Patent Application
20240067344
Embodiments of the disclosure relate to environmental control systems, and more specifically to an environmental control system (ECS) of an aircraft.
Aircraft need to have their internal environment controlled. In general, contemporary air conditioning 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 efficiency of an aircraft environmental control system is to eliminate the bleed air entirely and use electrical power to compress outside air. A second approach is to use lower engine pressure and thus, pressure to the inlet of the ECS. The third approach is to use the energy in the cabin outflow air to compress outside air and bring it into the cabin. Each of these approaches provides a reduction in airplane fuel burn.
According to an embodiment, an environmental control system of a vehicle includes an inlet for receiving a medium, an outlet for delivering a conditioned form of the medium to a load, a primary heat exchanger fluidly coupled to the inlet and a secondary heat exchanger. A thermodynamic device is fluidly coupled to the primary heat exchanger and the secondary heat exchanger. A first bypass conduit has a first bypass inlet arranged upstream from the primary heat exchanger and a first bypass outlet arranged upstream from the secondary heat exchanger. A first bypass valve is operable to control a flow of medium through the first bypass conduit. During operation in a first mode, the medium is configured to flow through the primary heat exchanger and the secondary heat exchanger in series. During operation in a second mode, the medium is configured to flow through the primary heat exchanger and the secondary heat exchanger in parallel.
In addition to one or more of the features described above, or as an alternative, in further embodiments the first bypass outlet is arranged downstream from a portion of the thermodynamic device.
In addition to one or more of the features described above, or as an alternative, in further embodiments the thermodynamic device further includes a compressor having a compressor outlet and a turbine operably coupled by a shaft. The first bypass outlet is arranged downstream from the compressor outlet.
In addition to one or more of the features described above, or as an alternative, in further embodiments including a second bypass conduit having a second bypass inlet arranged upstream from the thermodynamic device and a second bypass outlet arranged directly upstream from the outlet. A second bypass valve is operable to control the flow of medium through the second bypass conduit.
In addition to one or more of the features described above, or as an alternative, in further embodiments the second bypass inlet is arranged downstream from the primary heat exchanger.
In addition to one or more of the features described above, or as an alternative, in further embodiments the first bypass valve and the second bypass valve are independently operable.
In addition to one or more of the features described above, or as an alternative, in further embodiments the first bypass valve and the second bypass valve are operable in combination.
In addition to one or more of the features described above, or as an alternative, in further embodiments the thermodynamic device includes a compressor having a compressor inlet and at least one turbine operably coupled by a shaft. The second bypass inlet is arranged upstream from the compressor inlet.
In addition to one or more of the features described above, or as an alternative, in further embodiments the at least one turbine further includes a first turbine and a second turbine and the flow of medium provided to the second bypass conduit is configured to bypass the compressor, the first turbine and the second turbine.
In addition to one or more of the features described above, or as an alternative, in further embodiments further including a ram air circuit including a ram air shell. The primary heat exchanger and the secondary heat exchanger are arranged within the ram air shell.
In addition to one or more of the features described above, or as an alternative, in further embodiments the medium is bleed air.
In addition to one or more of the features described above, or as an alternative, in further embodiments the vehicle is an aircraft.
According to an embodiment, a method of operating an environmental control system of a vehicle includes supplying a medium to a primary heat exchanger and a secondary heat exchanger in series during a first mode of operation, and supplying a first portion of the medium to the primary heat exchanger and supplying a second portion of the medium to the secondary heat exchanger in parallel during a second mode of operation.
In addition to one or more of the features described above, or as an alternative, in further embodiments supplying the second portion of the medium to the secondary heat exchanger further includes adjusting a position of a first bypass valve associated with a first bypass conduit such that the second portion of the medium is provided to the first bypass conduit.
In addition to one or more of the features described above, or as an alternative, in further embodiments supplying the second portion of the medium to the secondary heat exchanger further comprises bypassing a portion of a thermodynamic device.
In addition to one or more of the features described above, or as an alternative, in further embodiments including directing at least part of the first portion of the medium into a second bypass conduit to bypass a thermodynamic device.
In addition to one or more of the features described above, or as an alternative, in further embodiments the first portion of the medium is directed into the second bypass conduit downstream from the primary heat exchanger.
In addition to one or more of the features described above, or as an alternative, in further embodiments the thermodynamic device includes a compressor and at least one turbine operably coupled by a shaft and the first portion of the medium bypasses the compressor and the at least one turbine.
In addition to one or more of the features described above, or as an alternative, in further embodiments including directing at least part of the second portion of the medium to bypass a thermodynamic device.
In addition to one or more of the features described above, or as an alternative, in further embodiments supplying the medium further comprises receiving bleed air from a bleed air system.
The following descriptions should not be considered limiting in any way. With reference to the accompanying drawing, like elements are numbered alike:
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 Figure.
Embodiments herein provide an environmental control system of an aircraft that mixes mediums from different 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.
With reference now to the Figures, schematic diagrams of a portion of an environment control system (ECS) 20, such as an air conditioning unit or pack for example, are depicted according to non-limiting embodiments. Although the environmental control system 20 is described with reference to an aircraft, alternative applications are also within the scope of the disclosure. As shown in each of the FIGS., the ECS 20 has an inlet 22 configured to receive a medium A from a source 24. The environmental control system 20 is configured to deliver a conditioned form of the medium A to a load 26, such as a cabin for example. In embodiments where the ECS 20 is used in an aircraft application, the medium A may be bled air, which is pressurized air originating from i.e. being “bled” from, an engine or auxiliary power unit of the aircraft. It shall be understood that one or more of the temperature, humidity, and pressure of the bleed air provided via a bleed air system 24 can vary based upon the compressor stage and revolutions per minute of the engine or auxiliary power unit from which the air is drawn.
In other embodiments, the medium A provided to the inlet 22 may be fresh air, such as outside air for example. The outside air can be procured via one or more scooping mechanisms, such as an impact scoop or a flush scoop for example. In such embodiments, the fresh air as described herein is at an ambient pressure equal to an air pressure outside of the aircraft when the aircraft is on the ground and is between an ambient pressure and a cabin pressure when the aircraft is in flight. Alternatively, the medium A may be provided from the cabin of the aircraft In such embodiments the medium is cabin discharge air, which is air leaving the cabin and that would typically be discharged overboard. In yet another embodiment, the medium A is provided from a cabin air compressor located upstream from the inlet 22. It should be understood that a medium A including a mixture of any of the mediums described herein or a may be provided from another suitable source of the aircraft is also within the scope of the disclosure.
The ECS 20 includes a RAM air circuit 30 having a shell or duct, illustrated schematically in broken lines at 32, within which one or more heat exchangers are located. The ram air shell 32 can receive and direct a medium, such as ram air for example, through a portion of the ECS 20. The one or more heat exchangers are devices built for efficient heat transfer from one medium to another. Although the heat exchangers are illustrated as having a single pass configuration, it should be appreciated that in other embodiments, at least one of the mediums may make multiple passes through the heat exchanger. Further, the mediums may be arranged in any suitable flow configuration at the heat exchanger, such as cross-flow, parallel flow, counter-flow, or any combination thereof. Examples of the type of heat exchangers that may be used, include, but are not limited to, double pipe, shell and tube, plate, plate and shell, adiabatic shell, plate fin, pillow plate, and fluid heat exchangers.
The one or more heat exchangers arranged within the shell 32 may be referred to as ram heat exchangers. In the illustrated, non-limiting embodiment, the ram heat exchangers include a first or primary heat exchanger 34 and a second or secondary heat exchanger 36. Although two heat exchangers are illustrated, it should be understood that embodiments including a single heat exchanger, or alternatively, embodiments including more than two heat exchangers are also contemplated herein. Within the heat exchangers 34, 36, ram air, such as outside air for example, acts as a heat sink to cool the medium passing there through.
The ECS 20 additionally comprises at least one thermodynamic device 40. In the illustrated, non-limiting embodiments, the ECS 20 includes a single thermodynamic device 40; however, embodiments including additional thermodynamic devices are also within the scope of the disclosure. In the illustrated, non-limiting embodiment, the thermodynamic device 40 is a mechanical device that includes components for performing thermodynamic work on a medium (e.g., extracts work from or applies work to the medium A by raising and/or lowering pressure and/or by raising and/or lowering temperature). Examples of a thermodynamic device 40 include an air cycle machine, a two-wheel air cycle machine, a three-wheel air cycle machine, a four-wheel air cycle machine, etc. In the illustrated, non-limiting embodiment, the thermodynamic device 40 is a four-wheel air cycle machine.
The thermodynamic device 40 includes a compressor 42 and at least one turbine 44 operably coupled to each other via a shaft 46. The compressor 42 is a mechanical device that raises a pressure of a medium and can be driven by another mechanical device (e.g., a motor or a medium via a turbine). 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. The turbine 44 is a mechanical device that expands a medium and extracts work therefrom (also referred to as extracting energy) to drive the compressor 42 via the shaft 46. In the illustrated, non-limiting embodiment, the thermodynamic device 40 includes a first turbine 44a and a second turbine 44b.
In an embodiment, the thermodynamic device 40 includes a fan 48 mounted to the shaft 46. The fan 48 is a mechanical device that can force via push or pull methods a medium (e.g., ram air) through the shell 32 across the one or more ram heat exchangers 34, 36 and at a variable cooling flow rate to control temperatures. As shown, the first turbine 44a and the second turbine 44b are operable independently or in combination, to drive the compressor 42 and the fan 48 via the shaft 46. Although the fan 48 is illustrated as being part of the four-wheel air cycle machine that forms the thermodynamic device 40, in other embodiments, the fan 48 may be separate from the thermodynamic device 40 and driven by another suitable means. In such instances, the fan 48 may be electrically driven, may be a tip-turbine fan, or may be part of a separate simple cycle machine.
The ECS 20 may additionally include a dehumidification system. In the illustrated, non-limiting embodiment of
The elements of the ECS 20 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. Valves can be operated by actuators, such that flow rates of the medium in any portion of the ECS 20 can be regulated to a desired value. It should be appreciated that the valves may be operated independently or in combination to form a medium A having a desired temperature and pressure at the outlet 64. For instance, a first valve V1 may be operable to control the supply of the medium A to the ECS 20. In an embodiment, a second valve is arranged within a conduit 60 extending between an outlet 62 of the secondary heat exchanger 36 and the outlet 64 of the ECS 20 (or directly upstream therefrom) such that when the second valve V2 is open, at least a portion of the medium A output from the secondary heat exchanger 36 bypasses the turbines 44a, 44b and the dehumidification system.
In embodiments where the thermodynamic device 40 includes a plurality of turbines 44, the ECS 20 may include at least one valve to allow the medium A to bypass at least one of the turbines 44. For example, in the non-limiting embodiment of
With continued reference to
The outlet 72 of the compressor 42 is fluidly connected to an inlet 74 of the secondary heat exchanger 36 by at least one conduit 76. The compressed medium A′ output from the compressor 42 is therefore provided to the secondary heat exchanger 36 where the compressed medium A′ is again cooled via the flow of ram air. From the outlet of the 62 of the secondary heat exchanger 36, the compressed medium A′ flows into conduit 60. Because valve V2 is closed during normal operation, the cool compressed medium A′ is configured to flow to the dehumidification system.
With reference to
Similarly, in the embodiment shown in
From the reheater 50 of the embodiment of
In the illustrated, non-limiting embodiments, each ECS 20 includes a first bypass conduit or passage 100 arranged in parallel with the primary heat exchanger 34 and the compressor 42. As shown, the first bypass conduit 100 has a first bypass inlet 102 arranged upstream from the inlet 104 of the primary heat exchanger 34 and a first bypass outlet 106 arranged downstream from the compressor outlet 72. A first bypass valve V5 is operable to control the flow of medium A into the first bypass conduit 100. In the illustrated, non-limiting embodiment, the valve V5 is located at a central portion of the first bypass conduit 100. In such embodiments, the valve V5 may be a simple valve transformable between an open and closed position. It should be understood that embodiments where the valve V5 is arranged another location, such as at either the first bypass inlet or outlet of the first bypass conduit 100 are also within the scope of the disclosure.
By positioning the valve V5 at the inlet end 102 of the first bypass conduit 100, the valve V5 may be controlled to direct the entire flow of medium A into the first bypass conduit 100. In such embodiments, the valve V5 may be a three way valve movable between a first position configured to direct all of the flow of the medium 1 to the primary heat exchanger 34, a second position configured to direct all of the flow of the medium A to the first bypass conduit 100, and a third position configured to direct a first portion of the flow of the medium A to the primary heat exchanger 34 and a second portion of the flow of the medium A to the first bypass conduit 100.
Alternatively, or in addition, the ECS 20 may include a second bypass conduit or passage 108 configured to bypass the remainder of the ECS 20 located downstream from the primary heat exchanger 34. As shown, the second bypass conduit 108 has a second bypass inlet 110 fluidly coupled to the conduit 66 at a location upstream from the inlet 70 of the compressor 42. A second bypass outlet 112108 is located at or directly upstream from the outlet 64 of the ECS 20. A second bypass valve V6 is operable to control the flow of medium A into the second bypass conduit 108. In the illustrated, non-limiting embodiment, the valve V6 is located at a central portion of the second bypass conduit 108. In such embodiments, the valve V6 may be a simple valve transformable between an open and closed position. It should be understood that embodiments where the valve V6 is arranged another location, such as at the second bypass inlet 110 or second bypass outlet 112 of the second bypass conduit 108, are also within the scope of the disclosure.
Similar to valve V5 described above, by positioning the valve V6 at the inlet end 110 of the second bypass conduit 108, the valve V6 may be controlled to direct the entire flow of medium A into the second bypass conduit 108. In such embodiments, the valve V6 may be a three way valve movable between a first position configured to direct all of the flow of the medium A to the compressor 42, a second position configured to direct all of the flow of the medium A to the second bypass conduit 108, and a third position configured to direct a first portion of the flow of the medium A to the compressor 42 and a second portion of the flow of the medium A to the second bypass conduit 108.
During operation of the ECS 20 in the first mode, valves V5 and V6 are closed, such that the flow of medium A follows the flow path previously described. In this normal of first mode of operation, the medium A is provided to the primary and secondary heat exchangers 34, 36 in series. For the conditioned medium A provided to the outlet 64 to have adequate flow, the pressure of the medium A provided to the inlet 22 must be sufficient to overcome the pressure drop of both the heat exchangers 34, 36 as well as the pressure drop of all other components between the inlet 22 and the outlet 64. Accordingly, during the first mode of operation, the medium A may be provided from a high-pressure spool of an engine via a bleed air system.
In a second mode of operation, such as when the aircraft is at altitude or in a cruise condition, valve V5 is opened such that at least a portion medium A is configured to bypass the primary heat exchanger 34 and the compressor 42. In this partially open configuration, the medium A is provided to the primary heat exchanger 34 and the secondary heat exchanger 36 in parallel. Further, in an embodiment, valve V6 may be at least partially opened such that some or all of the medium A output from the primary heat exchanger 34 is directed into the second bypass conduit 108, thereby bypassing the remaining components of the ECS 20. Alternatively, or in addition, the valve V2 may be opened such that at least a portion of the medium A provided at the outlet 62 of the secondary heat exchanger 36 is configured to bypass the remaining component of the system via the conduit 60. The two flows of the medium A may then mix before being delivered to the one or more loads 26 via the outlet of the ECS 20. At least one of the valves V2 and V6 may be positioned such that a portion of the flow of medium A is provided to one or more components of the thermodynamic device 40, such as the compressor 42 and at least one turbine 44a, 44b. In an embodiment, the flow of medium A provided to the thermodynamic device 40 is the minimum amount required to operate the thermodynamic device 40 to avoid failure thereof and noise.
Because the medium A is only provided to a single heat exchanger of the ram air heat exchangers, and in some embodiments bypasses the other components of the ECS 20, during the second mode, the pressure drop of the medium A within the ECS 20 is reduced. As a result, the pressure of the medium A provided to the inlet 22 may be lowered. Accordingly, in an embodiment, the pressure of the medium A provided to the inlet 22 during operation in the second mode is less than the pressure of the medium A provided to the inlet during operation in the first mode. For example, the medium A may be provided from a low-pressure spool of an engine via the bleed air system during the second mode. It should be understood that the pressure of the air drawn from the low-pressure spool is less than the pressure of the air drawn from a high-pressure spool.
As previously noted, the environmental control system 20 illustrated and described herein is intended as an example only. It should be understood that any environmental control system having a primary and secondary heat exchanger 34, 36 may be adapted to include at least the first bypass conduit and a corresponding valve, to selectively provide the flow of a medium A to the primary and secondary heat exchangers 34, 36 in series and in parallel.
The term “about” is intended to include the degree of error associated with measurement of the particular quantity based upon the equipment available at the time of filing the application.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the present disclosure. 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 or more other features, integers, steps, operations, element components, and/or groups thereof.
While the present disclosure has been described with reference to an exemplary embodiment or embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the present disclosure. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the present disclosure without departing from the essential scope thereof. Therefore, it is intended that the present disclosure not be limited to the particular embodiment disclosed as the best mode contemplated for carrying out this present disclosure, but that the present disclosure will include all embodiments falling within the scope of the claims.
This application claims the benefit of U.S. Provisional Application No. 63/401,848 filed Aug. 29, 2022, the disclosure of which is incorporated herein by reference in its entirety.
| Number | Date | Country | |
|---|---|---|---|
| 63401848 | Aug 2022 | US |
