TANDEM AIR CYCLE MACHINE MODULE FOR ENVIRONMENTAL CONTROL SYSTEMS
Tandem air cycle machine modules include a first air cycle machine having a first compressor and a first turbine, a second air cycle machine having a second compressor and a second turbine, and a structural manifold operably connected to both the first air cycle machine and the second air cycle machine.
The present application claims priority from U.S. Provisional Patent Application Numbers 62/309,076, 62/309,080, 62/309,081, and 62/309,084, filed on Mar. 16, 2016. The contents of the priority applications are hereby incorporated by reference in their entireties.
BACKGROUNDThe subject matter disclosed herein generally relates to environmental control systems and, more particularly, to air cycle machines of environmental control systems.
Commercial aircraft are conventionally equipped with two-pack environmental control system architectures that include redundant packs installed in separate bays beneath a center wing box of the aircraft and are encapsulated by the aircraft wing-to-body fairing. These bays are commonly separated by a Keel Beam that supports the weight of the aircraft in the event of a wheels-up landing. Local penetrations of the keel beam can be accommodated if properly reinforced.
Smaller configurations of environmental control system architectures can include pack-and-a-half architectures that fit within a single volume. However, such volume is larger than half of the convention two-pack architectures, and thus the pack-and-a-half architecture systems may be too large for use in such locations, and thus may be required to be installed in other locations of the aircraft (e.g., in a tail cone of the aircraft). It may be beneficial to further reduce the size of pack-and-a-half environmental control system architectures.
SUMMARYAccording to one embodiment, a tandem air cycle machine module is provided. The tandem air cycle machine module includes a first air cycle machine having a first compressor and a first turbine, a second air cycle machine having a second compressor and a second turbine, and a structural manifold operably connected to both the first air cycle machine and the second air cycle machine.
In addition to one or more of the features described above, or as an alternative, further embodiments of the tandem air cycle machine module may include an isolation valve within the structural manifold and configured to control an airflow into the first turbine and the second turbine.
In addition to one or more of the features described above, or as an alternative, further embodiments of the tandem air cycle machine module may include that the isolation valve comprises an actuator and a gate, the actuator configured to control and move the gate to selectively block flow into the first turbine or the second turbine.
In addition to one or more of the features described above, or as an alternative, further embodiments of the tandem air cycle machine module may include that the isolation valve further comprises a cover that fixedly connects to the structural manifold, the gate movably mounted to the cover.
In addition to one or more of the features described above, or as an alternative, further embodiments of the tandem air cycle machine module may include that the isolation valve is operable into (i) a first position wherein airflow can enter both the first turbine and the second turbine, (ii) a second position wherein airflow can enter only the first turbine and is prevented from entering the second turbine, and (iii) a third position wherein airflow can enter only the second turbine and is prevented from entering the first turbine.
In addition to one or more of the features described above, or as an alternative, further embodiments of the tandem air cycle machine module may include that the structural manifold includes a manifold inlet configured to receive an airflow from a water collector of an environmental control system of an aircraft.
In addition to one or more of the features described above, or as an alternative, further embodiments of the tandem air cycle machine module may include at least one mounting pad on the structural manifold, the at least one mounting pad configured to mount the structural manifold to a structure of an aircraft.
In addition to one or more of the features described above, or as an alternative, further embodiments of the tandem air cycle machine module may include at least one vibration isolator configured to limit transmission of vibration to or from the tandem air cycle machine.
In addition to one or more of the features described above, or as an alternative, further embodiments of the tandem air cycle machine module may include a plurality of securing mechanisms that connect and secure attachment of the first and second air cycle machines to the structural manifold.
According to another embodiment, an environmental control system of an aircraft is provided. The environmental control system includes a tandem air cycle machine module having a first air cycle machine having a first compressor and a first turbine, a second air cycle machine having a second compressor and a second turbine, and a structural manifold operably connected to both the first air cycle machine and the second air cycle machine.
In addition to one or more of the features described above, or as an alternative, further embodiments of the environmental control system may include an isolation valve within the structural manifold and configured to control an airflow into the first turbine and the second turbine.
In addition to one or more of the features described above, or as an alternative, further embodiments of the environmental control system may include that the isolation valve comprises an actuator and a gate, the actuator configured to control and move the gate to selectively block flow into the first turbine or the second turbine.
In addition to one or more of the features described above, or as an alternative, further embodiments of the environmental control system may include that the isolation valve further comprises a cover that fixedly connects to the structural manifold, the gate movably mounted to the cover.
In addition to one or more of the features described above, or as an alternative, further embodiments of the environmental control system may include that the isolation valve is operable into (i) a first position wherein airflow can enter both the first turbine and the second turbine, (ii) a second position wherein airflow can enter only the first turbine and is prevented from entering the second turbine, and (iii) a third position wherein airflow can enter only the second turbine and is prevented from entering the first turbine.
In addition to one or more of the features described above, or as an alternative, further embodiments of the environmental control system may include that the structural manifold includes a manifold inlet configured to receive an airflow from a water collector of an environmental control system of an aircraft.
In addition to one or more of the features described above, or as an alternative, further embodiments of the environmental control system may include at least one mounting pad on the structural manifold, the at least one mounting pad configured to mount the structural manifold to a structure of an aircraft.
In addition to one or more of the features described above, or as an alternative, further embodiments of the environmental control system may include at least one vibration isolator configured to limit transmission of vibration to or from the tandem air cycle machine.
In addition to one or more of the features described above, or as an alternative, further embodiments of the environmental control system may include a plurality of securing mechanisms that connect and secure attachment of the first and second air cycle machines to the structural manifold.
In addition to one or more of the features described above, or as an alternative, further embodiments of the environmental control system may include a water collector configured to supply conditioned air to the structural manifold.
In addition to one or more of the features described above, or as an alternative, further embodiments of the environmental control system may include a ram module, the ram module configured to receive air from at least one of the first compressor and the second compressor.
Technical effects of embodiments of the present disclosure include tandem air cycle machine modules for environmental control system architectures that include two or more air cycle machines operably coupled to a single central structural manifold. Further technical effects include air cycle machine isolation valves configured to control flow into and through tandem air cycle machine modules of the present disclosure.
The foregoing features and elements may be combined in various combinations without exclusivity, unless expressly indicated otherwise. These features and elements as well as the operation thereof will become more apparent in light of the following description and the accompanying drawings. It should be understood, however, that the following description and drawings are intended to be illustrative and explanatory in nature and non-limiting.
The subject matter is particularly pointed out and distinctly claimed at the conclusion of the specification. The foregoing and other features, and advantages of the present disclosure are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
As shown and described herein, various features of the disclosure will be presented. Various embodiments may have the same or similar features and thus the same or similar features may be labeled with the same reference numeral, but preceded by a different first number indicating the figure to which the feature is shown. Thus, for example, element “##” that is shown in FIG. X may be labeled “X##” and a similar feature in FIG. Z may be labeled “Z##.” Although similar reference numbers may be used in a generic sense, various embodiments will be described and various features may include changes, alterations, modifications, etc. as will be appreciated by those of skill in the art, whether explicitly described or otherwise would be appreciated by those of skill in the art.
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The refrigeration module 204 includes a condenser heat exchanger 216 and one or more air cycle machines 218. The condenser heat exchanger 216 can be operably connected to the secondary heat exchanger 208b by a first duct 206a that can supply hot air to the condenser heat exchanger 216. The air cycle machines 218 can be connected to one or both of the heat exchangers 208a, 208b, as shown. Recirculated air Arecirc can be supplied to and mixed with turbine outlet air from the air cycle machines 218 as indicated in
The condenser heat exchanger 216 is configured to condition air and supply relatively cool or cold air Acabin to a cabin of an aircraft. Thus, the condenser heat exchanger 216 includes an outlet header 220. The hot air that is supplied to the condenser heat exchanger 216 through the duct 206a is fed into an inlet header 222 of the condenser heat exchanger 216.
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The environmental control system 300 includes a ram module 302 and a refrigeration module 304. In some configurations, when installed on an aircraft, the ram module 302 can be installed into a right-hand side of the aircraft, and thus through a first bay door and the refrigeration module 304 can be installed into a left-hand side of the aircraft, and through a second bay door. In
The ram module 302 is operably connected to the refrigeration module 304 by one or more ducts 306a, 306b, 306c. The environmental control system 300 includes a primary heat exchanger 308a and a secondary heat exchanger 308b that receive bleed air Ableed and ram air Aram, respectively, to condition air within the ram module 302. One or more ram fans 314 are configured to aid in exhausting ram exhaust air Aram_exhaust from the ram module 302.
As shown, the refrigeration module 304 includes a condenser heat exchanger 316 and tandem air cycle machines 318a, 318b. Each of the tandem air cycle machines 318a, 318b includes a respective compressor 324a, 324b and a respective turbine 326a, 326b. The tandem air cycle machines 318a, 318b can form a tandem air cycle machine module 328, as indicated by the dashed-line box in
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The isolation valve 532 is configured within the manifold 530 includes a gate 548, a cover 550, an actuator 552, and a fastening mechanism 554. The actuator 552 is mounted to the cover 550 and is configured to control (e.g., rotate, open/close, etc.) the gate 548. The fastening mechanism 554, as shown, comprises multiple fasteners, though those of skill in the art will appreciate that any type of fastening can be used without departing from the scope of the present disclosure. For example, in some embodiments, the fastening mechanism can be achieved by welding, adhesives, interference fits, etc. The gate 548 of the isolation valve 532 is moveable or actuatable to selectively block flow through the turbine inlets 546a, 546b. The gate 548, as shown in the embodiment of
A first position of the gate 548, as controlled by the actuator 552, can be a position such that neither the first turbine inlet 546a nor the second turbine inlet 546b are blocked. That is, in the first position, airflow can flow into both a first turbine and a second turbine of a tandem air cycle machine module. In a second position, the gate 548 moved or positioned to block the second turbine inlet 546b and flow is allowed to flow through the first turbine inlet 546a. In a third position, the gate 548 is moved or positioned to block the first turbine inlet 546a and flow is allowed to flow through the second turbine inlet 546b.
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Advantageously, embodiments described herein provide tandem air cycle machine modules having two air cycle machines and a centralized manifold to form a compact unitized assembly. Various embodiments can be applied to, for example, two, three, or four wheel tandem air cycle machines. In some embodiments, an isolation valve can be integrated into the centralized manifold and control airflow into one or more of the connected air cycle machines. In accordance with some embodiments of the present disclosure, the central, shared manifold can simplify system ducting arrangements by coupling turbine inlet and compressor outlet connections. Furthermore, in some embodiments, a number of mounting points can simplify attachment to aircraft while facilitating the removal and replacement of individual air cycle machines of the tandem air cycle machine module. That is, embodiments provided herein enable a module and separable system wherein various parts or components can be separately removed and/or replaced during maintenance operations. Moreover, in some embodiments, vibration isolators can limit the transmission of structural borne noise to the airframe as well as external loads transmitted to the air cycle machines of the tandem air cycle machine module.
The use of the terms “a,” “an,” “the,” and similar references in the context of description (especially in the context of the following claims) are to be construed to cover both the singular and the plural, unless otherwise indicated herein or specifically contradicted by context. The modifier “about” used in connection with a quantity is inclusive of the stated value and has the meaning dictated by the context (e.g., it includes the degree of error associated with measurement of the particular quantity). All ranges disclosed herein are inclusive of the endpoints, and the endpoints are independently combinable with each other. It should be appreciated that relative positional terms such as “forward,” “aft,” “upper,” “lower,” “above,” “below,” and the like are with reference to normal operational attitude and should not be considered otherwise limiting.
While the present disclosure has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the present disclosure is not limited to such disclosed embodiments. Rather, the present disclosure can be modified to incorporate any number of variations, alterations, substitutions, combinations, sub-combinations, or equivalent arrangements not heretofore described, but which are commensurate with the scope of the present disclosure. Additionally, while various embodiments of the present disclosure have been described, it is to be understood that aspects of the present disclosure may include only some of the described embodiments.
For example, although shown and described with respect to a tandem air cycle machine module having two air cycle machines, various other tandem air cycle machine modules may employ embodiments of the present disclosure. For example, embodiments provided herein can be applied to two, three, or four wheel tandem air cycle machines.
Accordingly, the present disclosure is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.
Claims
1. A tandem air cycle machine module comprising:
- a first air cycle machine having a first compressor and a first turbine;
- a second air cycle machine having a second compressor and a second turbine; and
- a structural manifold operably connected to both the first air cycle machine and the second air cycle machine.
2. The tandem air cycle machine module of claim 1, further comprising an isolation valve within the structural manifold and configured to control an airflow into the first turbine and the second turbine.
3. The tandem air cycle machine module of claim 2, wherein the isolation valve comprises an actuator and a gate, the actuator configured to control and move the gate to selectively block flow into the first turbine or the second turbine.
4. The tandem air cycle machine module of claim 3, the isolation valve further comprising a cover that fixedly connects to the structural manifold, the gate movably mounted to the cover.
5. The tandem air cycle machine module of claim 2, wherein the isolation valve is operable into (i) a first position wherein airflow can enter both the first turbine and the second turbine, (ii) a second position wherein airflow can enter only the first turbine and is prevented from entering the second turbine, and (iii) a third position wherein airflow can enter only the second turbine and is prevented from entering the first turbine.
6. The tandem air cycle machine module of claim 1, wherein the structural manifold includes a manifold inlet configured to receive an airflow from a water collector of an environmental control system of an aircraft.
7. The tandem air cycle machine module of claim 1, further comprising at least one mounting pad on the structural manifold, the at least one mounting pad configured to mount the structural manifold to a structure of an aircraft.
8. The tandem air cycle machine module of claim 1, further comprising at least one vibration isolator configured to limit transmission of vibration to or from the tandem air cycle machine.
9. The tandem air cycle machine module of claim 1, further comprising a plurality of securing mechanisms that connect and secure attachment of the first and second air cycle machines to the structural manifold.
10. An environmental control system of an aircraft, the environmental control system comprising:
- a tandem air cycle machine module comprising: a first air cycle machine having a first compressor and a first turbine; a second air cycle machine having a second compressor and a second turbine; and a structural manifold operably connected to both the first air cycle machine and the second air cycle machine.
11. The environmental control system of claim 10, further comprising an isolation valve within the structural manifold and configured to control an airflow into the first turbine and the second turbine.
12. The environmental control system of claim 11, wherein the isolation valve comprises an actuator and a gate, the actuator configured to control and move the gate to selectively block flow into the first turbine or the second turbine.
13. The environmental control system of claim 12, the isolation valve further comprising a cover that fixedly connects to the structural manifold, the gate movably mounted to the cover.
14. The environmental control system of claim 11, wherein the isolation valve is operable into (i) a first position wherein airflow can enter both the first turbine and the second turbine, (ii) a second position wherein airflow can enter only the first turbine and is prevented from entering the second turbine, and (iii) a third position wherein airflow can enter only the second turbine and is prevented from entering the first turbine.
15. The environmental control system of claim 10, wherein the structural manifold includes a manifold inlet configured to receive an airflow from a water collector of an environmental control system of an aircraft.
16. The environmental control system of claim 10, further comprising at least one mounting pad on the structural manifold, the at least one mounting pad configured to mount the structural manifold to a structure of an aircraft.
17. The environmental control system of claim 10, further comprising at least one vibration isolator configured to limit transmission of vibration to or from the tandem air cycle machine.
18. The environmental control system of claim 10, further comprising a plurality of securing mechanisms that connect and secure attachment of the first and second air cycle machines to the structural manifold.
19. The environmental control system of claim 10, further comprising a water collector configured to supply conditioned air to the structural manifold.
20. The environmental control system of claim 10, further comprising a ram module, the ram module configured to receive air from at least one of the first compressor and the second compressor.
Type: Application
Filed: Aug 17, 2016
Publication Date: Sep 21, 2017
Inventors: Donald E. Army (Enfield, CT), Frederick Peacos, III (North Scituate, RI)
Application Number: 15/239,223