CONTINUOUSLY VARIABLE TURBINE

Abstract

A compressor includes an assembly with a case body defining a chamber, a shaft defining a rotational axis, a ring piston positioned within the chamber, a rotor assembly positioned within the ring piston, the rotor assembly being mounted on the shaft, and a pair of opposed compression vanes, each compression vane having a seal component with a surface that matches an outer curvature of the ring piston to form a continuous surface seal between the seal component and the ring piston as the rotor assembly and the ring piston rotate about the axis of the shaft, the position of the continuous surface seals in the chamber defining a first sub-chamber and a second sub-chamber between the surface seals, the case body further including an inlet port and an exhaust port for each sub-chamber.

Description

RELATED APPLICATION

The present application is a continuation-in-part of U.S. patent application Ser. No. 16/014,339, filed on Jun. 21, 2018, which claims the benefit of U.S. Provisional Patent Application No. 62/524,822, filed on Jun. 26, 2017.

The entire contents of the above-referenced applications are incorporated herein by reference.

INTRODUCTION

The present disclosure relates to a continuously variable turbine.

A turbine is a rotary device that extracts energy from a fluid and converts it into useful work. Many types of turbines have been developed in the past. Various types of turbines include steam turbines, wind turbines, gas turbines and water turbines.

In some turbines, a set of blades or vanes are positioned about a shaft or spindle. The blades or vanes are arranged such that flow of fluid through the blades or vanes causes the blades or vanes to move thereby causing the shaft or spindle to rotate. The turbine may be connected machinery such as a pump, compressor or components of a propulsion system. The work produced by the turbine can be utilized for generating power when coupled with a generator or producing thrust, for example, from jet engines.

While current turbines achieve their intended purpose, there is a need for a new and improved turbine with higher efficiencies.

SUMMARY

According to several aspects, a compressor includes an assembly with a case body defining a chamber, a shaft defining a rotational axis, a ring piston positioned within the chamber, a rotor assembly positioned within the ring piston, the rotor assembly being mounted on the shaft, and a pair of opposed compression vanes, each compression vane having a seal component with a surface that matches an outer curvature of the ring piston to form a continuous surface seal between the seal component and the ring piston as the rotor assembly and the ring piston rotate about the axis of the shaft, the position of the continuous surface seals in the chamber defining a first sub-chamber and a second sub-chamber between the surface seals, the case body further including an inlet port and an exhaust port for each sub-chamber.

In an additional aspect of the present disclosure, the compressor is configured to be staged with one or more additional compressors on the shaft.

In another aspect of the present disclosure, the staged compressors provide maximum fluid flow or maximum flow pressure depending upon the of the arrangement of the connections between the inlet ports and the outlet ports.

In another aspect of the present disclosure, the staged compressors are configured to operate as an air motor for an input of high air flow rate at low pressure or low air flow rate at high pressure.

In another aspect of the present disclosure, the staged compressors operate as both motors and compressors on the single rotational axis defined by the shaft to utilize a kinetic, pneumatic or hydraulic energy source to generate a pneumatic or hydraulic output, as well as a kinetic output.

In another aspect of the present disclosure, the inlet port is defined by an assembly including a check valve.

In another aspect of the present disclosure, the check valve is a reed valve made of a thin, flexible material.

In another aspect of the present disclosure, the outlet port is defined by an assembly including a check valve.

In another aspect of the present disclosure, the check valve is a reed valve made of a thin, flexible material.

In another aspect of the present disclosure, an inner surface or an outer surface or both the inner surface and the outer surface of the ring piston are coated with a material made of nano-particles to provide lubrication-less operation of the compressor.

According to several aspects, an assembly includes a plurality of compressors. Each compressor includes an assembly with a case body defining a chamber, a shaft defining a rotational axis, a ring piston positioned within the chamber, a rotor assembly positioned within the ring piston, the rotor assembly being mounted on the shaft, and a pair of opposed compression vanes, each compression vane having a seal component with a surface that matches an outer curvature of the ring piston to form a continuous surface seal between the seal component and the ring piston as the rotor assembly and the ring piston rotate about the axis of the shaft, the position of the continuous surface seals in the chamber defining a first sub-chamber and a second sub-chamber between the surface seals, the case body further including an inlet port and an exhaust port for each sub-chamber. The compressors are configured to be staged with one or more additional compressors on the shaft to rotate about the rotational axis.

In another aspect of the present disclosure, the staged compressors are configured to operate as an air motor for an input of high air flow rate at low pressure or low air flow rate at high pressure.

In another aspect of the present disclosure, the staged compressors operate as both motors and compressors on the single rotational axis defined by the shaft to utilize a kinetic, pneumatic or hydraulic energy source to generate a pneumatic or hydraulic output, as well as a kinetic output.

In another aspect of the present disclosure, the inlet port is defined by an inlet assembly including a check valve.

In another aspect of the present disclosure, the check valve is a reed valve made of a thin, flexible material.

In another aspect of the present disclosure, the outlet port is defined by an outlet assembly including a check valve.

In another aspect of the present disclosure, the check valve is a reed valve made of a thin, flexible material.

In another aspect of the present disclosure, an inner surface or an outer surface or both the inner surface and the outer surface of the ring piston are coated with a material made of nano-particles to provide lubrication-less operation of the compressor.

Further areas of applicability will become apparent from the description provided herein. It should be understood that the description and specific examples are intended for purposes of illustration only and are not intended to limit the scope of the present disclosure.

BRIEF DESCRIPTION OF THE DRAWINGS

The drawings described herein are for illustration purposes only and are not intended to limit the scope of the present disclosure in any way.

FIG. 1 is a top view of a continuously variable turbine in accordance with the principles of the present disclosure;

FIG. 2 is an exploded view of the turbine shown in FIG. 1;

FIG. 3 is a perspective view of a valve assembly for the turbine shown in FIG. 1;

FIG. 4 is a side view of the valve assembly shown in FIG. 3;

FIG. 5 illustrates two valve assemblies;

FIG. 6 is an exploded view of the valve assemblies and a ring piston of the turbine shown in FIG. 1;

FIG. 7 is a perspective view of a rotor assembly for the turbine shown in FIG. 1;

FIG. 8 is an exploded view of a multi-stack turbine in accordance with the principles of the present disclosure;

FIG. 9 shows the turbine of FIG. 1 operating as a compressor;

FIG. 10 shows the turbine of FIG. 1 operating as a motor;

FIG. 11 shows a thermal engine with two of the turbines shown in FIG. 1 in accordance with the principles of the present disclosure;

FIG. 12A is a perspective view of a rotor assembly for a compressor in accordance with the principles of the present disclosure;

FIGS. 12B and 12C are side view of the rotor assembly shown in FIG. 12A;

FIG. 13A is a perspective view of a rotary piston for a compressor in accordance with the principles of the present disclosure;

FIG. 13B is a side view of the rotary piston shown in FIG. 13A;

FIG. 13C is a view of the rotary piston taken from 13C-13C of FIG. 13B;

FIG. 14A is a perspective frontal view of a compression vane for a compressor in accordance with the principles of the present disclosure;

FIG. 14B is a perspective rear view of the compression vane for a compressor in accordance with the principles of the present disclosure;

FIG. 15A is a perspective view of an exhaust port assembly for a compressor in accordance with the principles of the present disclosure;

FIG. 15B is a view of an interface slot of the exhaust port assembly shown in FIG. 15A;

FIG. 15C is a view of an exhaust port of the exhaust port assembly shown in FIG. 15A;

FIG. 15D is a view of the exhaust port assembly taken along the lines 15D-15D of FIG. 15C;

FIG. 16A is a perspective view of an inlet port assembly for a compressor in accordance with the principles of the present disclosure;

FIG. 16B is a view of an interface slot of the inlet port assembly shown in FIG. 16A;

FIG. 16C is a view of an inlet port of the inlet port assembly shown in FIG. 16A;

FIG. 16D is a view of the inlet port assembly taken along the lines 16D-16D of FIG. 16C;

FIG. 17A is a perspective view of a compressor in accordance with the principles of the present disclosure;

FIG. 17B is a side view of a face of the compressor shown in FIG. 17A;

FIG. 17C is an edge view of the compressor shown in FIG. 17A;

FIG. 17D is a view of the compressor taken along the line 17D-17D of FIG. 17C; and

FIG. 17E is a perspective view of multiple staged compressors in accordance with the principles of the present disclosure.

DETAILED DESCRIPTION

The following description is merely exemplary in nature and is not intended to limit the present disclosure, application, or uses.

Referring to FIGS. 1 and 2, there is shown a continuously variable turbine 10. The turbine 10 includes a rotor assembly 11, a valve assembly 29 and a case assembly 40. The case assembly 40 includes a case body 40 with chamber 45. The rotor assembly 11 includes a ring piston 14 positioned in the chamber 45 and a rotor body 12 mounted on a shaft 19 and positioned within the ring piston 14.

Referring also to FIG. 7, a set of bearing shafts 17 extend through respective bearing holes 17 in the rotor body 12. A pair of bearings 16 are mounted on each bearing shaft 17. Note that the present disclosure is not limited to the use of two bearings on each shaft. In some configurations, a single bearing 16 may be mounted on each shaft 17, while in other configurations, three or more bearings 16 may be mounted on each shaft 17.

As shown in FIG. 1, each pair of bearings 16 makes contact with the inner surface of the ring piston 14 such that there are three contact regions between the rotor body 12 and the inner surface of the ring piston 14. Two of the bearing shafts 18 are positioned further away from an axis of rotation extending through the shaft 19 than the third shaft 18. Accordingly, as the rotor body 12 rotates concentrically about the axis of rotation, the piston ring 14 rotates eccentrically about the axis of rotation.

The case assembly 40 includes a pair of manifolds 41 as shown in FIG. 6. Each valve assembly 29 includes a valve body 30 positioned in a slot 32 of a respective manifold 41. As shown in FIGS. 3, 4 and 5, the valve assembly 29 further includes a pair of valve shafts 37 that extend through the manifold 41 and engage with retainers 34. A spring 33 is positioned about each valve shaft 37 between eh valve body 30 and the retainer 34, and the shafts 37 are able to reciprocate in respective channels 36 in the valve body 30. Accordingly, as the valve body 30 reciprocates outwardly and inwardly in the slot 32 relative to the axis of rotation of the shaft 19, the valve shafts 32 reciprocate in the channels 36 causing the springs 33 to compress and expand. A bottom plate 43 and a top plate 44 are matted and secured to the case body 41 to enclose the rotor assembly 11 and the valve assemblies 29 in the case body 41. The shaft 19 can extend through an opening in either or both the bottom plate 43 and the top plate 44. For example, as shown in FIG. 2, the shaft 19 extends through the bottom plate 43 while a bearing cap is employed to cover the opening in the top plate 44.

The valve assembly 29 also includes a seal component 31 attached to the seal body 30. Each seal component 31 has a curved surface or face 37 that corresponds to or matches the curvature of the outer surface of the ring piston 14. The springs 33 are pre-loaded so that there is continuous contact between the seal component 31 and the ring piston 14 as the ring piston 14 rotates eccentrically about the axis of rotation of the shaft 19. The seal component 31 articulates relative to the seal body 30. That is, the seal component 31 is able to move relative to the seal body 30 to fill the gaps 38 shown in FIG. 4 to ensure there is a continuous surface seal between the curved face 37 of the seal component 31 and the ring piston 14.

Each manifold 41 includes an intake port 48 and an exhaust port 49. The position of the surface seals formed by the seal components 31 define sub-chambers 45a and 45b. The robustness of the surface seals formed by the seal components 31 allow the sub-chambers 45a and 45b to withstand working pressures up to about 3000 psi without damaging or compromising the surface seals. Each valve body 30 includes a flow channel 35 to allow each chamber 45a and 45b to communicate with respective intake and exhaust ports 48 and 49.

The various components of the turbine can be made from any suitable material, such as, for example, metals and plastics. The metals can be selected, for example, from any combination of aluminum, steel, and titanium. In particular, the seal component 31 can be made from silicone.

Depending upon its use, a single turbine 10 can be employed or two or more turbine can be stacked together for higher output capabilities. For example, two turbines 10 are shown in a staked arrangement in FIG. 8. In this configuration, a single bottom plate 43 is employed as a divider between the two turbines 10, and a pair of top plates 44 are employed to encase the two rotor assemblies 11 and the two valve assemblies 29 in their respective case bodies 41.

Turning now to FIG. 9, there is shown the turbine 10 utilized as a compressor. Specifically, as the shaft 19 is rotated (for example, by a motor), the rotor assembly 12 and the ring piston 14 rotate about the axis of rotation of the shaft 19. Accordingly, inlet fluid 50a is drawn into the sub-chamber 45a though its respective intake port 48a. The fluid is compressed as the ring piston 14 rotates clockwise such that high pressure fluid 52a is exhausted through the exhaust port 49a associated with the sub-chamber 45a. Similarly, inlet fluid 50b is drawn into the sub-chamber 45b through its intake port 48b. The fluid is compressed such that high pressure fluid 52b is exhausted through the exhaust port 49b associated with the sub-chamber 45b.

The turbine 10 can also be utilized as a motor as shown in FIG. 10. In this arrangement, high pressure fluid 60a and 60b are injected through the intake ports 48a and 48b into the respective sub-chambers 45a and 45b. The expansion of the fluid cause the rotor body 12 and the ring piston 14 to rotate clockwise such that the expanded fluid 62a is exhausted from the sub-chamber 45a and the expanded fluid 62b is exhausted from the sub-chambers 45b through the exhaust ports 49a and 49b, respectively. Rotation of the rotor body 12 generates a torque on the shaft 19, which can be connected to any suitable device that can utilize the output torque from the turbine 10.

In another configuration, multiple turbines 10 can be utilized in a thermal engine 200 as shown in FIG. 11. The thermal engine 200 includes a cooling unit 202, a thermal exchange unit 204 that transfers heat to the cooling unit 202, a pump 10A that receives cooled fluid from the thermal exchange unit 204, a heating unit 206 that receives the cooled fluid from the pump 10A, and an expander 10B that receives high pressure heated fluid from the heating unit 206 and transmits low pressure heated fluid to the thermal exchange unit 204.

Both the pump 10A and the expander 10B are the same as the aforementioned turbine 10. Each is sized according to their desired function and operation. Each of the pump 10A and the expander 10B may be a single turbine, or each or both may be a multi-stacked turbine described previously. In operation, the pump 10A receives the cooled fluid from the thermal exchange unit 204 through a fluid line 214. The pump 10A receives the fluid through the intake ports 48a and 48b and pumps the fluid out of the respective sub-chambers 45a and 45b into the fluid line 218 via the exhaust ports 49a and 49b. The fluid is transmitted through the fluid line 218 to the thermal heating unit 206 where the fluid is heated. The high pressure heated fluid is transmitted from the thermal heating unit 206 to the expander 10A through fluid lines 220.

The high pressure heated fluid enters into the sub-chambers 45a and 45b of the expander 10B through the intake ports 48a and 48b, respectively. The expanded fluid leaves the sub-chambers 45a and 45b through the exhaust ports 49a and 49b and is transmitted to the thermal exchange unit 204. The rotation of the rotor body 12 of the expander 10B generates torque than can be transmitted via the shaft 19 to any desired machinery coupled to the shaft 19.

The thermal exchange unit 204 transfers the heat in the fluid from the expander 10B into the fluid circulating in fluid lines 212 and 213. More specifically, a circulation pump 208 draws the fluid from the thermal exchange unit 204 through the fluid line 212 and transmits it to the cooling unit 202. The cooled fluid is then pumped back to the thermal exchange unit 204 through the fluid line 213.

Note that the fluid flowing through the fluid lines 212 and 213 defines a first closed circuit of fluid flow, and the fluid flowing through the fluid lines 214, 218, 220 and 216 defines a second closed circuit of fluid flow. A control unit 210 may be utilized to control the operation of the thermal engine 200.

Referring now to FIGS. 17A-17D, there is shown an alternative compressor 800 in accordance with the principles of the present disclosure. The compressor 800 includes a case body 802 that defines a chamber 806. The compressor 800 further includes within the chamber 806 a rotor assembly 300 mounted on a shaft 302 and a ring piston 400 surrounding the rotor assembly 300. The rotor assembly 300 includes a set of roller bearings 804 that are in contact with the inner surface of the ring piston 400 as the rotor assembly rotates about a central axis extending through the shaft 302.

The compressor 800 further includes a pair of opposed compression vanes 500. Each compression vane 500 includes a seal component 510 with a surface that matches the outer curvature of the ring piston 400 to form a continuous surface seal between the seal component 510 and the ring piston 400 as the rotor assembly 300 and the ring piston 400 rotate about the axis of the shaft 302, the position of the continuous surface seals in the chamber 806 defining a first sub-chamber and a second sub-chamber between the surface seals. Each compression vane 500 also includes a spring 512 that urges the vane 500 towards the ring piston 400 to maintain a seal between the seal component 510 and the ring piston 400.

Associated with each sub-chamber of the chamber 806 is an exhaust port assembly 600 and an inlet port assembly 700. In various implementations, a pair of exhaust port assemblies 600 are positioned diametrically opposed to each other, and a pair of inlet port assemblies 700 are positioned diametrically opposed to each other. Each exhaust port assembly 600 includes an inlet opening 608, and each inlet port assembly 700 includes an outlet opening 708.

The compressor 800 also includes one or more mounting sites 803. The mounting sites 803 enable the compressor 800 to any suitable structure. Kinetic input energy is provided by the rotation of the shaft 302. The compressor case body 802 is made from metallic, ceramic synthetic material, or any other suitable material.

Referring further to FIG. 17E, there is shown two or more staged or stacked compressors 800 mounted about the shaft 302. In some implementations, for example, in a two-stage configuration, the second unit is offset from the first unit by 90°, and in a three-stage configuration, the second unit is offset from the first unit by 120° and the third unit is offset from the first unit by 240°. In various implementations, a plate 805 positioned on the outer surfaces of the outer most compressors 800. In certain implementations a plate 805 is positioned between the compressors 800.

In various implementations, the configuration shown in FIG. 17E produces maximum compressor fluid flow or maximum air pressure for a given rotational speed of the shaft 302, depending on how the inlets 608 and the outlets 708 are connected together. The configuration is utilized in certain implementations as an air motor optimized for an input of high air flow rate at low pressure or low air flow rate at high pressure. The configuration can also be operated with both motors and compressors mounted about a single shaft 302. As such, the configuration can utilize kinetic, pneumatic or hydraulic energy input to generate pneumatic or hydraulic output, as well as kinetic output.

In various implementations, the one or more compressors 800 operate under various thermal and pressure cycle environments. For example, the compressor 800, can be utilized, but not limited to, hazardous explosive environments, clean room environments where the risk of particulates may be harmful, and laboratory and medical theatre environments where antiseptic and antimicrobial matter is maintained at extreme levels.

In some implementations, the compressor 800 features adjustable eccentric bearing shafts on the rotary piston ring 400 drive bearings 805 that permit the eccentricity of the rotary piston ring 400 to be micro-adjusted to enable the precise control of the clearance between the rotary piston ring 400 and chamber 806 of the case body 802. This adjustability permits optimized performance and efficiency of the compressor 800.

Low friction, dry sliding, bearing plates 808 made from nano-particle material protect the oscillating motion of the sliding compression vanes 500 from friction and wear. These bearing plates permit lubrication-free operation and protect the oscillating motion of the sliding vanes 500. The compressor 800 utilizes pressure balance porting, through or around the slide vanes 500, which applies pressure and a resulting force to the slide vane 500 which keeps seal components 510 in contact with the rotary piston ring 400. Pressure balance features in the face of the seal components 510 balance the pressure on the seal components 510 to rotary piston ring 400 interface to minimize drag and resulting mechanical losses while maintaining the sealing function. Further, externally attached, modular check valve housings, with common inlet 708 and outlet 608 interfaces, permit easy reconfiguration from compressor to motor operation, and easy change from clockwise to counter-clockwise rotation of the shaft 302. Device architecture is scalable to allow optimization of individual stages sizes, number of stages, and combination of stages configurations for a broad spectrum of specific applications.

Referring now to FIGS. 12A through 12C, there are shown further details of the rotor assembly 300. The rotor assembly 300 includes concentric bearing mounting flanges 304, 306, 308 and 314 that define mounting slots 307 and 310 to mount, for example, roller bearings 805. Note that the present disclosure is not limited to the use of two bearings on each bearing shaft. Specific design geometries and configurations as depicted are scalable, depending on the overall system performance requirements and specifications. The rotor mass 312 is configured to provide internally-balanced operation. The internally-balanced rotating mass 312 of the eccentric hub results in minimal rotational vibration and improved bearing compressor life. This balanced mass also permits the joining of multiple compressor and motor stages on a single rotational axis without the use of external balancing devices. The output shaft 302 is keyed for multiple connections to other compressors as illustrated in FIG. 17E and to interface with other external system components. For example, the shaft 302 can interface with other features including, but not limited to, splines, geometric shapes (such as hexagonal shapes), pinned connectors and smooth shafts.

Turning now to FIGS. 13A through 13C, there are shown further details of the rotary ring piston 400. The ring piston 400 includes an outer surface 402 that interfaces with the seal components 510 of the compression vanes 500. The ring piston 400 has bearing races 406 on the inside of the ring piston 400. Additional bearing races can be added to the ring piston 400 to correspond to the number of bearing utilized by the rotor assembly 300 positioned in an opening 404. The outer surface 402 and inner surfaces 404 and 406 are coated with a material made of nano-particles in various implementations to provide lubrication-less operation of the ring piston 400. The piston ring 400 is sealed via a sealing material in slots 403 on the outer circumference of on both side of the piston ring 400. The piston ring can be made from a variety of materials including metallic, ceramic, and synthetic materials. The sealing material 403 is dry-sliding, low friction, ring insets in the end face of the rotary piston ring 400 in various implementations that act as both a seal and a bearing surface. This maintains a mean pressure region inside the rotary piston ring 400 that reduces the internal leakage from the compression space, resulting in greater compression performance.

Referring now to FIGS. 14A and 14B, there are shown further details of the compression vane 500. The compression vane 500 is configured with geometries 502 and 504 to ensure desired sealing between the compression vane and the case body 802 of the compressor 800. For example, seal components, such as, for example, seal component 510 is utilized in various implementations. The compression vane 500 also includes channels 510 and 512 and balancing ports 508 and 514 to provide dynamic positive pressure to maintained aligned operand of the seal component 510 to the outer surface 402 of the piston ring 400. The body of the compression vane 500 can be made from a variety of metallic, ceramic or synthetic materials.

Referring now to FIGS. 15A to 15D, there are shown further details of the exhaust port assembly 600. The exhaust port assembly 600 includes a first portion 602 and a second portion 604 joined together with a set of fasteners 612. The exhaust port assembly 600 is modular to provide rapid reconfiguration on the compressor 800. In some implementations, the exhaust port assembly 600 satisfies ISO standards. The exhaust port assembly 600 utilizes a check valve based on a reed valve 614. The read valve has one end 615 attached to the portion 604 with a fastener 616. The exhaust port assembly 600 further includes an interface slot 610 that communicates with a respective sub-chamber of the chamber 806 and an exhaust port 606 with an opening 608. Accordingly, a fluid at a desired pressure pushes an end 617 of the reed valve 614 away from the interface slot 610 so that fluid drawn from a respective sub-chamber of the chamber 806 into the exhaust port assembly 600 and is exhausted from the exhaust port assembly 600 through the opening 608. The body of the exhaust port assembly can be made from a variety of metallic, ceramic or synthetic materials.

Referring now to FIGS. 16A to 6D, there are shown further details of the inlet port assembly 700. The inlet port assembly 700 includes a first portion 702 and a second portion 704 joined together with a set of fasteners 710. The inlet port assembly 700 is modular to provide rapid reconfiguration on the compressor 800. In some implementations, the inlet port assembly 700 satisfies ISO standards. The inlet port assembly 700 utilizes a check valve based on a reed valve 718. The read valve has one end 720 attached to the portion 702 with a fastener 722. The inlet port assembly 700 further includes an interface 712 with a slot 714 that communicates with a respective sub-chamber of the chamber 806 and an inlet port 706 with an opening 708. Accordingly, a fluid at a desired pressure pushes an end 724 of the reed valve 718 away from a slotted opening 716 that is in fluid communication with the opening 708 so that fluid is drawn into the opening 708 and exits the inlet port assembly 700 through the slot 714 into a respective sub-chamber of the chamber 806. The body of the exhaust port assembly can be made from a variety of metallic, ceramic or synthetic materials.

Both the exhaust port assembly 600 and the inlet port assembly utilize check valves based on reed valves that are configured to minimize pressure losses, facilitate rapid checking (that is, sealing) for high speed operation, and for long life.

The description of the present disclosure is merely exemplary in nature and variations that do not depart from the gist of the present disclosure are intended to be within the scope of the present disclosure. Such variations are not to be regarded as a departure from the spirit and scope of the present disclosure.

Claims

1. A compressor comprising:

an assembly with a case body defining a chamber;

a shaft defining a rotational axis;

a ring piston positioned within the chamber;

a rotor assembly positioned within the ring piston, the rotor assembly being mounted on the shaft; and

a pair of opposed compression vanes, each compression vane having a seal component with a surface that matches an outer curvature of the ring piston to form a continuous surface seal between the seal component and the ring piston as the rotor assembly and the ring piston rotate about the axis of the shaft, the position of the continuous surface seals in the chamber defining a first sub-chamber and a second sub-chamber between the surface seals, the case body further including an inlet port and an exhaust port for each sub-chamber.

2. The compressor of claim 1, wherein the compressor is configured to be staged with one or more additional compressors on the shaft.

3. The compressor of claim 2, wherein the staged compressors provide maximum fluid flow or maximum flow pressure depending upon the of the arrangement of the connections between the inlet ports and the outlet ports.

4. The compressor of claim 2, wherein the staged compressors are configured to operate as an air motor for an input of high air flow rate at low pressure or low air flow rate at high pressure.

5. The compressor of claim 2, wherein the staged compressors operate as both motors and compressors on the single rotational axis defined by the shaft to utilize a kinetic, pneumatic or hydraulic energy source to generate a pneumatic or hydraulic output, as well as a kinetic output.

6. The compressor of claim 1, wherein the inlet port is defined by an assembly including a check valve.

7. The compressor of claim 6, wherein the check valve is a reed valve made of a thin, flexible material.

8. The compressor of claim 1, wherein the outlet port is defined by an assembly including a check valve.

9. The compressor of claim 8, wherein the check valve is a reed valve made of a thin, flexible material.

10. The compressor of claim 1, wherein an inner surface or an outer surface or both the inner surface and the outer surface of the ring piston are coated with a material made of nano-particles to provide lubrication-less operation of the compressor.

11. An assembly with a plurality of compressors, each compressor comprising:

an assembly with a case body defining a chamber;

a shaft defining a rotational axis;

a ring piston positioned within the chamber;

a rotor assembly positioned within the ring piston, the rotor assembly being mounted on the shaft; and

a pair of opposed compression vanes, each compression vane having a seal component with a surface that matches an outer curvature of the ring piston to form a continuous surface seal between the seal component and the ring piston as the rotor assembly and the ring piston rotate about the axis of the shaft, the position of the continuous surface seals in the chamber defining a first sub-chamber and a second sub-chamber between the surface seals, the case body further including an inlet port and an exhaust port for each sub-chamber,

wherein the compressors are configured to be staged with one or more additional compressors on the shaft to rotate about the rotational axis.

12. The assembly of claim 11, wherein the staged compressors are configured to operate as an air motor for an input of high air flow rate at low pressure or low air flow rate at high pressure.

13. The compressor of claim 11, wherein the staged compressors operate as both motors and compressors on the single rotational axis defined by the shaft to utilize a kinetic, pneumatic or hydraulic energy source to generate a pneumatic or hydraulic output, as well as a kinetic output.

14. The assembly of claim 11, wherein the inlet port is defined by an inlet assembly including a check valve.

15. The assembly of claim 14, wherein the check valve is a reed valve made of a thin, flexible material.

16. The assembly claim 11, wherein the outlet port is defined by an outlet assembly including a check valve.

17. The assembly of claim 16, wherein the check valve is a reed valve made of a thin, flexible material.

18. The assembly of claim 11, wherein an inner surface or an outer surface or both the inner surface and the outer surface of the ring piston are coated with a material made of nano-particles to provide lubrication-less operation of the compressor.