Boundary layer effect turbine

Abstract

Described herein are embodiments of a boundary layer effect turbine and a hydrodynamic speed reducer. Described is a boundary layer effect turbine that utilizes the phenomena of the boundary layer to drive a turbine impeller that is made of a plurality of spaced disks oriented along a rotatable shaft. As operating fluid is directed over surfaces of the plurality of disks of the boundary layer effect turbine, energy is transferred from the fluid to the disks as a result of the adhesive and viscous properties of the fluid.

1 . A modified boundary layer turbine, comprising:
 a housing having a fluid inlet port and a fluid outlet port;   a central shaft, extending through the housing, the central shaft defining a central axis;   a plurality of annular disks within the housing, each of the disks having a face and being spaced apart from an adjacent disk such that the faces of the disks are substantially parallel;
 wherein each of the disks has an outer edge, and an inner opening through which the central shaft extends; 
 wherein the plurality of annular disks is configured in the housing to transmit kinetic energy between at least one of the disks, as it rotates about the central shaft, and fluid introduced into the housing through the fluid inlet port, the transmission of kinetic energy resulting, at least in part, from a boundary layer formed at the face of at least one of the disks; and 
   a plurality of elongate, arcuate elevations extending along the face of at least one of the disks, each of the arcuate elevations having a first region and a second region;
 wherein the first region of each of the arcuate elevations is located closer to the central axis than is the second region of the same arcuate elevation; and 
 wherein each of the arcuate elevations tapers in width as it extends from the first region to the second region, such that a width of each of the arcuate elevations at its first region is greater than a width of the same arcuate elevation at its second region. 
   
     
     
         2 . The modified boundary layer turbine of  claim 1 , wherein the arcuate elevation comprises substantially an airfoil shape. 
     
     
         3 . The modified boundary layer turbine of  claim 1 , wherein the arcuate elevation has a thickness equal to about one-half of a space between adjacent disks. 
     
     
         4 . The modified boundary layer turbine of  claim 1 , wherein the arcuate elevation has a thickness less than one-half of a space between adjacent disks. 
     
     
         5 . The modified boundary layer turbine of  claim 1 , wherein, during rotation of the central shaft, the plurality of arcuate elevations directs fluid flowing across the face of the disk in a radially outward direction. 
     
     
         6 . The modified boundary layer turbine of  claim 1 , wherein, during rotation of the central shaft, the plurality of arcuate elevations directs fluid flowing across the face of the disk in a radially inward direction. 
     
     
         7 . The modified boundary layer turbine of  claim 1 , wherein at least one of the arcuate elevations comprises a thickness equal to about the thickness of a laminar flow boundary layer of a fluid that flows into the housing from the fluid inlet port and across the face of at least one of the disks. 
     
     
         8 . The modified boundary layer turbine of  claim 1 , wherein at least two of the disks with a space between them equal to two boundary layer laminar flow thicknesses. 
     
     
         9 . The modified boundary layer compressor of  claim 1 , wherein at least two of the disks are spaced to allow air compression to take place in the fringe of the laminar flow zone. 
     
     
         10 . The modified boundary layer turbine of  claim 1 , wherein at least one of the arcuate elevations are integrally formed with at least one of the plurality of annular disks. 
     
     
         11 . The modified boundary layer turbine of  claim 1 , wherein at least one of the arcuate elevations comprises a different material than does the at least one of the disks. 
     
     
         12 . The modified boundary layer turbine of  claim 1 , wherein the central shaft is integral with a starter generator and is supported by at least one magnetic bearing. 
     
     
         13 . The modified boundary layer turbine of  claim 1 , wherein the central shaft is supported by at least one air bearing. 
     
     
         14 . The modified boundary layer turbine of  claim 1 , further comprising a combustor having an annular excess air bypass control system that facilitates combustion management by sending air either through a plurality of venturi burners or through a bypass. 
     
     
         15 . A boundary layer turbine, comprising:
 a housing having a fluid inlet port and a fluid outlet port;   a central drive shaft, extending through a central portion of the housing, the central drive shaft defining a central axis;   a plurality of annular disks, within the housing, arrayed along and coupled to the central drive shaft;
 wherein each of the plurality of the annular disks has a front face and a rear face and is positioned along the central axis such that a plurality of substantially parallel annular spaces is defined between adjacent faces of the plurality of the annular disks; 
 wherein the plurality of the annular disks define a cylindrical space located central to inner edges of the annular disks, the cylindrical space containing the central drive shaft; 
   a blade member extending, in the cylindrical space, from the central drive shaft toward the inner edges of the annular disks, the blade member further extending helically about the central axis;   wherein, during rotation of the central drive shaft, fluid located in the annular spaces is drawn in the direction of rotation in a boundary layer within the annular spaces; and   wherein, during rotation of the central drive shaft, fluid in the cylindrical space is received along the cylindrical space from the fluid inlet port and directed radially outwardly through the annular spaces.   
     
     
         16 . The boundary layer turbine of  claim 15 , wherein the blade member has width that extends from an interior edge of the blade member, located adjacent the central shaft, to an outer edge of the blade member that is closer to at least one of the plurality of the annular disks than is the interior edge;
 wherein the blade member is curved along its width.   
     
     
         17 . The boundary layer turbine of  claim 15 , wherein the inner edge of at least one of the plurality of the annular disks is tapered. 
     
     
         18 . The boundary layer turbine of  claim 15 , wherein an outer edge of at least one of the plurality of the annular disks is tapered. 
     
     
         19 . The boundary layer turbine of  claim 18 , wherein the inner edge of the at least one of the plurality of the annular disks is tapered. 
     
     
         20 . The boundary layer turbine of  claim 15 , wherein at least one of the plurality of the annular disks comprises a plurality of elongate, arcuate elevations extending along the face of the at least one of the disks, each of the arcuate elevations having a first region and a second region;
 wherein the first region of each of the arcuate elevations is located closer to the central axis than is the second region of the same arcuate elevation; and   wherein each of the arcuate elevations tapers in width as it extends from the first region to the second region, such that a width of each of the arcuate elevations at its first region is greater than a width of the same arcuate elevation at its second region.   
     
     
         21 . The boundary layer turbine of  claim 15 , further comprising a plurality of blade members extending, in the cylindrical space, from the central drive shaft toward the inner edges of the annular disks, each of the plurality of blade members further extending helically about the central axis. 
     
     
         22 . The modified boundary layer turbine of  claim 15 , wherein the central shaft is supported, during rotation, by at least one magnetic bearing. 
     
     
         23 . The modified boundary layer turbine of  claim 15 , wherein the central shaft is supported, during rotation, by at least one air bearing. 
     
     
         24 . A disk turbine impeller, comprising:
 a plurality of substantially parallel annular disks, axially spaced along a rotation axis, the annular disks defining a cylindrical space extending through a center portion of the annular disks and bounded by inner edges of the annular disks;
 wherein the plurality of annular disks define a plurality of annular spaces between adjacent of the annular disks; and 
   a plurality of axial vanes that extend, within the cylindrical space, toward the inner edges of the annular disks from the rotation axis;   wherein the axial vanes are oriented helically about the rotation axis.   
     
     
         25 . The disk turbine assembly of  claim 24 , wherein the blade member has width that extends from an interior edge of the blade member, located adjacent the rotation axis, to an outer edge of the blade member that is closer to at least one of the plurality of the annular disks than is the interior edge;
 wherein the blade member is curved along its width.   
     
     
         26 . The disk turbine assembly of  claim 24 , wherein the inner edge of at least one of the plurality of the annular disks is tapered. 
     
     
         27 . The disk turbine assembly of  claim 24 , wherein an outer edge of at least one of the plurality of the annular disks is tapered. 
     
     
         28 . The disk turbine assembly of  claim 27 , wherein the inner edge of the at least one of the plurality of the annular disks is tapered. 
     
     
         29 . The disk turbine assembly of  claim 24 , wherein at least one of the plurality of the annular disks comprises a plurality of elongate, arcuate elevations extending along a face of the at least one of the disks, each of the arcuate elevations having a first region and a second region;
 wherein the first region of each of the arcuate elevations is located closer to the rotation axis than is the second region of the same arcuate elevation; and   wherein each of the arcuate elevations tapers in width as it extends from the first region to the second region, such that a width of each of the arcuate elevations at its first region is greater than a width of the same arcuate elevation at its second region.   
     
     
         30 . The disk turbine assembly of  claim 24 , further comprising a plurality of blade members extending, in the cylindrical space, from the rotation axis toward the inner edges of the annular disks, each of the plurality of blade members further extending helically about the rotation axis.