US20190002110A1 - Mixing bleed and ram air using an air cycle machine with two turbines - Google Patents
Mixing bleed and ram air using an air cycle machine with two turbines Download PDFInfo
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- US20190002110A1 US20190002110A1 US16/110,163 US201816110163A US2019002110A1 US 20190002110 A1 US20190002110 A1 US 20190002110A1 US 201816110163 A US201816110163 A US 201816110163A US 2019002110 A1 US2019002110 A1 US 2019002110A1
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- air
- turbine
- medium
- control system
- environmental control
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D13/08—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned the air being heated or cooled
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/02—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being pressurised
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/105—Final actuators by passing part of the fluid
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
- F04D25/045—Units comprising pumps and their driving means the pump being fluid-driven the pump wheel carrying the fluid driving means, e.g. turbine blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
- F04D29/053—Shafts
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0618—Environmental Control Systems with arrangements for reducing or managing bleed air, using another air source, e.g. ram air
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0644—Environmental Control Systems including electric motors or generators
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0648—Environmental Control Systems with energy recovery means, e.g. using turbines
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0688—Environmental Control Systems with means for recirculating cabin air
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/60—Fluid transfer
- F05D2260/606—Bypassing the fluid
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/50—On board measures aiming to increase energy efficiency
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- Y02T50/56—
Abstract
An air cycle machine for an environmental control system for an aircraft is provided. The air cycle machine includes a compressor configured to compress a first medium, a turbine configured to receive second medium, a mixing point downstream of the compressor and downstream of the turbine; and a shaft mechanically coupling the compressor and the turbine.
Description
- This application claims benefit of U.S. patent application Ser. No. 15/604,496, filed May 24, 2017 which claims benefit of priority to U.S. Provisional Application No. 62/341,887, filed May 26, 2016, the disclosure of which is incorporated herein by reference in its entirety
- In general, contemporary air condition systems are supplied a pressure at cruise that is approximately 30 psig to 35 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.
- According to one or more embodiments, an air cycle machine for an environmental control system for an aircraft is provided. The air cycle machine includes a compressor configured to compress a first medium; a turbine configured to receive second medium; a mixing point downstream of the compressor and downstream of the turbine; and a shaft mechanically coupling the compressor and the turbine.
- According to one or more embodiments or the above air cycle machine embodiment, the air cycle machine can comprise a fan on the shaft.
- According to one or more embodiments or any of the above air cycle machine embodiments, the fan can be located at a first end of the shaft.
- According to one or more embodiments or any of the above air cycle machine embodiments, the air cycle machine can comprise a second turbine mounted on the shaft and can be configured to expand the first medium.
- According to one or more embodiments or any of the above air cycle machine embodiments, the turbine can be located at the first end of the shaft.
- According to one or more embodiments or any of the above air cycle machine embodiments, the air cycle machine can comprise a fan on the shaft, and the fan can be located at a second end of the shaft.
- According to one or more embodiments or any of the above air cycle machine embodiments, the second turbine can be configured to receive a third medium, and the third medium can be cabin discharge air.
- According to one or more embodiments or any of the above air cycle machine embodiments, the first medium can comprise fresh air, and the second medium can comprise bleed air.
- According to one or more embodiments, an air conditioning system for an aircraft is provided. The air conditioning system comprises a compressor configured to compress a first medium; a turbine configured to receive a second medium; a mixing point downstream of the compressor and downstream of the turbine; and a shaft mechanically coupling the compressor and the turbine.
- According to one or more embodiments or the above air conditioning system embodiment, the air conditioning system can comprise a second turbine mounted on the shaft and configured to expand the first medium.
- According to one or more embodiments or any of the above air conditioning system embodiments, the air conditioning system can comprise a fan driven by a third turbine driven by the second medium.
- According to one or more embodiments or any of the above air conditioning system embodiments, the air conditioning system can comprise an integral rotor comprising the third turbine and the fan.
- According to one or more embodiments or any of the above air conditioning system embodiments, the air conditioning system can comprise a second shaft mechanically coupling the fan and the third turbine.
- According to one or more embodiments or any of the above air conditioning system embodiments, the air conditioning system can comprise a fan driven by a motor.
- According to one or more embodiments or any of the above air conditioning system embodiments, the second turbine can be configured to receive a third medium, and wherein the third medium is cabin discharge air.
- According to one or more embodiments or any of the above air conditioning system embodiments, the air conditioning system can comprise a second turbine configured to expand the first medium to drive a fan.
- According to one or more embodiments or any of the above air conditioning system embodiments, the air conditioning system can comprise an integral rotor comprising the second turbine and the fan.
- According to one or more embodiments or any of the above air conditioning system embodiments, the air conditioning system can comprise a third turbine mounted on the shaft and configure to receive cabin discharge air.
- According to one or more embodiments or any of the above air conditioning system embodiments, the air conditioning system can comprise a second shaft mechanically coupling the fan and the second turbine.
- According to one or more embodiments or any of the above air conditioning system embodiments, the second turbine can be configured to receive a third medium, and the third medium can be cabin discharge air.
- Additional features and advantages are realized through the techniques of the embodiments herein. Other embodiments are described in detail herein and are considered a part of the claims. For a better understanding of the embodiments with the advantages and the features, refer to the description and to the drawings.
- 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:
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FIG. 1 is a diagram of an schematic of an environmental control system according to an embodiment; -
FIG. 2 is operation example of an environmental control system that mixes fresh air with bleed air according to an embodiment; -
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 embodiment; -
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 embodiment; -
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 embodiment; -
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 embodiment. - A detailed description of one or more embodiments of the disclosed apparatus and method are presented herein by way of exemplification and not limitation with reference to the FIGS.
- Embodiments 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.
- Turning to
FIG. 1 , asystem 100 that receives a medium from aninlet 101 and provides a conditioned form of the medium to achamber 102 is illustrated. Thesystem 100 comprises acompressing device 110. As shown, thecompressing device 110 comprises acompressor 112, aturbine 113, afan 116, and ashaft 118. Thesystem 100 also comprises aprimary heat exchanger 120, asecondary heat exchanger 130, acondenser 160, awater extractor 162, and areheater 164. - 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 thecompressing device 110 include an air cycle machine, a three-wheel air cycle machine, a four-wheel air cycle machine, etc. - The
compressor 112 is a mechanical device that raises the pressure of the medium received from theinlet 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 theturbine 113. - The
turbine 113 is mechanical device that drives thecompressor 112 and thefan 116 via theshaft 118. The fan 116 (e.g., a ram air fan) is a mechanical device that can force via push or pull methods air through theshell 119 across theheat exchangers shell 119 receives and directs a medium (such as ram air) through thesystem 100. In general, ram air is outside air used as a heat sink by thesystem 100. - The
heat exchangers - The
condenser 160 and thereheater 164 are particular types of heat exchangers. Thewater extractor 162 is a mechanical device that performs a process of taking water from the medium. Together, thecondenser 160, thewater extractor 162, and/or thereheater 164 can combine to be a high pressure water separator. - 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 thesystem 100. Valves can be operated by actuators, such that flow rates of the medium in any portion of thesystem 100 can be regulated to a desired value. - As shown in
FIG. 1 , the medium can flow from aninlet 101 through thesystem 100 to achamber 102, as indicated by solid-lined arrows. A vale V1 (e.g., a mass flow control valve) controls the flow of the medium from theinlet 101 to thesystem 100. Further, a vale V2 controls whether the flow of the medium from thesecondary heat exchanger 130 bypasses thecondenser 160 in accordance with a mode of thesystem 100. A combination of components of thesystem 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 thecondenser 162. - The
system 100 will now be described in view of the above aircraft embodiment. In the aircraft embodiment, the medium can be air and thesystem 100 can be an environmental control system. The air supplied to the environmental control system at theinlet 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 theinlet 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. - Turning now to
FIG. 2 , a schematic of an environmental control system 200 (e.g., an embodiment of system 100), as it could be installed on an aircraft, where in operation theenvironmental control system 200 mixes fresh air with bleed air, is depicted according to an embodiment. Components of thesystem 100 that are similar to theenvironmental control system 200 have been reused for ease of explanation, by using the same identifiers, and are not re-introduced. Alternative components of theenvironmental control system 200 include a compressing device 210 (that comprises acompressor 212, aturbine 213, aturbine 214, afan 116, and a shaft 118), aninlet 201, anoutlet 202, an outflowvalve heat exchanger 230, awater collector 271, and awater collector 272, along with a path for the medium denoted by the dot-dashed line F2 (where the medium can be provided from thechamber 102 into the environmental control system 200). - In view of the above aircraft embodiment, 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 embodiments, an exhaust from the
environmental control system 200 can be released to ambient air through theshell 119 or sent to the outlet 202 (e.g., a cabin pressure control system). - 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, theinlet 201 can be considered a fresh air inlet. - 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 viainlet 101 through the valve V1 enters theprimary heat exchanger 120. Theprimary 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 thecondenser 160, where it is further cooled by air from theturbines compressing device 210. Upon exiting thecondenser 160, the cool high pressure air enters thewater extractor 272 so that moisture in the air is removed. - The cool high pressure air enters the
turbine 213 through a nozzle. The cool high pressure air is expanded across theturbine 213 and work extracted from the cool high pressure air. This extracted work drives thecompressor 212 used to compress fresh outside air. This extracted work also drives thefan 216, which is used to move air through theprimary heat exchanger 120 and the secondary heat exchanger 130 (also known as ram air heat exchangers). - 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 thesecondary heat exchanger 130 and is further cooled to nearly ambient temperature. The air exiting thesecondary heat exchanger 130 then enters thewater extractor 271, where any free moisture is removed, to produce cool medium pressure air. This cool medium pressure air then enters theturbine 214 through a nozzle. The cool medium pressure air is expanded across theturbine 214 and work extracted from the cool high pressure air. Note that the chamber discharge air exiting from the outflowvalve heat exchanger 230 can then be sent to anoutlet 202. Theoutlet 202 can be a cabin pressure control system that utilized the energy of the chamber discharge air. - 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 theenvironmental control system 200. The mixed air leaves then enters thecondenser 160 to cool the bleed air leaving theprimary heat exchanger 120. The mixed air is then sent to condition thechamber 102. - 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.
- 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 theturbine 113 or at the first mixing point). In this situation, the air exiting thewater extractor 271 is the cool medium pressure air. This cool medium pressure air is directed by the valve V2 to downstream of thecondenser 160. The location at which this cool medium pressure air mixes with the bleed air, which is sourced from theinlet 101 and exiting thecondenser 160, can be considered a second mixing point of theenvironmental control system 200. - 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. -
FIGS. 3, 4, and 5 illustrate variations of theenvironmental control system 200. Turning now toFIG. 3 , a schematic of an environmental control system 300 (e.g., an embodiment of the environmental control system 200) is depicted according to an embodiment. Components of thesystems environmental control system 300 have been reused for ease of explanation, by using the same identifiers, and are not re-introduced. Alternative components of theenvironmental control system 300 include acompressing device 310, which comprises acompressor 312, aturbine 313, aturbine 314, and ashaft 315, and a rotating device 316 (e.g., turbine driven fan), which comprises aturbine 317 and afan 319, along with a secondary path for the medium sourced from the inlet 101 (e.g., a valve V3 can provide the medium from theinlet 101 to an inlet of the turbine 317). - The
environmental control system 300 operates similarly to theenvironmental control system 200 in that different mixing points are utilized based on the mode of operation. In addition, theenvironmental 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 therotating device 316. Theturbine 317 of therotating device 316 is powered by the bleed air sourced from theinlet 101 flowing through the valve V3. - Turning now to
FIG. 4 , a schematic of an environmental control system 400 (e.g., an embodiment of the environmental control system 200) is depicted according to an embodiment. Components of thesystems environmental control system 400 have been reused for ease of explanation, by using the same identifiers, and are not re-introduced. Alternative components of theenvironmental control system 400 include arotating device 416, which comprises amotor 417 and afan 419. - The
environmental control system 400 operates similarly to theenvironmental control system 200 in that different mixing points are utilized based on the mode of operation. In addition, theenvironmental 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 therotating device 416. Themotor 417 of therotating device 416 is powered by electric power. - Turning now to
FIG. 5 , a schematic of an environmental control system 500 (e.g., an embodiment of the environmental control system 200) is depicted according to an embodiment. Components of thesystems environmental control system 500 have been reused for ease of explanation, by using the same identifiers, and are not re-introduced. Alternative components of theenvironmental control system 400 include acompressing device 510, which comprises acompressor 512, aturbine 513, and ashaft 515, and arotating device 516, which comprises amotor 517 and afan 519. Note that therotating device 516 is along a path of the medium sourced from theinlet 201, such that therotating device 516 can be supplied this medium or bypassed. - The
environmental control system 500 operates similarly to theenvironmental control system 200 in that different mixing points are utilized based on the mode of operation. In addition, theenvironmental 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 therotating device 516. Theturbine 517 of therotating device 516 is powered by the fresh air sourced from theinlet 201. - 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 theenvironmental control system 600 can provide mixed air from any combination of fresh air, bleed air, and cabin discharge air. Components of thesystems environmental control system 600 have been reused for ease of explanation, by using the same identifiers, and are not re-introduced. Alternative components of theenvironmental control system 600 include anoutlet 601 and acompressing device 610 that comprises a compressor 612, aturbine 613, aturbine 614, afan 616, and ashaft 618. Alternative components of theenvironmental 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 theturbine 614 can be a dual use. A dual use turbine is configured to receive flows of different mediums in the alternative. - 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 viainlet 101 through the valve V1 enters theprimary heat exchanger 120. Theprimary 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 thecondenser 160, where it is further cooled by air from theturbines compressing device 610. Upon exiting thecondenser 160, the cool high pressure air enters thewater extractor 272 so that moisture in the air is removed. - The cool high pressure air enters the
turbine 613 through a nozzle. The cool high pressure air is expanded across theturbine 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 thefan 616, which is used to move air through theprimary heat exchanger 120 and thesecondary heat exchanger 130. - 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 thesecondary heat exchanger 130 and is further cooled to nearly ambient temperature. The air exiting thesecondary heat exchanger 130 then enters thewater extractor 271, where any free moisture is removed, to produce cool medium pressure air. This cool medium pressure air then enters theturbine 614 through a nozzle. The cool medium pressure air is expanded across theturbine 614 and work extracted from the cool high pressure air. - 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 theturbine 614 away from the chamber or to downstream of the turbine 613 (to provide the cool medium pressure air exiting theturbine 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 theenvironmental control system 600. The mixed air leaves then enters thecondenser 160 to cool the bleed air leaving theprimary heat exchanger 120. The mixed air is then sent to condition thechamber 102. - 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.
- 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 thewater extractor 271 is the cool medium pressure air. This cool medium pressure air is directed by the valve V6.3 to downstream of thecondenser 160. - 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 theturbine 614. Note that the cabin discharge air enters theturbine 614 through a nozzle such that theturbine 614 expands hot air from the outflowvalve 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 theturbine 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). - 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. -
FIGS. 7, 8, and 9 illustrate variations of theenvironmental control system 600. Turning now toFIG. 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 thesystems environmental control system 700 have been reused for ease of explanation, by using the same identifiers, and are not re-introduced. Alternative components of theenvironmental control system 700 include acompressing device 710, which comprises acompressor 712, aturbine 713, aturbine 714, and ashaft 715. Note that theturbine 614 is a dual use. - The
environmental control system 700 operates similarly to theenvironmental control system 600 in that different mixing points are utilized based on the mode of operation. In addition, theenvironmental 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 therotating device 316. Theturbine 317 of therotating device 316 is powered by the bleed air sourced from theinlet 101 flowing through the valve V3. - Further, energy in the fresh air exiting from the
water extractor 271 can be used to power thecompressor 712 by feeding the air exiting thewater extractor 271 via the valve V6.3 to theturbine 714. Furthermore, energy in the cabin discharge air exiting from the outflowvalve heat exchanger 230 can be used to power thecompressor 712 by feeding (e.g., the dot-dashed line F6.2) the cabin discharge air to theturbine 714. In this way, the additional orsecond turbine 714 can be fed air from the outflow valve heat exchanger 230 (e.g., cabin discharge air) or air exiting the water extractor 271 (e.g., fresh outside air), while thefirst turbine 713 can be fed air from the primary heat exchanger 120 (e.g., bleed air). In turn, thecompressor 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 theturbine 713. - 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 thesystems environmental control system 800 have been reused for ease of explanation, by using the same identifiers, and are not re-introduced. - The
environmental control system 800 operates similarly to theenvironmental control system 600 in that different mixing points are utilized based on the mode of operation. In addition, theenvironmental 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 therotating device 416. The motor 717 of the rotating device 716 is powered by electric power. - Turning now to
FIG. 9 , a schematic of an environmental control system 900 (e.g., an embodiment of the environmental control system 600) is depicted according to an embodiment. Components of thesystems environmental control system 900 have been reused for ease of explanation, by using the same identifiers, and are not re-introduced. Alternative components of theenvironmental control system 900 include a path for the medium denoted by the dot-dashed line F9 (where the medium can be provided from thechamber 102 to the turbine 714). - The
environmental control system 900 operates similarly to theenvironmental control system 600 in that different mixing points are utilized based on the mode of operation. In addition, theenvironmental 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 therotating device 516. Theturbine 517 of therotating device 516 is powered by the fresh air sourced from theinlet 201. Note that therotating device 516 is along a path of the medium sourced from theinlet 201, such that therotating 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 theturbine 714 can be sent to the outlet 202 (e.g., a cabin pressure control system) after theturbine 714 extracts work from the medium received from path F9. - Aspects of the embodiments are described herein with reference to flowchart illustrations, schematics, and/or block diagrams of methods, apparatus, and/or systems according to embodiments. Further, the descriptions of the various embodiments have been presented for purposes of illustration, but are not intended to be exhaustive or limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments. The terminology used herein was chosen to best explain the principles of the embodiments, the practical application or technical improvement over technologies found in the marketplace, or to enable others of ordinary skill in the art to understand the embodiments disclosed herein.
- The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting. As used herein, the singular forms “a”, “an” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprises” and/or “comprising,” when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one more other features, integers, steps, operations, element components, and/or groups thereof.
- The flow diagrams depicted herein are just one example. There may be many variations to this diagram or the steps (or operations) described therein without departing from the spirit of embodiments herein. For instance, the steps may be performed in a differing order or steps may be added, deleted or modified. All of these variations are considered a part of the claims.
- While the preferred embodiment has been described, it will be understood that those skilled in the art, both now and in the future, may make various improvements and enhancements which fall within the scope of the claims which follow. These claims should be construed to maintain the proper protection.
Claims (14)
1. An air cycle machine for an environmental control system for an aircraft, the air cycle machine comprising:
a compressor configured to compress a first medium;
a turbine configured to receive second medium;
a mixing point downstream of the compressor and downstream of the turbine;
a shaft mechanically coupling the compressor and the turbine;
a second turbine mounted on the shaft and configured to expand the first medium; and
a fan driven by a motor.
2. The air cycle machine of claim 1 , further comprising the fan on a second shaft.
3. The air cycle machine of claim 2 , wherein the fan is located at a first end of the second shaft.
4. The air cycle machine of claim 3 , wherein a third turbine is located at a first end of the shaft.
5. The air cycle machine of claim 4 , further comprising the fan located at a second end of the shaft.
6. The air cycle machine of claim 3 , wherein the second turbine is configured to receive a third medium, and
wherein the third medium is cabin discharge air.
7. The air cycle machine of claim 1 , wherein the first medium comprises fresh air, and
wherein the second medium comprises bleed air.
8. An air conditioning system for an aircraft comprising:
a compressor configured to compress a first medium;
a turbine configured to receive a second medium;
a mixing point downstream of the compressor and downstream of the turbine; and
a shaft mechanically coupling the compressor and the turbine;
a second turbine mounted on the shaft and configured to expand the first medium; and
a fan driven by a motor.
9. The air conditioning system of claim 8 , further comprising the fan on a second shaft.
10. The air conditioning system of claim 9 , wherein the fan is located at a first end of the second shaft.
11. The air conditioning system of claim 10 , wherein a third turbine is located at a first end of the shaft.
12. The air conditioning system of claim 11 , further comprising the fan located at a second end of the shaft.
13. The air conditioning system of claim 10 , wherein the second turbine is configured to receive a third medium, and
wherein the third medium is cabin discharge air.
14. The air conditioning system of claim 8 , wherein the first medium comprises fresh air, and
wherein the second medium comprises bleed air.
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US16/110,163 US20190002110A1 (en) | 2016-05-26 | 2018-08-23 | Mixing bleed and ram air using an air cycle machine with two turbines |
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US16/110,163 US20190002110A1 (en) | 2016-05-26 | 2018-08-23 | Mixing bleed and ram air using an air cycle machine with two turbines |
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2017
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BR102017011083B1 (en) | 2024-01-16 |
CN107444655B (en) | 2022-06-10 |
EP3248879B1 (en) | 2021-06-30 |
US20190002111A1 (en) | 2019-01-03 |
BR102017011083A2 (en) | 2017-12-12 |
CA2968735A1 (en) | 2017-11-26 |
US20170341765A1 (en) | 2017-11-30 |
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EP3248879A1 (en) | 2017-11-29 |
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