operation can be considered a high altitude mode. The high altitude mode can be used at high altitude cruise, climb, and descent flight conditions. In the high altitude mode, fresh air aviation requirements for passengers are met by mixing the two air flows (e.g., the fresh outside air sourcing from 201 and the bleed air sourcing from inlet 101). Further, depending on an altitude of the aircraft, an amount of bleed air needed can be reduced. In this way, the environmental control system 200 provides bleed air reduction ranging from 40% to 75% to provide higher efficiencies with respect to engine fuel burn than contemporary airplane air systems.

    [0026] FIGS. 3, 4, and 5 illustrate variations of the environmental control system 200. In general. Turning now to FIG. 3, a schematic of an environmental control system 300 (e.g., an example of the environmental control system 200) is depicted according to an example. Components of the systems 100 and 200 that are similar to the environmental control system 300 have been reused for ease of explanation, by using the same identifiers, and are not re-introduced. Alternative components of the environmental control system 300 include a compressing device

    [0027] 310, which comprises a compressor 312, a turbine 313, a turbine 314, and a shaft 315, and a rotating device 316 (e.g., turbine driven fan), which comprises a turbine 317 and a fan 319, along with a secondary path for the medium sourced from the inlet 101 (e.g., a valve V3 can provide the medium from the inlet 101 to an inlet of the turbine 317).

    [0028] The environmental control system 300 operates similarly to the environmental control system 200 in that different mixing points are utilized based on the mode of operation. In addition, the environmental control system 300 separates the ram air fan (e.g., fan 116) from the air cycle machine (e.g., the compressing device 110) and provides the ram air fan within the rotating device 316. The turbine 317 of the rotating device 316 is powered by the bleed air sourced from the inlet 101 flowing through the valve V3.

    [0029] Turning now to FIG. 4, a schematic of an environmental control system 400 (e.g., an example of the environmental control system 200) is depicted according to an example. Components of the systems 100, 200, and 300 that are similar to the environmental control system 400 have been reused for ease of explanation, by using the same identifiers, and are not re-introduced. Alternative components of the environmental control system 400 include a rotating device 416, which comprises a motor 417 and a fan 419.

    [0030] The environmental control system 400 operates similarly to the environmental control system 200 in that different mixing points are utilized based on the mode of operation. In addition, the environmental control system 400 separates the ram air fan (e.g., fan 116) from the air cycle machine (e.g., the compressing device 110) and provides the ram air fan within the rotating device 416. The motor 417 of the rotating device 416 is powered by electric power.

    [0031] Turning now to FIG. 5, a schematic of an environmental control system 500 (e.g., an example of the environmental control system 200) is depicted according to an example. Components of the systems 100, 200, 300, and 400 that are similar to the environmental control system 500 have been reused for ease of explanation, by using the same identifiers, and are not re-introduced. Alternative components of the environmental control system 400 include a compressing device 510, which comprises a compressor 512, a turbine 513, and a shaft 515, and a rotating device 516, which comprises a motor 517 and a fan 519. Note that the rotating device 516 is along a path of the medium sourced from the inlet 201, such that the rotating device 516 can be supplied this medium or bypassed.

    [0032] The environmental control system 500 operates similarly to the environmental control system 200 in that different mixing points are utilized based on the mode of operation. In addition, the environmental control system 500 separates the ram air fan (e.g., fan 116) from the air cycle machine (e.g., the compressing device 110) and provides the ram air fan within the rotating device 516. The turbine 517 of the rotating device 516 is powered by the fresh air sourced from the inlet 201.

    [0033] Turning now to FIG. 6, a schematic of an environmental control system 600 (e.g., an embodiment of system 100), as it could be installed on an aircraft is depicted according to an embodiment. In operation the environmental control system 600 can provide mixed air from any combination of fresh air, bleed air, and cabin discharge air. Components of the systems 100, 200, 300, 400 and 500 that are similar to the environmental control system 600 have been reused for ease of explanation, by using the same identifiers, and are not re-introduced. Alternative components of the environmental control system 600 include an outlet 601 and a compressing device 610 that comprises a compressor 612, a turbine 613, a turbine 614, a fan 616, and a shaft 618. Alternative components of the environmental control system 600 also include valves V6.1, V6.2, and V6.3. A path is further denoted by the dot-dashed line F6.1 for a flow the medium that is controlled by valve V6.1 to the outlet 601 (e.g., which can be overboard). Another path is denoted by the dot-dashed line F6.2 for a flow the medium that is controlled by valve V6.2 for supplying the cabin discharge air to the valve V6.3 (otherwise the cabin discharge air can be directed overboard through the shell 119). Note that the turbine 614 can be a dual use. A dual use turbine is configured to receive flows of different mediums in the alternative

    [0034] In low altitude operation of the environmental control system 600, high-pressure high-temperature air from either the turbine engine or the auxiliary power unit via inlet 101 through the valve V1 enters the primary heat exchanger 120. The primary heat exchanger 120 cools the pressure high-temperature air to nearly ambient temperature to produce cool high pressure air. This cool high pressure air enters the condenser 160, where it is further cooled by air from the turbines 613 and 614 of the compressing device 610. Upon exiting the condenser 160, the cool high pressure air enters the water extractor 272 so that moisture in the air is removed.

    [0035] The cool high pressure air enters the turbine 613 through a nozzle. The cool high pressure air is expanded across the turbine 613 and work extracted from the cool high pressure air. This extracted work drives the compressor 612 used to compress fresh outside air. This extracted work also drives the fan 616, which is used to move air through the primary heat exchanger 120 and the secondary heat exchanger 130.

    [0036] The act of compressing the fresh outside air, heats the fresh outside air. The compressed fresh outside air enters the outflow valve heat exchanger 230 and is cooled by the chamber discharge air to produce cooled compressed fresh outside air. The cooled compressed fresh outside air then enters the secondary heat exchanger 130 and is further cooled to nearly ambient temperature. The air exiting the secondary heat exchanger 130 then enters the water extractor 271, where any free moisture is removed, to produce cool medium pressure air. This cool medium pressure air then enters the turbine 614 through a nozzle. The cool medium pressure air is expanded across the turbine 614 and work extracted from the cool high pressure air.

    [0037] The two air flows (e.g., the fresh outside air sourcing from 201 and the bleed air sourcing from inlet 101) are mixed downstream of the turbine 613 to produce mixed air. A valve V6.1 can then be used to direct an outlet of the turbine 614 away from the chamber or to downstream of the turbine 613 (to provide the cool medium pressure air exiting the turbine 614 to the first mixing point such that it flows to the chamber 102). This downstream location can be considered a first mixing point of the environmental control system 600. The mixed air leaves then enters the condenser 160 to cool the bleed air leaving the primary heat exchanger 120. The mixed air is then sent to condition the chamber 102.

    [0038] This low altitude operation can be consider a low altitude mode. The low altitude mode can be used for ground and low altitude flight conditions, such as ground idle, taxi, take-off, and hold conditions.

    [0039] In high altitude operation of the environmental control system 600, the fresh outside air can be mixed downstream of the condenser 160 (rather than at the first mixing point). In this situation, the air exiting the water extractor 271 is the cool medium pressure air. This cool medium pressure air is directed by the valve V6.3 to downstream of the condenser 160.

    [0040] The valve V6.3 can also direct the cabin discharge air to the turbine 614. For instance, energy in the cabin discharge air can be used to power the compressor 612 by feeding (e.g., the dot-dashed line F6.2) the cabin discharge air to the turbine 614. Note that the cabin discharge air enters the turbine 614 through a nozzle such that the turbine 614 expands hot air from the outflow valve heat exchanger 230. The cabin discharge air can continue overboard (e.g., to outlet 601) through valve V6.1. Overboard comprise an ambient pressure at high altitude operation. By the cabin discharge air continuing to overboard, a pressure drop across the turbine 614 is created such that the cabin discharge air is drawn though the turbine 614 (e.g., cabin discharge air pressure is higher than ambient air pressure). In this way, the compressor 612 receives power from both the bleed air (across the turbine 613) and the cabin discharge air (across the turbine 614).

    [0041] This high altitude operation can be considered a high altitude mode. The high altitude mode can be used at high altitude cruise, climb, and descent flight conditions. In the high altitude mode, fresh air aviation requirements for passengers are met by mixing the two air flows (e.g., the fresh outside air sourcing from 201 and the bleed air sourcing from inlet 101). Further, depending on an altitude of the aircraft, an amount of bleed air needed can be reduced. In this way, the environmental control system 200 provides bleed air reduction ranging from 40% to 60% to provide higher efficiencies with respect to engine fuel burn than contemporary airplane air systems.

    [0042] FIGS. 7, 8, and 9 illustrate variations of the environmental control system 600. In general. Turning now to FIG. 7, a schematic of an environmental control system 700 (e.g., an embodiment of the environmental control system 600) is depicted according to an embodiment. Components of the systems 100, 200, 300, 400, 500, and 600 that are similar to the environmental control system 700 have been reused for ease of explanation, by using the same identifiers, and are not re-introduced. Alternative components of the environmental control system 700 include a compressing device 710, which comprises a compressor 712, a turbine 713, a turbine 714, and a shaft 715. Note that the turbine 614 is a dual use.

    [0043] The environmental control system 700 operates similarly to the environmental control system 600 in that different mixing points are utilized based on the mode of operation. In addition, the environmental control system 700 separates the ram air fan (e.g., fan 116) from the air cycle machine (e.g., the compressing device 110) and provides the ram air fan within the rotating device 316. The turbine 317 of the rotating device 316 is powered by the bleed air sourced from the inlet 101 flowing through the valve V3.

    [0044] Further, energy in the fresh air exiting from the water extractor 271 can be used to power the compressor 712 by feeding the air exiting the water extractor 271 via the valve V6.3 to the turbine 714. Furthermore, energy in the cabin discharge air exiting from the outflow valve heat exchanger 230 can be used to power the compressor 712 by feeding (e.g., the dot-dashed line F6.2) the cabin discharge air to the turbine 714. In this way, the second turbine 714 can be fed air from the outflow valve heat exchanger 230 (e.g., cabin discharge air) and/or air exiting the water extractor 271 (e.g., fresh outside air), while the first turbine 713 can be fed air from the primary heat exchanger 120 (e.g., bleed air). In turn, the compressor 712 can receive power from the bleed air (via turbine 713), the cabin discharge air (via turbine 714), and/or the fresh outside air (also via turbine 714). Note that the cabin discharge air or the fresh outside air can be mixed with the bleed air downstream of the turbine 713.

    [0045] Turning now to FIG. 8, a schematic of an environmental control system 800 (e.g., an embodiment of the environmental control system 600) is depicted according to an embodiment. Components of the systems 100, 200, 300, 400, 500, 600, and 700 that are similar to the environmental control system 800 have been reused for ease of explanation, by using the same identifiers, and are not re-introduced.

    [0046] The environmental control system 800 operates similarly to the environmental control system 600 in that different mixing points are utilized based on the mode of operation. In addition, the environmental control system 800 separates the ram air fan (e.g., fan 116) from the air cycle machine (e.g., the compressing device 110) and provides the ram air fan within the rotating device 416. The motor 717 of the rotating device 716 is powered by electric power.

    [0047] Turning now to FIG. 9, a schematic of an environmental control system 900 (e.g., an example of the environmental control system 600) is depicted according to an example. Components of the systems 100, 200, 300, 400, 500, 600, 700, and 800 that are similar to the environmental control system 900 have been reused for ease of explanation, by using the same identifiers, and are not re-introduced. Alternative components of the environmental control system 900 include a path for the medium denoted by the dot-dashed line F9 (where the medium can be provided from the chamber 102 to the turbine 714).

    [0048] The environmental control system 900 operates similarly to the environmental control system 600 in that different mixing points are utilized based on the mode of operation. In addition, the environmental control system 900 separates the ram air fan (e.g., fan 116) from the air cycle machine (e.g., the compressing device 110) and provides the ram air fan within the rotating device 516. The turbine 517 of the rotating device 516 is powered by the fresh air sourced from the inlet 201. Note that the rotating device 516 is along a path of the medium sourced from the inlet 201, such that the rotating device 516 can be supplied this medium or bypassed based on the operation of valve V5. In addition, Note in one or more embodiments, an exhaust from the turbine 714 can be sent to the outlet 601 (e.g., a cabin pressure control system) after the turbine 714 extracts work from the medium received from path F9.

    [0049] The scope of the invention is defined by the appended claims.


    Claims

    1. An airplane comprising:

    a pressurized volume; and

    an air conditioning system comprising:

    a compressor (612) configured to receive a flow of a first medium comprising fresh air,

    a turbine (614) downstream of the compressor in a flow path of the first medium,

    a first valve configured to divert the flow of the first medium around the turbine,

    a second valve configured to provide a second medium comprising cabin discharge air to the turbine,

    a third valve downstream of the turbine configured to direct an outlet flow of the turbine towards the pressurized volume and to direct the outlet flow of the turbine away from the pressurized volume;

    characterised in that the air conditioning system further comprises

    a second turbine (613) configured to receive a third medium comprising bleed air

    wherein the first medium is mixed with the third medium downstream of the second turbine (613).


     
    2. An airplane comprising:

    a pressurized volume; and

    an air conditioning system comprising:

    a compressor (612) configured to receive a flow of a first medium comprising fresh air,

    a turbine (614) downstream of the compressor in a flow path of the first medium,

    a first valve configured to divert the flow of the first medium around the turbine and configured to provide a second medium comprising cabin discharge air to the turbine, and

    a second valve downstream of the turbine configured to direct an outlet flow of the turbine towards the pressurized volume and to direct the outlet flow of the turbine away from the pressurized volume;

    characterised in that the air conditioning system further comprises

    a second turbine (613) configured to receive a third medium comprising bleed air

    wherein the first medium is mixed with the third medium downstream of the second turbine (613).


     


    Ansprüche

    1. Flugzeug, Folgendes umfassend:

    ein unter Druck stehendes Volumen; und

    ein Klimaanlagensystem, das Folgendes umfasst:

    einen Kompressor (612), der dazu konfiguriert ist, eine Strömung eines ersten Mediums aufzunehmen, das Frischluft umfasst,

    eine Turbine (614), die sich stromabwärts des Kompressors in einem Strömungspfad des ersten Mediums befindet,

    ein erstes Ventil, das dazu konfiguriert ist, eine Strömung des ersten Mediums um eine Turbine herumzuleiten,

    ein zweites Ventil, das dazu konfiguriert ist, der Turbine ein zweites Medium bereitzustellen, das Kabinenabluft umfasst,

    ein drittes Ventil, das sich stromabwärts von der Turbine befindet und dazu konfiguriert ist, eine Auslassströmung der Turbine zu dem unter Druck stehenden Volumen hinzuleiten und die Auslassströmung der Turbine von dem unter Druck stehenden Volumen fortzuleiten;

    dadurch gekennzeichnet, dass das Klimaanlagensystem ferner eine zweite Turbine (613) umfasst, die dazu konfiguriert ist, ein drittes Medium aufzunehmen, das Zapfluft umfasst, wobei das erste Medium stromabwärts von der zweiten Turbine (613) mit dem dritten Medium vermischt wird.


     
    2. Flugzeug, Folgendes umfassend:

    ein unter Druck stehendes Volumen; und

    ein Klimaanlagensystem, das Folgendes umfasst:

    einen Kompressor (612), der dazu konfiguriert ist, eine Strömung eines ersten Mediums aufzunehmen, das Frischluft umfasst,

    eine Turbine (614), die sich stromabwärts von dem Kompressor in einem Strömungspfad des ersten Mediums befindet, ein erstes Ventil, das dazu konfiguriert ist, die Strömung des ersten Mediums um die Turbine herumzuleiten und das dazu konfiguriert ist, der Turbine ein zweites Medium bereitzustellen, das Kabinenabluft umfasst, und

    ein zweites Ventil, das sich stromabwärts der Turbine befindet und dazu konfiguriert ist, eine Auslassströmung der Turbine zu dem unter Druck stehenden Volumen hinzuleiten und die Auslassströmung der Turbine von dem unter Druck stehenden Volumen fortzuleiten;

    dadurch gekennzeichnet, dass das Klimaanlagensystem ferner eine zweite Turbine (613) umfasst, die dazu konfiguriert ist, ein drittes Medium aufzunehmen, das Zapfluft umfasst, wobei das erste Medium stromabwärts von der zweiten Turbine (613) mit dem dritten Medium vermischt wird.


     


    Revendications

    1. Avion comprenant :

    un volume pressurisé ; et

    un système de climatisation comprenant :

    un compresseur (612) conçu pour recevoir un écoulement d'un premier milieu comprenant de l'air frais,

    une turbine (614) en aval du compresseur dans un chemin d'écoulement du premier milieu,

    une première vanne conçue pour dérouter l'écoulement du premier milieu autour de la turbine,

    une deuxième vanne conçue pour fournir un deuxième milieu comprenant de l'air d'évacuation de cabine à la turbine,

    une troisième vanne en aval de la turbine conçue pour diriger un écoulement de sortie de la turbine vers le volume pressurisé et pour diriger l'écoulement de sortie de la turbine en éloignement du volume pressurisé ;

    caractérisé en ce que le système de climatisation comprend en outre une seconde turbine (613) conçue pour recevoir un troisième milieu comprenant de l'air de purge dans lequel le premier milieu est mélangé au troisième milieu en aval de la seconde turbine (613).


     
    2. Avion comprenant :

    un volume pressurisé ; et

    un système de climatisation comprenant :

    un compresseur (612) conçu pour recevoir un écoulement d'un premier milieu comprenant de l'air frais,

    une turbine (614) en aval du compresseur dans un chemin d'écoulement du premier milieu,

    une première vanne conçue pour dérouter l'écoulement du premier milieu autour de la turbine et conçue pour fournir un deuxième milieu comprenant de l'air d'évacuation de cabine à la turbine, et

    une deuxième vanne en aval de la turbine conçue pour diriger un écoulement de sortie de la turbine vers le volume pressurisé et pour diriger l'écoulement de sortie de la turbine en éloignement du volume pressurisé ;

    caractérisé en ce que le système de climatisation comprend en outre
    une seconde turbine (613) conçue pour recevoir un troisième milieu comprenant de l'air de purge dans lequel le premier milieu est mélangé au troisième milieu en aval de la seconde turbine (613).


     




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    REFERENCES CITED IN THE DESCRIPTION



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    Patent documents cited in the description