Abstract:
A novel molecular adhesion turbine includes improved disc array, flywheel, housing and nozzle structural designs each adapted to exhibit molecularly repulsive and/or molecularly adhesive properties depending upon the particular working fluid used with the turbine. Backflow turbulence and drag forces are reduced, and turbine operating efficiencies are improved as a result. The invention includes an insulating enclosure, which provides added noise cancellation and heat capture benefits. The new molecular adhesion turbine is modular and thus capable of sealable applications, including connecting the turbine to a bladed steam turbine of the type typically used in power plants for heretofore unrealized downstream energy efficiencies.

Description:
REFERENCE TO RELATED APPLICATION 
       [0001]    This application is a continuation-in-part of U.S. application Ser. No. 14/262,773, filed Apr. 27, 2014, now pending, which is a continuation-in-part of application Ser. No. 13/871,365, filed Apr. 26, 2013, now pending. 
     
    
     BACKGROUND OF THE INVENTION 
       [0002]    The present invention relates generally to the field of systems fir deriving power from moving fluids and, more particularly, to a blade less turbine system. 
         [0003]    Impeller systems for deriving mechanical power from moving fluids are known. U.S. Pat. No. 1,061,206, which I hereby incorporated by reference, describes an apparatus for converting moving fluids to energy by adhesion to a central rotor comprising a set of flat discs with spaces between each disc. As disclosed in U.S. Pat. No. 1,061,206, such apparatus are also operable as fluid pumps. The discs have flat edges and are secured for rotation on a shaft. Working fluid enters an inlet passage tangentially aligned with the discs. The fluid adheres to the discs transferring its energy to the discs to rotate the shaft. 
         [0004]    Each disc has a central opening for the moving fluid to escape from the housing that contains the disc array and shaft. On the other hand, when the discs are rotated by means of an external motor, fluid is elected by the discs through a fluid outlet aligned tangentially with the discs. The mechanical features of this bladeless turbine system and their corresponding inefficiencies are known. The discs are subject to erosion, wear and warping caused by the extreme heat and supersonic rate of flow of the moving fluid over time. 
         [0005]    Turbulence is another problem. The moving fluid is typically in a highly pressurized saturated gaseous state. Imperfections in the surfaces of the discs, the housing and other fluid-directing components, therefore, produce turbulence and hence drag on the system. One example is the fluid intake passage. At (sub/super)sonic flow rates, the working fluid often produces harmonic wave patterns at the intake, which disrupts flow and causes turbulence. The physical properties of the particular moving fluid also impact overall system efficiency. 
         [0006]    Fluid viscosity contributes to the fluid particle size that manifests between the rotating discs. Fluid viscosity and adhesion control the rate at which the fluid moves through the system as well as system energy yields. The mechanical properties of the system such as the shape of the disc, disc spacing and disc mounting/connective structures, for example, should thus be carefully engineered so that the system is optimally efficient regardless of the particular moving fluid used. Another factor influencing the efficiency of a bladeless turbine is the rate at which the fluid exits the stator housing. 
         [0007]    Upon start up of the turbine the moving fluid exits the housing through the outlet ports at a slower rate and the disc array functions at a slower RPM rate than when the turbine is fully operational. Backflow issues are therefore common at start up as a result. As the system picks up speed, the fluid exit rate increases, backflow begins to subside and the pressure of the system equalizes. Initial turbine function and backpressure, however, often delay the time it takes to achieve system equilibrium. 
         [0008]    Other constant tormentors such as radiant heat escape and system vibration constantly discount turbine system energy yields as well. 
         [0009]    There is, therefore, a need for a more efficient bladeless turbine. The present invention is directed toward this need. 
       SUMMARY OF THE INVENTION 
       [0010]    The invention is a modular thermal molecular adhesion turbine for converting moving fluids into mechanical or electrical energy. The new turbine includes an upper removable stator housing with an open horizontally located chamber to accept various nozzle designs and inserts. Various nozzle designs are interchangeable depending upon the temperature, pressure, pounds per hour of working fluid variations, or other factors requiring alternate inlet nozzle designs. The lower stator housing is fastened to a fixed platform and contains low fiction bearing assemblies at each end of the housing to support the main rotor shaft, which is at a horizontal plane in reference to the system configuration. Both upper and lower stator housings have a half circular port at the central exterior and when joined provide a full circular port to exhaust the working fluid from the interior of the stator housing. This fixed port size is maximized to match the full diameter of the exit holes found in the central area of the discs. 
         [0011]    Fitted to the main rotor shaft is a plurality of flat polished discs, which have parabolic end edges instead of fiat and which are coated in repel the incoming working fluid. This modification prevents pitting and erosion of the disc edges while channeling more working fluid into the gap spacing between each disc. Each disc has a male notch that is inserted into the longitudinal female notch running along the length of the central shaft. During the turbine operation the main rotor shaft imparts mechanical rotational power to the preferred electrical conversion source. A spacing washer is positioned between each disc to provide a uniformity of gaps between each. The discs are also coated on both flat sides with greater working fluid adhesion properties near the exterior working area of the disc and working fluid repulsion coating on the surface area nearest the center of the disc. 
         [0012]    These coatings increase the adhesion properties of the working fluid and allow the working fluid to escape through the center holes in each disc with no frictional losses. As mentioned, each disc has openings located near the center with several central spokes supporting the discs and ending in the center to slip onto the main rotor shaft. Each disc spoke has at tapered edge which prevents pitting and erosion when the rotor disc set is operational at very high rotations per minute and working fluid is passing through the internal exhaust channel created by the disc set. The discs have openings near the center so that exhausting working fluid can flow to either side of the internal disc set and exhaust through the turbine stator housing at each end. At the end of each disc set is a single flywheel, which is thicker than the interior discs. 
         [0013]    Each flywheel has a greater diameter than the discs and has a male notch at the flywheel disc edge fitting into a recessed matching female notch in the turbine stator housing inhibiting the working fluid from coming in contact with the outer flywheel disc surface and the turbine stator wall. The exterior of the flywheel is coated with material to act as a repellent to the working fluid preventing any frictional losses from the interaction of the flywheels, working fluid and turbine stator walls. 
         [0014]    The flywheels and discs have a series of small holes close to half the radius length of the discs. Each disc has matching holes in the flat surface area. A series of small diameter stabilization rods fit through each series of disc holes, terminate and attach at each exterior wall of both flywheels and thus, the flywheels and discs rotate as a single unit on the shaft. 
         [0015]    In another aspect of the invention, at the exterior of each side of the turbine stator housing is mounted a tuned port apparatus that can open fully to match the turbine stator exhaust port or can incrementally restrict the exit exhaust hole size to help with leveling internal back pressure during the beginning start up time required by the turbine to reach operational rotations per minute. The working fluid then travels into both exterior exhaust port chambers and exits the system either into the atmosphere, a closed-loop or a complementary condensing unit providing a partial vacuum. 
         [0016]    In another aspect, at least two of the turbines are operatively connected together by a common shaft to form a modular turbine system. A working flowable fluid source, such as a bladed steam turbine, may be operatively connected to an inlet port upstream of the modular turbine system, and an exhaust capture means may be operatively connected to the outlet port downstream of the modular turbine. 
         [0017]    In yet another aspect, an insulative enclosure is provided, which includes an interior assembly that covers the turbine for noise cancellation and an exterior assembly that covers the interior assembly for heat capture. 
         [0018]    One object of the invention is to provide a more efficient bladeless turbine. Related objects and advantages of the invention will be apparent from the following description. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0019]      FIG. 1  is a cutaway side view of the nozzle receptacle and internal rotary discs. 
           [0020]      FIG. 2  is a cutaway of an embodiment of the straight tube nozzle insert. 
           [0021]      FIG. 3  is a cutaway of an embodiment of a convergent/divergent nozzle insert. 
           [0022]      FIG. 4  is a cutaway view of an embodiment of the convergent/anharmonic nozzle insert. 
           [0023]      FIG. 5  is a front view of the nozzle connector flange ring, connector holes and high-pressure o-ring. 
           [0024]      FIG. 6  is a front view of a single internal rotating turbine disc. 
           [0025]      FIG. 7  is a front view of the inter-disc spacer. 
           [0026]      FIG. 8  is a close up view of a disc spoke tapered edge. 
           [0027]      FIG. 9  is a front view of a single side of an embodiment of the rotor disc of the invention showing the molecular adhesion and repulsion coating areas. 
           [0028]      FIG. 10  is a diagrammatic enlarged cutaway view of a partial internal rotor disc array showing disc gap and specialized disc tip. 
           [0029]      FIG. 11  is a front and partial side view of the end flywheel disc with turbine housing notch and coating area facing the internal disc array. 
           [0030]      FIG. 12  is a cutaway view of a single complete modular turbine assembly. 
           [0031]      FIG. 13  is a cutaway view of a typical modular set of turbines connected together. 
           [0032]      FIG. 14  is a side view of the modular turbine enclosure housing and mounting block. 
           [0033]      FIG. 15  is a top cutaway view of a modular turbine set with multiple inlet manifold connections from one working fluid input port. 
           [0034]      FIG. 16  is a side view of the external tunable exhaust port from the turbine stator housing for disc exhaust. 
           [0035]      FIG. 17  is an internal side view of the tunable exhaust apparatus without the gear housing cover. 
           [0036]      FIG. 18  is a cutaway front view of an embodiment of the turbine noise cancellation and thermal heat capture enclosure diagrammatically shown with a turbine. 
           [0037]      FIG. 19  is a diagrammatic top cutaway view of half of the two-stage modular turbine array working fluid pathway through the complementary external exhaust capture apparatus. 
           [0038]      FIG. 20  is a diagrammatic top cutaway view of a bladed steam turbine connected to multiple condensing units. 
           [0039]      FIG. 21  is a diagrammatic top cutaway view of a bladed steam turbine connected upstream of the modular turbine showing the modular turbine array stages one and two with complementary condensing unit and additional modular condensing units connected downstream of the modular turbine. 
       
    
    
     DETAILED DESCRIPTION OF INVENTION 
       [0040]    For the purposes of promoting an understanding of the principles of the invention, specific embodiments have been described. It should nevertheless be understood that the description is intended to be illustrative and not restrictive in character, and that no limitation of the scope of the invention is intended. Any alterations and further modifications in the described components, elements, processes, or devices, and any further applications of the principles of the invention as described herein, are contemplated as would normally occur to one skilled in the art to which the invention relates. 
         [0041]    In this description the terms “working fluid,” “flowable fluid” and “moving fluid” shall have the same meaning, namely a fluid or gas used with the invention to derive energy. Water in the form of saturated steam has been used in this description as only one such example. 
         [0042]    The invention also contemplates the recovery of heat and flowable fluids from both renewable and non-renewable sources where they are otherwise wasted so the may be captured and used in connection with the invention. Heat produced during manufacturing processes and geothermal steam serve as examples. 
         [0043]    With reference to  FIGS. 1-4 , the modular thermal molecular adhesion turbine, herein known as ‘turbine’ begins with the introduction of a working fluid into a nozzle inlet opening  103 . A straight tube nozzle  205  is shown in a cutaway view showing the working fluid flow direction upon entering nozzle inlet opening  103  and exiting through nozzle exit  203  to impart action through working fluid adhesion upon the internal disc array  1203  ( FIG. 12 ) and each singular disc  106 . The interior nozzle coating  204  is a molecular repulsion material to reduce molecular adhesion drag and frictional temperature increases. The area of initial working fluid contact with the internal disc array  1203  occurs at the back-end half of nozzle  203 . The turbine stator housing  105  has a receptacle  104  or replaceable nozzle shaft cavity, which allows for easy replacement of various nozzle types. 
         [0044]    Each removable nozzle design attaches to the turbine stator housing flange  102  with the corresponding nozzle flange  101  and is fastened through a set of hardware with acceptable matching holes  503 , as shown in  FIG. 5 . A high-pressure gasket  502  is inserted between the turbine stator Range  102  and each replaceable nozzle flange  101 . In one embodiment, a high pressure saturated steam gasket  502  made of inorganic fibers with a nitrite binder is used to seal the nozzle flange  101  to the corresponding housing flange  102  using high strength threaded studs with steel washers and nuts and barrier dielectric washers and bolt sleeves. 
         [0045]    There are many nozzle designs that can be made adaptable to the turbine stator nozzle shaft cavity  104 . In one embodiment, a straight tune nozzle is used. In a more preferred embodiment, a convergent/divergent nozzle may be used, and most preferably, a specially engineered convergent/anharmonic nozzle is applied. A typical straight tube nozzle  205  is used when the working fluid has sufficient fluid power and speed of movement to bring the internal disc array  1203  to the desired operational rotations per minute. The working fluid travels through the fluid flow path  201  of the straight tube housing shell  202  and enters the turbine stator housing  105  unimpeded. 
         [0046]    In another embodiment, a convergent/divergent nozzle design, as shown in  FIG. 3 , has a working fluid flow chamber  301  housed in a rigid shell  302  that allows the working fluid to enter at nozzle inlet opening  103  and travel through nozzle exit  301  into the turbine stator housing  105 . This design is for lower power and fluid speeds imparted in the working fluid used. The convergent/divergent nozzle design has an internal flow reduction neck  303 , which increases the speed of the working fluid from subsonic to supersonic speeds. The convergent/divergent nozzle design  304  is customized for constant working fluid speeds and does not work at its most efficient with variable or intermittent working fluid speeds. 
         [0047]    In one embodiment, the working fluid is saturated steam. In that embodiment, a convergent/anharmonic nozzle  406  is preferably constructed using a solid rod stock of high temperature steel such as 17-22-XX-grade steel. The solid rod stock may be CNC core drilled in stages to provide the correct internal multiple-tapering sections and end boring to produce a structurally sound replaceable nozzle flange  101 . The reduction neck compresses the incoming working fluid at subsonic speeds and releases the working fluid at supersonic speed prior to entering the stator housing  105 . The multiple stepped flow chambers  402 ,  403 , and  404  do not allow the working fluid to produce harmonic wave patterns inside the flow chamber  401  and thus prevent turbulence. 
         [0048]    The outer and inner diameters of the anharmonic rigid shell  405  are formed to compensate for the incoming steam pressure and flow characteristics to ensure proper reduction of the internal working fluid turbulence. A thicker shell with an increased outer diameter is required to handle more highly pressurized working fluid while the opposite is the case with lower pressure fluid. The size of the inner diameter of the rigid shell therefore may be predetermined accordingly. Referring to  FIG. 4 , a phantom line depicts the portion of the long axis that extends the length of the anharmonic extension chamber of the nozzle. In one embodiment the divergent portion of the interior passage of the nozzle and the long axis of the passage define at least two angles for canceling acoustic resonance frequency peaks of the working fluid. Turbulence typically produced by the resonance of pressurized fluid in turbine applications cannot thus multiply exponentially. In another embodiment, the divergent portion of interior passage of the nozzle defines three angles. Referring to  FIG. 4 , the passage angles or “steps” are defined according to the following. 
         [0049]    Steps,  402  {S 1 },  403  {S 2 }, &amp;  404  {S 3 }
   A x =total length  407 , 2 decimal place percentages represented in embodiment   
 
         [0000]        A   x   ={S   1   }˜A   x /6.9686 [R\Q]+{S   2 }˜1.9846 [R\Q]×S   1   +{S   3 }˜2.007 [R\Q]×S   2  
 
         [0000]    Angular degree, V 1 , V 2  &amp; V 3 , where I 1  is the length of the inner diameter of the passage at  408  and E 1  is the length of the inner diameter of the passage at  409 . 
         [0000]      (( E   1   −I   1 )/2)×15.45%=√(( S   1 ) 2 −(cos V   1   ×S   1 ) 2 )
 
         [0000]      (( E   1   −I   1 )/2)×27.48%=√(( S   2 ) 2 −(cos V   2   ×S   2 ) 2 )
 
         [0000]      (( E   1   −I   1 )/2)×27.51%=√(( S   3 ) 2 −(cos V   3   ×S   3 ) 2 )
 
         [0051]    When using saturated steam as the working fluid, the three “steps” of the chambers  402 ,  403  and  404 , as a percentage of the total length  407 , along with their corresponding angles are, approximately: 14.35% and 8.1 degrees; 28.48% and 6.2 degrees; and 57.17% and 4.3 degrees. 
         [0052]    With respect to this embodiment of the nozzle, the term “steps” is used for convenience in understanding the transition in the interior diameter of the chamber wall and is not intended to necessarily suggest the interior wall of the chamber is not consistently sloped or includes non-smooth annular surfaces. Additionally, each of the aforementioned angles are defined by extrapolating the appropriate portion of the inner chamber wall and the long axis (shown in phantom) until they meet to define an angle. The dissimilar non-integer related angles and corresponding wall lengths prevent flowing fluid harmonics from being produced at any fluid flow speed or pressure. Values, including those corresponding to E 1  and I 1 , are dependent upon the particular working fluid used. 
         [0053]    With saturated steam as the working fluid, a hydrophobic coating is applied to the internal surfaces of the anharmonic fluid flow chamber  401 . An amorphous carbon film about 3 microns in thickness is coated on the high temperature steel by close field unbalanced magnetron sputter ion plating. This coating will provide the hydrophobic properties needed to repel steam particles from adhering to the surface of the convergent/anharmonic fluid flow chamber  401  and provide heat and wear resistance needed for extended operations. As the working fluid exits the selected nozzle design it enters the interior turbine stator housing  105  and begins imparting force on the internal disc array  1203  along the interior disc fiat surface  601  ( FIG. 6 ). 
         [0054]    The disc material will be of high tensile strength metal, plastic, alloy or composite. Internal disc material selection will be based on compatibility with the particular working fluid type. In the exemplary embodiment, the working fluid is saturated steam, which interacts with the disc flat surface  601 . The disc material may be Inconel Alloy 718 which is a precipitation hardenable nickel-based alloy designed to display exceptionally high yield, tensile and creep-rupture properties at temperatures up to 1300° F. This material is preferable when using saturated steam as the working fluid. Based on the extremely high tensile strength of Inconel Alloy 718 the internal disc array  1201  can be operated at RPMs of over 100,000. Discs can be cut from flat stock using high-speed CNC milling practices, electropolished and mechanically buffed for an ultra smooth surface needed for higher hydrophilic properties of the metal alloy surface. 
         [0055]    Each internal rotating disc  601  is comprised of a polished flat surface, interconnected multi-disc stabilization holes  602 , center disc opening for internal rotating main shaft  603 , center disc male notch  604  for main rotating shaft  1205 , multiple disc openings  606  for spent working fluid exhaust, supporting multiple internal disc spokes  607  and tapered disc spoke edge  608 . The working fluid comes in contact With the exterior disc surface  601  and during disc rotation follows a decreasing circular path until it reaches the disc openings  606  and exits the center of the rotating disc array  1203  through the stator housing exhaust ports  1605  ( FIG. 16 ). Disc opening  606  in another embodiment can be of various disc openings  609  shapes and sizes so that a wide variety of working fluids can exit the disc openings  606  more efficiently traveling through the decreasing circular flow path ensuring that low adhesion working fluids exit the disc opening  606  prior to the point at which the working fluid causes frictional drag without imparting additional energy to the modular thermal molecular adhesion turbine system. This variable opening area will match the molecular adhesion properties of the working fluid used and allow for weaker adhesion working fluids to exit the system without the spent working fluid causing frictional drag. The tapered disc spoke edges  608  decrease erosion and pitting that flat surface spoke edges would have by cutting through the internal working fluid flow exiting the disc openings  606  instead of hitting the working fluid at a perpendicular angle. In ( FIG. 8 ) it is shown the parabolic tip  801  and a close up view of the spoke taper  608  in relation to the working fluid flow path. 
         [0056]    A specific parabolic formula generates the characteristic tapered angle and distance from the beginning of the disc taper to the center point of the parabolic disc tip  801  that is ideal for the physical properties of said working fluid. Following on with the saturated steam example, the formulaic example uses the average steam particle size of 0.015625″ diameter and the fixed disc thickness of 0.03125″. As the steam particle adheres to the Inconel disc surface with a hydrophilic coating of magnesium zirconate the wetted steam particle is pressed down and the distance from the disc surface to the quadrant of the outer circumference of the steam particle decreases to 0.0078125″. By adding the thickness of both the adhered disc sides and free steam particles flowing through the medial disc gap the sum would be 0.03125″. This gap distance, therefore, is ideal for the given estimated average saturated steam particle size to both adhere and impact causing rotational movement in the disc array  1203 . 
         [0057]    The preferred parabolic shape of the disc end tip for a saturated steam application is thus obtained using formula Y=0.6×(½X) 2  where Y is the thickness of the disc (in inches) and X is the distance for the perpendicular point Y to the center point of the parabolic disc tip. Thus, using a disc thickness of 0.03125″ and the average water (steam) particle diameter 0.015625 yields a tip height of 0.0375″ and a taper angle of 4.75 degrees for a disc width of 0.03125″ and saturated steam used as the working fluid. If compressed pressurized air were being used as the working fluid the tip height would be greater and the taper angle would decrease due to smaller average working fluid particle size. 
         [0058]    Beginning at the midpoint of the disc array  1203  each disc  601  to the left of center has the spoke taper  608  facing from the left exiting working fluid flow likewise each disc  601  to the right of center has the spoke taper  608  facing from the right exiting working fluid flow. This directional taper design acts as an additional motive force aiding the working fluids exhaust path from the internal center disc openings  606  to the turbine stator external exhaust ports  1605 . A central disc spacer  605  is placed in-between each disc  601  to provide uniform gap spacing  1002  ( FIG. 10 ) between each disc  601 . 
         [0059]    When the working fluid is saturated steam, the gap spacing  1002 , central disc spacer  605 , gap spacing between the discs  601  and flywheels  1107  ( FIG. 11 ), and the disc thickness should all be 0.03125″. This spacing allows for the saturated steam particles to adhere to the disc surfaces and allow enough room for non-adhering steam particles which are just above the planar surface of the discs to impact the adhering steam particles thus providing contact movement to the rotating discs  601 . If compressed pressurized air were to be used as the working fluid then the gap spacing would decrease to 0.006125 due to the decreased molecular size of the working fluid particles. 
         [0060]    The gap spacing  1002  is variable in size depending on the type of working fluid to be used. Each disc spacer  605  has a central hole  701  ( FIG. 7 ) which fits on the main rotor shaft  1205  to separate each disc  601  and also in-between discs next to the flywheels  1107  ( FIG. 11 ). Each disc  601  side has specialized molecular adhesion and repulsion coating areas ( FIG. 9 ) increasing the energy imparted by the working fluid and aids in the spent working fluid exhaust speed into the central disc openings  606 . The molecular adhesion and repulsion coatings are matched to the type of working fluid that is used in the turbine system. The adhesion coating area  901  is applied to the outer disc  601  so that the maximum conversion of energy from the working fluid is realized. 
         [0061]    The molecular repulsion coating area  902  is applied to the outer disc  601  so that the working fluid does not incur unneeded frictional resistance as it exits the central disc openings  606 . The phantom line  903  of  FIG. 9  identifies the barrier between the molecular adhesion coating  901  and molecular repulsion coating  902 . The parabolic disc edges  1001  are coated with molecular repulsion material, which directs working fluid into the disc nap spacing  1002  without frictional losses and prevents pitting and erosion. 
         [0062]    In one embodiment, the molecular repulsion coating for saturated steam can be an amorphous carbon film about 3 microns in thickness coated on the high temperature steel by close field unbalanced magnetron sputter ion plating. For this application, areas that may require this coating are the inner disc area  902 , disc spokes  607 , disc spoke tapered edges  608 , parabolic disc tips  801 ,  1001 , interior flywheel area  1108  and the internal flywheel inner diameter. The internal aluminum stator housing will be also coated with a hydrophobic polymer, polytetrafluoroethylene, which is heat resistant up to 536 degrees F. and highly wear resistant. Areas needing hydrophilic coatings, when saturated steam is used as the working fluid, are the inner disc area  901  and the internal flywheel area  1104 . One type of coating for high hydrophilic properties can be plasma sprayed magnesium zirconate which also provides a very good heat and abrasion resistant permanent layer. 
         [0063]    Disc array  1203  has two end flywheels  1107  that are slightly greater in diameter than the discs  601  and are notched  1101  and  1102  at the end to fit into the female notch in the internal turbine stator housing  105 . The flywheel notch  1103  provides a nearly complete barrier to the working fluid front entering the area in-between the turbine stator housing  105  and the exterior of the flywheel disc surface  1108 . Frictional interaction of the working fluid between the rotating external flywheel surface  1108  and the turbine stator housing  105  is further reduced by coating the external flywheel surface  1108  and coating the internal turbine stator housing walls  1003  with molecular repulsion material. The near total reduction of frictional losses improves the overall turbine efficiency. The molecular adhesion coating is applied to the flywheel interior surface  1109  at area  1104  and the molecular repulsion coating is applied to the flywheel interior surface  1109  at area  1105  and to both the flywheel spokes  1111  and flywheel spoke tapers  1110 . There is a boundary line  1106  between the two coating areas that will vary with changes in disc diameter and the type of working fluid used in the turbine system. 
         [0064]    With reference to  FIG. 12 , a cutaway view of the entire modular turbine assembly  1213  shows the upper half of the turbine disc assembly housing  1201 , lower half of the turbine disc assembly housing  1202 , internal rotor disc array  1203 , working fluid exhaust shell  1204 , internal main rotor shaft  1205 , single shaft connection  1206 , rotor Shaft extension  1207  for reduction gear attachment, then to generator/alternator  1212 , external exhaust port for working fluid  1208 , external exhaust port connector flange  1209 , internal cavity of the main exhaust chamber  1210  and modular rotor shaft interconnect dual shaft connection  1211 . The working fluid enters the upper turbine stator housing  1201  from the nozzle exit  203  and imparts energy to the disc array  1203 . The working fluid exits the central disc array  1203  through the multiple disc openings  606  and exhausts through the turbine stator housing side ports  1605 . The working fluid then travels through the internal cavity of the main exhaust chamber  1210  and exits the external exhaust port  1208  into a closed-loop system, the front end expander area of at complementary external exhaust capture apparatus unit  1914  ( FIG. 19 ) or into the atmosphere. The modular rotor shaft interconnect single shaft connection  1206  can be replaced with the modular rotor shah interconnect dual shaft connection  1211  joining another modular turbine to the system. 
         [0065]    An example of the modularity of the turbine is shown in ( FIG. 13 ) with a single unit modular turbine  1301  operatively connected to three additional single unit modular turbine  1301  assemblies to form a final group of four turbine units  1302 . Any number of single unit modular turbine  1301  assemblies can be connected together for use with any expanded working fluid system. 
         [0066]    Side view of the exterior of the modular turbine enclosure housing including both locking bracket and mounting block are shown in  FIG. 14 . This drawing identifies the assembly parts for the exterior turbine housing, which includes the upper locking bracket for multiple modular turbines in tandem  1401 , lower turbine stator housing flange connector  1402 , upper turbine stator housing flange connector  1403 , frictionless bearing assembly  1404 , mounting bracket for bearing assembly and interconnect for base mounting plate and upper locking bracket  1405 , base mounting plate for modular turbine array  1406  and upper turbine stator chamber receiver for interchangeable nozzle types  1407 . To connect more than one modular turbine together, the mounting bracket for bearing assembly and interconnect for base mounting plate and upper locking bracket  1405  is removed then additional modular single turbine units  1301  are added. Also, the base mourning plate for modular turbine array  1406  will be customized to it additional modular single turbine units  1301  when added. The frictionless bearing assembly  1404  reduces shaft friction and improves efficiency. 
         [0067]    When multiple modular single turbine units  1301  are connected together to form a group, for example a four unit modular turbine set  1302 , a custom manifold  1507  ( FIG. 15 ) is required. This drawing comprises the interconnects for the manifold  1507 , upper housing  1201  and the lower housing  1202  all being joined together by the upper locking bracket  1401  through the upper locking bracket holes  1501  for connection to the upper turbine stator housing flange  1403  and manifold  1507 , external exhaust port chamber  1502 , multiple exhaust manifold connector flange  1503  which interconnects with nozzle insert connector flange  101  and turbine stator housing nozzle chamber flange  102 , multiple exhaust manifold chamber shell  1504 , working fluid path prior to turbine nozzle inlet  1505 , working fluid input port  1506  and the final customized manifold  1507 . The manifold  1507  is connected by the manifold flange  1503  to both the nozzle flange  101  and the turbine stator housing flange  102  by through-hole fasteners and each flange has an inserted high pressure o-ring  502  between each flange connection. Working fluid enters the manifold  1507  through the manifold input port  1506  and is distributed evenly to each working fluid path  1505  prior to each turbine nozzle inlet  103 . 
         [0068]    The upper exterior turbine stator housing  1204  allows for mounting the tunable exhaust base plate  1703  ( FIG. 17 ) which holds in place the nine tuning blades and provides fastening points for the minor rotating tuning gear  1701 , the main gear  1705 , rotational expander channels  1706  for tuning blades  1602  and slider pegs  1708 . The main gear  1705  has matching sprocket teeth  1704  interacting with the minor rotation tuning gear sprocket teeth  1702  to adjust the rotational blades  1602  for varied exhaust port  1604  diameter. This tunable exhaust port assembly  1709  allows the working fluid exhaust pressure to be adjusted to prevent excess backpressure in the turbine system. 
         [0069]    This embodiment shows the invisible view of the edge of the tuning blades  1707  which are expanded and contracted through the fixed slider pegs  1708  moving through the expander channels  1706 . The tunable port gear housing cover  1601  is fastened to the upper turbine stator housing  1201  and the lower turbine stator housing  1202  and provides an opening for the rotor shaft  1205  to exit through the main exhaust port  1605 . An end view of the main shaft  1603  can be seen in relation to the rotational blades  1602  inside the tunable port gear housing cover  1601 . 
         [0070]    At the beginning of the introduction of saturated steam into the turbine the tunable exhaust apparatus  1709  would be completely constricted making the exhaust port diameter  1604  small preventing the internal pressure and temperature of the saturated steam from decreasing during start up conditions. During start up the RPM of the internal disc array  1203  increases as does the exhaust port diameter to prevent backpressure from building inside the stator turbine housing  105 . At operational RPM the exhaust port diameter  1604  is fully open allowing free flowing spent saturated steam to exit the system as hot condensed water. 
         [0071]    Heat loss from the modular single turbine assembly  1301  will be prevented through the installation of a noise cancellation and thermal heat capture enclosure  1809  ( FIG. 18 ). This three-piece enclosure drawing shows the final enclosure cover for the matched triple-insulated turbine noise cancellation and thermal heat capture side coupling assembly  1801 , hollow interior of the final enclosure  1802 , low density thermal insulating foam and noise canceling material  1803 , rigid structural box frame material  1804 , vacuum impregnated panel (VIP) matched pair sub assembly  1804 , flexible double ply steel mesh to absorb minimal vibrational impact from normal turbine operation  1805 , matched set of VIP, thermal insulating foam and noise canceling sub assemblies  1806 , final enclosure opening which slips over and encloses the matching sub assembly shells when applied against the turbine  1807  and turbine outline  1808 . Preventing heat from escaping the turbine through the exterior sides increases the efficiency of the heat engine and also cancels out unwanted noise. 
         [0072]    As a follow on to the saturated steam example, the modular thermal molecular adhesion turbine  1213  is shown in a modular stacked two-phase grouping  1913  ( FIG. 19 ) with a complementary external exhaust capture apparatus  1914  attached. The modular stacked two phase grouping  1913  and complementary external exhaust capture apparatus  1914  will replace the common Condenser unit  2013  ( FIG. 20 ) at the backend of a typical bladed steam turbine  2012 . Bladed steam turbines are used in power plants and serve here as an example of an upstream working flowable fluid source that is operatively connected to the inlet port of the modular turbine. The bladed turbines produce waste exhaust comprised of high pressure and temperature saturated steam. This drawing shows a top cutaway view of the modular stacked two phase grouping  1913  and a saturated steam flow pathway through the system ending with its exit into the complementary external exhaust capture apparatus  1914 . In this embodiment, the external exhaust capture apparatus  1914  is a common cold water tube condensing unit with an external vacuum pump to provide positive flow of the hot condensate exiting the modular stacked two phase grouping  1913 . 
         [0073]    The assembly parts of the modular stacked two phase grouping  1913  consist of a modular turbine array connector flange  1901 , common industrial steam turbine exhaust flange  2014 , top tier inlet  1920 , modular turbine array manifold  1507 , mid tier exhaust inlet  1903 , sub tier exhaust inlet  1902 , two stage modular turbine arrays  1907 ,  1908 , exterior housing  1904 , main rotor shaft extension  1905 , minor rotor shaft extension  1906 , expander exhaust tube  1909 , capillary expander joint inlet  1910 , external partial vacuum pump piping  1911 , modular turbine array separation housing  1912 , and complementary external exhaust capture apparatus unit  1914 . In this embodiment, the modular turbine array  1913  and complementary external exhaust capture apparatus unit  1914  connects to the waste exhaust from a common bladed steam turbine  2012  ( FIG. 20 ) and converts the waste exhaust into mechanical or electrical energy. The modular turbine array  1913  has a complementary external exhaust capture apparatus  1914  which uses the exiting working fluid energy and external vacuum pump system to create a partial vacuum assisting in forward flow of the working fluid throughout the entire modular turbine array  1913  system increasing overall mechanical or electrical output. Other embodiments call for vacuum means also in fluid communication with the modular turbine for creating at least a partial vacuum in a housing of the modular turbine. A nonexclusive list of vacuum means includes inert means, ambient heat differentials, condenser means, a vacuum pump and vacuum produced by the rotary action of the heat engine/turbine itself. 
         [0074]    In the example illustrated, waste saturated steam exhaust leaves the common bladed steam turbine  2012  from exhaust chamber  2005  and enters multiple exhaust inlets of type  1902 ,  1903  and  1920 . There are four levels of the modular stacked two-phase grouping  1913  which are not shown on this drawing ( FIG. 19 ) but are also fed by the bladed steam turbine exhaust  2005 . Saturated steam enters each individual modular turbine assembly  1213  and produces mechanical energy that is transferred to the main rotor shaft extension  1905 , which runs an external generator  1212 . As saturated steam exits the first stage modular turbine array  1907  it enters the second singe modular turbine array  1908  through the exhaust to inlet array connector  1917  to produce additional mechanical energy Which is transferred to the minor rotor shaft extension  1906  which runs an external generator  1212 . In this example, a vacuum is pulled by an external vacuum pump tube  1911  which aids the exiting hot water from the second stage modular turbine array  1908  exhaust into the expander exhaust tube  1909  array and then into a common cold water tube condensing unit  2105  ( FIG. 21 ) with an external vacuum pump to provide positive flow of the hot condensate exiting the modular stacked two phase grouping  1913 . Other embodiments employ any one or a combination of vacuum means described above. 
         [0075]    A common bladed steam turbine  2012  and a joined modular condenser unit  2013  are shown coupled ( FIG. 20 ). This is just one type of waste exhaust system producing saturated steam waste gas that can be used by the modular stacked two phase grouping  1913  to produce mechanical to electrical energy without additional fuel. 
         [0076]    The main assembly parts, interconnects and waste gas flow path include inlet for high-pressure, high temperature superheated steam working fluid  2001 , stage one expander steam turbine blades  2002 , stage two expander steam turbine blades  2003 , stage three expander steam turbine blades  2004 , common bladed steam turbine high pressure saturated steam exhaust chamber  2005 , common bladed steam turbine  2012  high pressure saturated steam exhaust chamber diverted downward flow  2006 , multi condenser unit chiller tube matrix  2007 , common condenser expander area typical in all modular condenser additions  2008 , area for additional modular condenser units based on increased exhaust from common steam turbine base unit enlargement  2009 , common condenser expander housing shell  2010  and the flow path of high pressure saturated steam from common steam turbine final exhaust port  2011 . A great deal of waste energy is lost through the practice of using a common bladed steam turbine  2012  to produce energy from fossil fuels and other non-renewable energy sources worldwide. 
         [0077]    When the two-phase turbine array  2101  is placed at the end exhaust of a common bladed steam turbine  2012  the exiting waste gas will be converted into usable mechanical or electrical energy without additional fuel. A typical cold water tube condensing unit  2105  is connected to the exhaust end of the two-phase turbine array  2101  which allows the exiting hot condensate to enter the condensing chamber  2102  flow over the cold water tube array  2103  and exit the condenser through dry bulb temperature condensate port  2104 . 
         [0078]    While the invention has been illustrated and described in detail in the drawings and foregoing description, the same is to be considered illustrative and not restrictive in character. It is understood that the embodiments have been shown and described in the foregoing specification in satisfaction of the be mode and enablement requirements. It is understood that one of ordinary skill in the art could readily make a nearly infinite number of insubstantial changes and modifications to the above-described embodiments and that it would be impractical to attempt to describe all such embodiment variations in the present specification. Thus, it is understood that it is desirable to protect all the changes and modifications that come within the spirit of the invention.