Turbomachine with separate collector

Abstract

The present application relates to turbomachinery with a separate collector. Disclosed is turbomachinery, such as an air dynamometer, that includes a radial flow out compressor and a gas collector. In some examples, the gas collector is designed as a separate component that is coupled to the machine, such as to the frame. In some examples, the collector and frame are intentionally spaced apart and coupled at discrete points to minimize the transfer of mechanical and thermal energy between the collector and frame. Aspects of the present disclosure also include turbomachinery that includes at least one impeller bypass flow path for directly transferring air between the environment and a location in the collector downstream of the impeller blades. In some examples, such a flow path can allow external ambient air to flow into the collector.

Description

[0001] This application is a divisional application of the application filed on January 19, 2019, with application number 201980008373.4 and invention title "Turbine with Separate Collector".

[0002] Relevant application data

[0003] This application claims the benefit of priority to U.S. Provisional Patent Application No. 62 / 619,514, filed January 19, 2018, entitled “Radial Outflow Compressor with Separate Impeller Housing and High-Energy Gas Collector,” and U.S. Provisional Patent Application No. 62 / 634,609, filed February 23, 2018, entitled “Air Dynamometer,” each of which is incorporated herein by reference in its entirety. Invention Field

[0004] This invention generally relates to the field of turbomachinery. Specifically, this invention relates to turbines having a decoupled collector. background

[0005] A compressor is a type of turbine designed to transfer energy to a working fluid via a rotating impeller. The higher-energy fluid typically flows from the impeller into a collector. In some prior art designs, the collector and impeller are housed in a common casing. The working fluid is then typically guided to a pipe or conduit via the container's outlet flange.

[0006] Overview of this disclosure

[0007] In one embodiment, this disclosure relates to a turbine. The turbine includes a compressor comprising an impeller having a plurality of blades rotatably supported by a frame; and a collector coupled to the frame and fluidly coupled to the impeller to collect air discharged from the impeller; wherein the collector is supported by the frame independently of the compressor.

[0008] In another embodiment, this disclosure relates to a turbine. The turbine includes a compressor having an impeller with a plurality of blades rotatably supported by a frame; and a collector coupled to the frame and operatively coupled to the impeller to collect air discharged from the impeller; wherein the turbine includes at least one impeller bypass flow path for directly transferring air between the environment and a location within the collector downstream of the impeller blades.

[0009] In another embodiment, this disclosure relates to a method of manufacturing a turbine including a collector, a frame, and a compressor having an impeller with a plurality of impeller blades. The method includes providing mechanical and thermal attenuation between the collector, compressor, and frame by independently supporting the collector and compressor by the frame, to minimize the transfer of mechanical and thermal energy between the collector and compressor during operation.

[0010] Various aspects of this disclosure may be implemented in one or more of the embodiments described below.

[0011] 1) A turbine, comprising:

[0012] A compressor, the compressor including an impeller having multiple blades, the impeller being rotatably supported by a frame; and

[0013] A collector, which is coupled to the frame and fluidly coupled to the impeller, to collect the air discharged by the impeller;

[0014] The collector is supported by the frame independently of the compressor.

[0015] 2) The turbine according to 1), wherein the collector is attached to the frame at a plurality of discrete attachment points.

[0016] 3) The turbine according to 2), wherein the collector is connected to the frame by at least one mounting bracket located at one of the discrete attachment points.

[0017] 4) The turbine according to 3), wherein the at least one mounting bracket comprises a vibration-damping elastic material.

[0018] 5) The turbine according to 1), wherein the collector is coupled to the frame and suspended from the frame.

[0019] 6) The turbine according to 1), wherein the frame includes at least two transverse members, wherein the collector is suspended from at least one of the at least two transverse members.

[0020] 7) The turbine according to 1), wherein at least one outer wall of the collector is adjacent to, faces, and spaced apart from the frame.

[0021] 8) The turbine according to claim 1), wherein the impeller extends through the collector and the plurality of blades are located within the collector.

[0022] 9) The turbine according to 8), wherein the collector includes an annular inlet and the compressor further includes a shroud movably disposed in the annular inlet.

[0023] 10) The turbine according to 1), wherein the collector is not structurally supported by the compressor.

[0024] 11) A turbine according to any one of 1)-10), wherein the frame includes a base and two opposing vertical supports extending from the base, the impeller includes a shaft rotatably coupled to the vertical supports, wherein the collector is located between the two opposing vertical supports and surrounds the blades.

[0025] 12) A turbine according to any one of 1)-11), wherein the impeller extends through the collector and is offset from the centerline of the collector.

[0026] 13) The turbine according to any one of 1)-12), wherein the collector and the frame are made of different materials.

[0027] 14) A turbine according to any one of 1)-13), wherein the collector includes at least one impeller bypass flow path for directly transferring air between the environment and a location in the collector downstream of the blades.

[0028] 15) The turbine according to 14), wherein the at least one impeller bypass flow path is located at the interface between the collector and the impeller shroud.

[0029] 16) The turbine according to 14), wherein the collector includes an annular inlet, the turbine further includes at least one shroud disposed adjacent to the blades and located in the annular inlet, wherein the at least one flow path is located between the annular inlet and the shroud.

[0030] 17) The turbine according to 14), wherein the turbine is designed to generate negative pressure, thereby drawing ambient air into the collector through the at least one impeller bypass flow path.

[0031] 18) A turbine according to any one of 1)-17), wherein the turbine is an air force gauge.

[0032] 19) The turbine according to 18), wherein the collector has an asymmetrical shape and the impeller is offset from the centerline of the collector.

[0033] 20) A turbine according to any one of 1)-17), wherein the turbine is a compressor.

[0034] 21) A turbine, comprising:

[0035] A compressor, the compressor including an impeller having multiple blades, the impeller being rotatably supported by a frame; and

[0036] A collector, which is coupled to the frame and operably coupled to the impeller, to collect air discharged by the impeller;

[0037] The turbine includes at least one impeller bypass flow path for directly transferring air between the environment and a location within the collector downstream of the blades.

[0038] 22) The turbine according to 21), wherein the at least one impeller bypass flow path is located at the interface between the collector and the impeller shroud.

[0039] 23) The turbine of claim 21), wherein the collector includes an annular inlet, the turbine further includes at least one shroud disposed adjacent to the blades and located in the annular inlet, wherein the at least one flow path is located between the annular inlet and the shroud.

[0040] 24) The turbine according to 21), wherein the turbine is designed to generate negative pressure, thereby drawing ambient air into the collector through the at least one impeller bypass flow path.

[0041] 25) The turbine according to 21), wherein the collector is supported by the frame independently of the compressor.

[0042] 26. The turbine according to any one of 21)-25), wherein the collector is connected to the frame by at least one mounting bracket located at one of the discrete attachment points.

[0043] 27. The turbine according to 26), wherein the at least one mounting bracket comprises a vibration-damping elastic material.

[0044] 28. The turbine according to any one of 21)-25), wherein the collector is coupled to and suspended from the frame.

[0045] 29) The turbine according to any one of 21)-25), wherein the frame comprises at least two transverse members, wherein the collector is suspended from at least one of the at least two transverse members.

[0046] 30) The turbine according to any one of 21)-29), wherein at least one outer wall of the collector is adjacent to, faces, and spaced apart from the frame.

[0047] 31) A turbine according to any one of 21)-30), wherein the impeller extends through the collector and the plurality of blades are located within the collector.

[0048] 32) A turbine according to any one of 21)-31), wherein the frame includes a base and two opposing vertical supports extending from the base, the impeller includes a shaft rotatably coupled to the vertical supports, wherein the collector is located between the two opposing vertical supports and surrounds the blades.

[0049] 33) A turbine according to any one of 21)-32), wherein the impeller extends through the collector and is offset from the centerline of the collector.

[0050] 34) The turbine according to any one of 21)-33), wherein the collector and the frame are made of different materials.

[0051] 35) A turbine according to any one of 21)-34), wherein the turbine is an air force gauge.

[0052] 36) The turbine according to 35), wherein the collector has an asymmetrical shape and the impeller is offset from the centerline of the collector.

[0053] 37) A turbine according to any one of 21)-34), wherein the turbine is a compressor.

[0054] 38) A method of manufacturing a turbine, the turbine comprising a collector, a frame, and a compressor having an impeller having a plurality of impeller blades, the method comprising:

[0055] By independently supporting the collector and the compressor by the frame, mechanical and thermal attenuation is provided between the collector, the compressor and the frame to minimize the transfer of mechanical and thermal energy between the collector and the compressor during operation.

[0056] 39) The method according to 38) further includes incorporating at least one impeller bypass flow path for directly transferring air between the environment and a location in the collector downstream of the impeller blades. Brief description of the attached diagram

[0057] For the purpose of illustrating the invention, the accompanying drawings show aspects of one or more embodiments of the invention. However, it should be understood that the invention is not limited to the precise arrangements and mechanisms shown in the drawings, wherein:

[0058] Figure 1It is a perspective view of an air force gauge including a compressor and a collector, which are independently connected to and supported by the frame.

[0059] Figure 2 yes Figure 1 A cross-sectional perspective view of an air force gauge;

[0060] Figure 3 yes Figure 1 and Figure 2 A perspective view of an air force gauge;

[0061] Figure 4 yes Figure 3 A perspective view of the collector;

[0062] Figure 5 yes Figure 1 and Figure 2 Perspective view of the frame;

[0063] Figure 6 yes Figure 1 A front cross-sectional view of the air force gauge, showing the movable shield in the fully closed position;

[0064] Figure 7 yes Figure 1 A close-up front cross-sectional view of the air force gauge in the image;

[0065] Figure 8 yes Figure 1 Another close-up front cross-sectional view of the air force gauge in the image;

[0066] Figure 9 This is a perspective view of another example of a collector manufactured according to this disclosure;

[0067] Figure 10 It is connected to the frame. Figure 9 A perspective cross-sectional view of the collector; and

[0068] Figure 11 yes Figure 1 A diagram illustrating the computational fluid dynamics calculations of the airflow within the collector. Detailed description

[0069] This disclosure includes aspects of a turbine (such as an air force gauge) comprising a radially discharging compressor and a gas collector. In some examples, the gas collector is designed as a separate component coupled to the machine, such as to a frame. The collector and compressor may be independently supported by the frame. In some examples, the collector and frame are intentionally spaced apart and coupled at discrete points to minimize the transfer of mechanical and thermal energy between the collector and the frame. This disclosure also includes a turbine comprising at least one flow path for directly transferring air between the environment and a location in the collector downstream of the impeller blades. In some examples, such a flow path may facilitate the inflow of ambient air into the machine.

[0070] Turbines with a separate collector design offer several benefits. For example, high compressor outlet velocities (e.g., supersonic) can cause vibrations in the collector. By providing a separate collector, the transmission of collector vibrations from the collector to the rest of the machine, such as impeller shaft bearings, is minimized. Furthermore, high gas temperatures at the impeller outlet (e.g., above 400 degrees Fahrenheit) can cause thermal stresses in the collector. A separate collector design allows for easier management of such thermal stresses and minimizes their transmission to the rest of the machine. Manufacturing costs can also be reduced by designing the collector as a separate component attached to the machine. For example, lower-cost materials, such as sheet metal, can be used, and tolerances can be lower. By incorporating a flow path for direct airflow between the environment and the location within the collector, cool ambient air can be drawn into the collector, minimizing thermal stresses caused by hot gas leaving the compressor. Additionally, at least one flow path can be located at the interface between the collector and the impeller shroud, eliminating the need for a sealed interface and further reducing manufacturing costs. In some examples, the impeller and collector are designed such that during use, the pressure (e.g., static pressure) at the impeller outlet is lower than atmospheric pressure, for example, in the range of about -47379 Pa to about -641 Pa (gauge pressure), thereby facilitating the transfer of unsealed interfaces and cooled ambient air into the collector.

[0071] Figure 1An exemplary embodiment of an air force gauge 100 manufactured according to the present disclosure is illustrated. The air force gauge 100 includes a collector 102 and a compressor 103 coupled to a frame 104. The frame 104 has a U-shaped or yoke-shaped configuration including a base 106 and two opposing vertical supports 108a, 108b extending vertically from the base. In the illustrated example, the base 106 has a first end 110 and a second end 112, and the vertical supports 108a, 108b extend from the first end to the second end along the entire length of the base. The vertical supports 108a, 108b are spaced apart from each other, defining a space 114 between them, and the collector 102 is located in this space, positioned above the base 110, and coupled to the frame 104. The collector 102 is configured as a separate component from the frame 104 and coupled to the frame at discrete attachment points, as described below. In the illustrated example, collector 102 and frame 104 are made of different materials. For example, frame 104 may be made of cast iron, which can provide vibration damping benefits, and collector 102 may be formed of sheet metal. In other examples, collector 102 and frame 104 may be formed of the same type of material.

[0072] Figure 2 This is a perspective cross-sectional view of the air force gauge 100. As shown, the compressor 103 includes an impeller 202 having an impeller shaft 204 rotatably connected to vertical supports 108a, 108b. The impeller 202 also includes a plurality of impeller blades 206. Figure 2 (Only one is marked in the text). Figure 2 As shown, the impeller 202 extends through the collector 102, with the impeller blades 206 located within the collector. (See below for reference.) Figure 6 In more detail, the compressor also includes an adjustable shroud 610, a bearing assembly 604, and a shroud adjustment assembly 612.

[0073] Figure 3 This is a perspective side view of collector 102 and impeller 202. Collector 102 includes a front wall 302 and a rear wall 304, as well as a curved bottom wall 306, and also includes opposing side walls 308, 310, which together define an internal volume for collecting air discharged by impeller 202. Collector 102 also includes a flange 312 located at collector outlet 313 for connection to a downstream duct (not shown) and an internal partition wall 314 dividing the collector's internal volume into two volumes. Side walls 308, 310 include annular inlets 316, 402 (see...). Figure 4 ).like Figure 3As shown, the impeller 202 is offset by an offset distance d1 from the centerline 318 of the collector, resulting in the impeller blades 206 (see...) Figure 2 The collector is closer to the front wall 302 than the rear wall 304, and is spaced a first distance d2 from the front wall and a second distance d3 from the rear wall, the first distance being smaller than the second distance. As described below, this offset design can result in improved aerodynamic performance, including a reduced gas velocity at the collector outlet 313, which can reduce noise and vibration.

[0074] Figure 4 This is a perspective view of collector 102 and also illustrates mounting bracket 404 configured to attach the collector to the frame at a plurality of discrete attachment points. In the illustrated example, mounting bracket 404 includes a first base mounting bracket 404a and a second base mounting bracket 404b for supporting the collector on the base 110 of frame 104 and attaching the collector to the base (see [reference]). Figure 1 Mounting bracket 404 also includes front mounting brackets 404c, 404d, 404e and three rear mounting brackets (only rear mounting bracket 404f is shown). The front mounting brackets 404c, 404d, 404e are configured to attach the collector to the front cross brace 116 of the frame 104 (see [link to image]). Figure 1 , Figure 5 The rear mounting bracket is used to attach the collector to the rear crossbar 502 of the frame (see...). Figure 5 The width Wc of collector 102 is less than the length of space 114 between the opposing vertical supports 108a and 108b (see...). Figure 1 This provides spacings S1 and S2 between the sidewalls 308 and 310 and the adjacent vertical supports. Figure 6Such spacings S1, S2 facilitate separation of collector 102 from frame 104 to minimize the transfer of mechanical and thermal energy between the collector and frame. Mounting bracket 404 extends between collector 102 and frame 104, thereby providing a relatively small number of attachment points between the collector and frame to minimize the transfer of mechanical and thermal energy. In some examples, one or more of mounting brackets 404 may also include vibration-damping elastic members (not shown). For example, at least one layer of any type of elastic material known in the art for providing vibration damping, such as one or more layers of natural rubber, synthetic rubber, or polymer foam. Mounting bracket 404 may also be designed to allow some movement of the collector to allow for thermal expansion of the collector. Mounting brackets may be designed as isolation mounts or may include isolation mounts, such as elastomers, springs, or hydraulic isolation mounts. The individual design allows vibrations in collector 102 to be sufficiently damped, such that the remaining components of the system, including impeller shaft bearing 606 ( Figure 6 The arrangement will not be adversely affected. It also allows for the thermal expansion of the collector (which may be made of sheet metal), and the support 404 can also be designed to provide a radiator function for removing heat from the collector. Figure 5 This is a perspective view of frame 104, illustrating the yoke configuration of the frame, which has vertical supports 108a and 108b extending vertically from the base 110, and a front crossbar 116 and a rear crossbar 502 extending between the vertical supports.

[0075] Figure 6This is a front cross-sectional view of the air force gauge 100. As shown, the compressor 103 includes an impeller 202, which is a radially outflow impeller in the illustrated example. The impeller includes a hub 600 and a plurality of impeller blades 602 (only four blades 602a, 602b, 602c, and 602d are shown). The compressor 103 also includes bearing assemblies 604a and 604b, which include bearings 606a and 606b disposed in bearing housings 608a and 608b for rotatably connecting the impeller 202 to the frame 104. The compressor 103 also includes shrouds 610a and 610b, which are movable in an axial direction parallel to the longitudinal axis a1 of the impeller shaft 204. The shrouds 610a and 610b are movable to control the power or energy consumption of the force gauge. The shrouds 610a and 610b have shapes complementary to the external shape of the impeller blades 602, including an annular external shape and a C-shaped cross-section for sliding over the blades, thereby controlling the amount of air reaching the impeller blades. The force gauge 100 also includes shroud adjustment assemblies 612a and 612b, which include motors 614a and 614b, gears 615a and 615b, and chains 616a and 616b for moving the shrouds 610a and 610b. Figure 6 As shown, collector 102 surrounds impeller 202, with impeller blades 602 located within the collector. Impeller blades 602 comprise two opposing rows of blades on opposite sides of hub 600, and a partition wall 314 is located between the two rows of blades, forming partitioned internal volumes 620a, 620b that guide compressed air from the two rows of blades through the partitioned internal volumes toward impeller outlet 313. Therefore, collector 102 and compressor 103 are independently supported by frame 104, and the collector is structurally not supported by the compressor. Instead, in the illustrated example, collector 102 and compressor 103 are slidably provided only at annular inlets 316, 402 in shrouds 610a, 610b. Figure 4 The collector 102 and compressor 103 are directly mechanically connected at a location within the compressor. This structural separation between the collector 102 and compressor 103 helps to minimize any transfer of mechanical or thermal energy from the collector to the compressor.

[0076] Figure 7 This is a close-up front cross-sectional view of the air force gauge 100. During operation, ambient air enters through annular inlets 316 and 402 in the general direction indicated by arrow A of the main gas flow path. The main gas flow path A is partially defined by the bearing housings 608a and 608b on the hub side and the hub surfaces 702a and 702b, and partially defined by the annular inlets 316 and 402 and the shields 610a and 610b on the shield side. Figure 7The illustration shows the shroud 610 in the fully inserted position, which prevents air from reaching the impeller blades 602. During operation, the impeller shaft 204 is driven by a driving force, such as a motor (not shown), and the amount of energy consumed by the impeller 202 can be increased by retracting the shroud 610 from the impeller blades 602, thereby increasing the volume of the airflow entering the air force gauge 100 and being compressed by the impeller 202.

[0077] Figure 8 This is a close-up front cross-sectional view of the air force gauge 100. As shown, in the illustrated example, the annular inlet 402 of the collector 102 is configured and sized to fit snugly around the outer surface 802 of the shroud 610b, thereby forming an interface 804 between the collector and the impeller 202 (the annular inlet 316 is similarly configured to fit around the shroud 610a to form an interface). In the illustrated example, the interface 804 is not sealed (and similarly, the interface between the annular inlet 316 and the shroud 610a on the opposite side of the collector is not sealed), thus forming an impeller bypass flow path B at a location in the collector downstream of the impeller blades 602 for direct air transfer between the environment and the internal volume 620b of the collector. Therefore, the flow path B allows air to bypass the impeller 202 and be transferred directly between the environment and the internal volumes 620a, 620b of the collector. In other examples, the air force gauge 100 may include one or more seals to prevent gas flow across the interface 804. Examples of seals may include any type of resilient seal or labyrinth seal. In some examples, the air force gauge 100 may include a seal configured to prevent airflow across interface 804 while substantially preventing or attenuating the transfer of mechanical and / or thermal energy between collector 102 and shroud 610. As noted above, interface 804 is not a structural interface for supporting the collector. Instead, in the illustrated example, collector 102 is structurally supported by frame 104 and compressor 103 effectively floats within the collector, where compressor is also independently supported by the frame.

[0078] Figure 8The illustration shows the main gas flow path A between the inner wall 808 of the shroud 610b on the shroud side and the bearing housing 608b and hub surface 702b on the hub side. Ambient air is compressed and accelerated by the impeller blades 602 and discharged into the internal volume 620 of the collector. The sidewall 310 and outer surface 810 of the annular inlet 402 of the collector define a frame that facilitates some internal recirculation of air near the interface 804 (as illustrated by arrow R). In the illustrated example, the impeller 202 and collector 102 have an aerodynamic design that results in negative static pressure generated by the impeller blades 602 in the internal volume 620b of the collector near the impeller blades and interface 804, causing ambient air to be drawn into the collector, as indicated by arrow B. Such negative pressure design and the unsealed interface 804 can provide several benefits, including introducing relatively cool ambient air into the collector, which can reduce the temperature of the air inside the collector and thus reduce thermal stress. The recirculation flow path R facilitated by the collector rack at surface 810 also helps ambient air flow inward into the collector across interface 804. In other examples, in addition to or replacing the bypass flow path B at interface 804, collector 102 may have another bypass flow path to allow ambient air inflow, such as one or more openings in one or more walls 302, 304, 306, 308, 310 of the collector.

[0079] Figure 9 and Figure 10 Another example of collector 902 is illustrated, which is substantially the same as collector 102 and can be used in place of collector 102. Like collector 102, collector 902 is designed as a separate component from frame 104 and compressor 103, which provides several benefits, including minimizing the transfer of mechanical and thermal energy, such as vibration and heat transfer, between the collector and the frame and compressor. Collector 902 includes a top half 904 and a bottom half 906 joined together at flanges 908, 910. Figure 10 As shown, collector 102 (which is mounted on bracket 404) Figure 4Unlike the connection to frame 104, collector 902 is configured to be supported by crossbars 116, 502 of frame 104 by positioning flanges 908, 910 on top of the transverse members and attaching the flanges to the transverse members. Thus, collector 902 is positioned on top of a portion of frame 104 and suspended by the frame. Like collector 102, collector 902 is not structurally supported by compressor 103, and the compressor effectively floats within the collector, which is also supported by the frame. In some examples, damping material may be added between flanges 910 and crossbars 116, 502 to further isolate collector 902 from frame 104. The connection of flanges 908, 910 to crossbars 116, 502 may also allow for thermal expansion of the flanges relative to the crossbars, for example, by incorporating elliptical openings or slotted openings in the flanges, these openings being larger in one dimension than the outer diameter of the bolts used to attach the collector to the frame. In other examples, collector 902 may include additional mounting brackets (such as mounting bracket 404). Figure 4 )) to be used to attach the collector to frame 104.

[0080] Figure 11 The illustration shows the computational fluid dynamics (CFD) calculations of the collector 102 and impeller blades 602 during the operation of the air force gauge 100, illustrating the air velocity within the collector. Figure 11 As shown, collector 102 has an asymmetrical shape and impeller 202 is offset within the collector, wherein the impeller is closer to the front wall 302 than to the rear wall 304 (see also...). Figure 3 Arrow R indicates the direction of rotation of impeller 202, and the illustrated CFD flow tube shows high-speed air being discharged from the impeller blades toward the front wall 302 and bottom wall 306, and then slowed down as the air flows toward the collector's rear wall 304 and outlet 313. Such an asymmetrical collector shape and offset impeller position can result in a reduced air velocity at collector outlet 313 compared to a centrally located impeller and / or a symmetrically shaped collector (i.e., symmetrical about a vertical centerline extending parallel to the front wall 302 and rear wall 304). This can help reduce noise and vibration.

[0081] The foregoing is a detailed description of illustrative embodiments of the present invention. Note that, in this specification and the appended claims, unless otherwise specifically stated or indicated, connective language used in phrases such as “at least one of X, Y, and Z” and “one or more of X, Y, and Z” should be understood to mean that each item in the list of connectives can be presented as any mark excluding all other items in the list, or as a combination of any mark with any or all other items in the list of connectives, each of which can also be presented as any mark. Applying this general rule, the connective phrases in the foregoing examples (where the list of connectives consists of X, Y, and Z) should each cover: one or more of X; one or more of Y; one or more of Z; one or more of X and one or more of Y; one or more of Y and one or more of Z; one or more of X and one or more of Z; and one or more of X, one or more of Y, and one or more of Z.

[0082] Various modifications and additions can be made without departing from the spirit and scope of the invention. Features of each of the various embodiments described above may be combined with features of other described embodiments as appropriate to provide multiple combinations of features in related new embodiments. Furthermore, while the foregoing describes multiple individual embodiments, the content described herein merely illustrates the application of the principles of the invention. Moreover, although specific methods herein may be shown and / or described as being performed in a particular order, this order is highly variable within the skill of the art to achieve multiple aspects of this disclosure. Accordingly, this description is intended to be taken as an example only and does not otherwise limit the scope of the invention.

[0083] Exemplary embodiments have been disclosed above and illustrated in the accompanying drawings. Those skilled in the art will understand that various changes, omissions, and additions can be made to the content particularly disclosed herein without departing from the spirit and scope of the invention.

Claims

1. A turbine, comprising: frame; An impeller having multiple impeller blades, the impeller being rotatably supported by the frame; A collector, which is coupled to the frame and fluidly coupled to the impeller, to collect the air discharged by the impeller; and At least one shroud is attached to the frame, the at least one shroud is movable relative to the plurality of impeller blades, and is movable in a first direction parallel to the longitudinal axis of the impeller shaft to control the amount of air transferred from the impeller to the collector; The collector is supported by the frame independently of the impeller to mechanically separate the collector from the impeller and minimize the transfer of mechanical and thermal energy between the collector and the impeller.

2. The turbine of claim 1, wherein the collector includes a first sidewall and a second sidewall, and wherein the impeller includes a hub and a first shaft portion and a second shaft portion extending from opposite sides of the hub, wherein the impeller extends through the collector, wherein the plurality of impeller blades are located within the collector and the first shaft portion and the second shaft portion extend laterally outward from respective sidewalls of the first sidewall and the second sidewall of the collector.

3. The turbine of claim 1, wherein the collector includes at least one sidewall having an opening, wherein the at least one shroud is located in the opening.

4. The turbine of claim 3, wherein the at least one sidewall comprises a first sidewall and an opposing second sidewall, and the at least one shield comprises a first shield and a second shield, the first shield and the second shield being located in corresponding openings in the openings in the first sidewall and the opposing second sidewall.

5. The turbine of claim 3, wherein the collector comprises a front wall and a rear wall, the at least one side wall extending between the front wall and the rear wall, wherein the impeller is located inside the collector and offset from the centerline of the collector, and positioned closer to the front wall than the rear wall, and is designed to guide working fluid in a downward direction along the front wall and in an upward direction towards the outlet of the collector along the rear wall.

6. The turbine of claim 1, wherein the at least one shroud has a shape complementary to the external shape of the plurality of impeller blades, including an annular external shape and a C-shaped cross-section for sliding over the plurality of impeller blades, thereby controlling the amount of air reaching the plurality of impeller blades.

7. The turbine of claim 1, wherein the at least one shroud comprises a first shroud and a second shroud, wherein the turbine comprises a first annular inlet and a second annular inlet located on a first side and an opposite second side of the turbine, wherein the first shroud and the second shroud are located near the plurality of impeller blades in the respective inlets of the first annular inlet and the second annular inlet.

8. The turbine according to any one of claims 1-7, wherein the collector is coupled to the frame at a plurality of discrete attachment points, and the turbine further comprises a damping elastic material located between the collector and the frame at one or more of the discrete attachment points.

9. The turbine according to any one of claims 1-7, wherein the collector includes at least one impeller bypass flow path for directly transferring air between the environment and a location downstream of the plurality of impeller blades in the collector.

10. The turbine of claim 9, wherein the turbine is designed and configured to generate negative pressure, thereby drawing ambient air into the collector through the at least one impeller bypass flow path.

11. The turbine of claim 9, wherein the at least one impeller bypass flow path is located at the interface between an opening in the sidewall of the collector and at least one shroud.

12. The turbine according to any one of claims 1-7, wherein the turbine is an air force gauge.

13. The turbine according to any one of claims 1-7, wherein the turbine is an air compressor.

14. The turbine according to any one of claims 1-7, wherein the collector has an asymmetrical shape and the axis of rotation of the impeller is offset from the centerline of the collector.

15. The turbine according to any one of claims 1-7, wherein the frame comprises two opposing vertical supports, wherein the collector is located between the two opposing vertical supports and surrounds the plurality of impeller blades.

16. The turbine according to any one of claims 1-7, wherein the collector is suspended from the frame.

17. The turbine according to any one of claims 1-7, wherein the frame comprises at least one vertical support and at least one transverse member extending from the at least one vertical support, wherein the collector is suspended from the at least one transverse member.

18. A turbine, comprising: frame; An impeller having a plurality of impeller blades and a first shaft portion and a second shaft portion extending from opposite sides of the impeller, the impeller being rotatably supported by the frame and by a first bearing and a second bearing connected to the first shaft portion and the second shaft portion; A collector, which is coupled to the frame and fluidly coupled to the impeller, to collect the air discharged by the impeller; At least one shroud is attached to the frame, the at least one shroud is movable relative to the plurality of impeller blades, and is movable in a first direction parallel to the longitudinal axis of the impeller shaft to control the amount of air transferred from the impeller to the collector; and A first annular inlet and a second annular inlet, located on a first side and an opposite second side of the collector. At least a portion of the first shaft portion is located in the first annular inlet, and at least a portion of the second shaft portion is located in the second annular inlet, wherein the first annular inlet and the second annular inlet are configured as working fluid channels for drawing ambient air into the turbine. The collector is supported by the frame independently of the impeller to mechanically separate the collector from the impeller and minimize the transfer of mechanical and thermal energy between the collector and the impeller.

19. The turbine according to claim 18, wherein, The at least one shield includes a first shield and a second shield, wherein the first shield and the second shield are located near the plurality of impeller blades in the respective inlets of the first annular inlet and the second annular inlet.

20. The turbine of claim 19, wherein the collector includes a first sidewall and a second sidewall, each sidewall including an opening, wherein the first shield and the second shield are located in corresponding openings in the openings of the first sidewall and the second sidewall.

21. The turbine according to any one of claims 18-20, wherein the collector is coupled to the frame at a plurality of discrete attachment points, the turbine further comprising a damping elastic material located between the collector and the frame at one or more of the discrete attachment points.

22. The turbine according to any one of claims 18-20, wherein the collector includes at least one impeller bypass flow path for directly transferring air between the environment and a location downstream of the plurality of impeller blades in the collector.

23. The turbine of claim 22, wherein the turbine is designed and configured to generate negative pressure, thereby drawing ambient air into the collector through the at least one impeller bypass flow path.

24. The turbine of claim 22, wherein the at least one impeller bypass flow path is located at the interface between an opening in the sidewall of the collector and at least one shroud.

25. The turbine according to any one of claims 18-20, wherein the turbine is an air force gauge.

26. The turbine according to any one of claims 18-20, wherein the turbine is an air compressor.

27. The turbine according to any one of claims 18-20, wherein the collector has an asymmetrical shape and the axis of rotation of the impeller is offset from the centerline of the collector.

28. The turbine according to any one of claims 18-20, wherein the frame comprises two opposing vertical supports, wherein the collector is located between the two opposing vertical supports and surrounds the plurality of impeller blades.

29. The turbine according to any one of claims 18-20, wherein the collector is suspended from the frame.

30. The turbine according to any one of claims 18-20, wherein the frame comprises at least one vertical support and at least one transverse member extending from the at least one vertical support, wherein the collector is suspended from the at least one transverse member.

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