Patent Publication Number: US-2020277958-A1

Title: Continuously variable turbine

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  13 C- 13 C 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  15 D- 15 D 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  16 D- 16 D 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  17 D- 17 D 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  45   a  and  45   b.  The robustness of the surface seals formed by the seal components  31  allow the sub-chambers  45   a  and  45   b  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  45   a  and  45   b  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  50   a  is drawn into the sub-chamber  45   a  though its respective intake port  48   a.  The fluid is compressed as the ring piston  14  rotates clockwise such that high pressure fluid  52   a  is exhausted through the exhaust port  49   a  associated with the sub-chamber  45   a.  Similarly, inlet fluid  50   b  is drawn into the sub-chamber  45   b  through its intake port  48   b.  The fluid is compressed such that high pressure fluid  52   b  is exhausted through the exhaust port  49   b  associated with the sub-chamber  45   b.    
     The turbine  10  can also be utilized as a motor as shown in  FIG. 10 . In this arrangement, high pressure fluid  60   a  and  60   b  are injected through the intake ports  48   a  and  48   b  into the respective sub-chambers  45   a  and  45   b.  The expansion of the fluid cause the rotor body  12  and the ring piston  14  to rotate clockwise such that the expanded fluid  62   a  is exhausted from the sub-chamber  45   a  and the expanded fluid  62   b  is exhausted from the sub-chambers  45   b  through the exhaust ports  49   a  and  49   b,  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  10 A that receives cooled fluid from the thermal exchange unit  204 , a heating unit  206  that receives the cooled fluid from the pump  10 A, and an expander  10 B 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  10 A and the expander  10 B are the same as the aforementioned turbine  10 . Each is sized according to their desired function and operation. Each of the pump  10 A and the expander  10 B may be a single turbine, or each or both may be a multi-stacked turbine described previously. In operation, the pump  10 A receives the cooled fluid from the thermal exchange unit  204  through a fluid line  214 . The pump  10 A receives the fluid through the intake ports  48   a  and  48   b  and pumps the fluid out of the respective sub-chambers  45   a  and  45   b  into the fluid line  218  via the exhaust ports  49   a  and  49   b.  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  10 A through fluid lines  220 . 
     The high pressure heated fluid enters into the sub-chambers  45   a  and  45   b  of the expander  10 B through the intake ports  48   a  and  48   b,  respectively. The expanded fluid leaves the sub-chambers  45   a  and  45   b  through the exhaust ports  49   a  and  49   b  and is transmitted to the thermal exchange unit  204 . The rotation of the rotor body  12  of the expander  10 B 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  10 B 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.