Boundary layer turbomachine

Abstract

A boundary layer turbomachine ( 100 ) can include a housing ( 110 ) defining an interior space ( 115 ) and having an inlet opening ( 112 ) and an outlet ( 113 ) opening to facilitate movement of a fluid through the housing ( 110 ). The boundary layer turbomachine ( 100 ) can also include a rotor assembly ( 120 ) disposed in the rotor chamber ( 117 ) and configured to rotate about an axis of rotation ( 101 ). The rotor assembly ( 120 ) can have a plurality of disks ( 121 ) spaced apart along the axis of rotation ( 101 ) and defining an interior opening along the axis of rotation ( 101 ). The fluid can pass through gaps between the disks ( 121 ) and the interior opening as the fluid moves through the housing ( 110 ). Corresponding rotor assembly and partition are also provided.

1 . A boundary layer turbomachine, comprising:
 a housing defining an interior space and having an inlet opening and an outlet opening to facilitate movement of a fluid through the housing;   a partition circumferentially dividing the interior space into an outer chamber and a rotor chamber located radially inward of the outer chamber, the partition having partition openings such that fluid is movable through the partition between the outer chamber and the rotor chamber; and   a rotor assembly disposed in the rotor chamber and configured to rotate about an axis of rotation, the rotor assembly having a plurality of disks spaced apart along the axis of rotation and defining an interior opening along the axis of rotation, wherein the fluid passes through gaps between the disks and the interior opening as the fluid moves through the housing.   
     
     
         2 . The boundary layer turbomachine of  claim 1 , wherein the plurality of disks are oriented perpendicular to the axis of rotation. 
     
     
         3 . The boundary layer turbomachine of  claim 1 , wherein the disks are spaced apart by a distance equal to 3 to 10 times a boundary layer thickness of the fluid by a plurality of spacers, wherein the spacers are optionally confined to a region within one-third of a radius of the disks, and wherein the spacers are optionally arranged in a ring configuration across each disk. 
     
     
         4 . The boundary layer turbomachine of  claim 1 , wherein the disks are coupled to one another by a plurality of fasteners which pass through the plurality of disks. 
     
     
         5 . The boundary layer turbomachine of  claim 1 , wherein outer edges of the disks are tapered. 
     
     
         6 . The boundary layer turbomachine of  claim 1 , wherein the rotor assembly includes an extension member to couple the rotor assembly to the housing and facilitate rotation of the rotor assembly about the axis of rotation, wherein the extension member optionally includes a vent port extending therethrough in fluid communication with the interior opening. 
     
     
         7 . The boundary layer turbomachine of  claim 1 , further comprising a flywheel coupled to the rotor assembly, wherein the flywheel optionally includes an electricity generation member. 
     
     
         8 . The boundary layer turbomachine of  claim 1 , wherein the inlet opening is associated with the outer chamber such that the outer chamber serves as an expansion chamber for the fluid. 
     
     
         9 . The boundary layer turbomachine of  claim 8 , wherein a cross-section of the outer chamber is uniform 360 degrees about the axis of rotation. 
     
     
         10 . The boundary layer turbomachine of  claim 1 , wherein the partition openings are equally spaced circumferentially around the partition and the partition openings are defined by a number of partition members, wherein the number of the partition members is 8 or equal to the nearest whole number of units of 2.54 cm within an outer diameter of the plurality of disks divided by 2 whichever is greater. 
     
     
         11 . The boundary layer turbomachine of  claim 10 , wherein a radius of the inlet surface which forms a portion of a partition opening inlet is within 5% of 1.5 times a radial thickness of the partition member, wherein each partition member optionally has an outlet surface radius forming a portion of a partition opening outlet within 5% of one-third of the inlet surface radius. 
     
     
         12 . The boundary layer turbomachine of  claim 10 , wherein one of the partition members is located such that a midpoint of the partition member is offset by 51% of a length of the partition member from a terminal point of the housing defining a fluid inlet pathway. 
     
     
         13 . The boundary layer turbomachine of  claim 1 , wherein the housing further comprises a distribution region between the inlet opening and the interior space to transition fluid flow from the inlet opening to the interior space, wherein the inlet opening optionally includes a modular inlet manifold having an expansion region which progressively transitions a circular inlet to a rectangular distribution region cross section. 
     
     
         14 . The boundary layer turbomachine of  claim 1 , wherein a radial distance between an outer diameter of the disks and an inner surface of the partition is equal to 3 to 10 times a boundary layer thickness of the fluid. 
     
     
         15 . The boundary layer turbomachine of  claim 1 , wherein at least one of the plurality of disks is constructed of a woven fiber resin composite material. 
     
     
         16 . A rotor assembly for a boundary layer turbomachine, comprising:
 a plurality of disks; and   a plurality of spacers disposed between adjacent disks to space the disks apart along an axis of rotation,   wherein the disks define an interior opening along the axis of rotation such that fluid passes through gaps between the disks and the interior opening as the fluid moves through the rotor assembly.   
     
     
         17 . The rotor assembly of  claim 16 , wherein the plurality of disks are oriented perpendicular to the axis of rotation. 
     
     
         18 . (canceled) 
     
     
         19 . (canceled) 
     
     
         20 . (canceled) 
     
     
         21 . The rotor assembly of  claim 16 , wherein the rotor assembly includes an extension member to couple the rotor assembly to a portion of the turbomachine and facilitate rotation of the rotor assembly about the axis of rotation. 
     
     
         22 . The rotor assembly of  claim 16 , wherein the disks are spaced apart by a distance equal to 3 to 10 times a boundary layer thickness of the fluid and the disks have a disk thickness from 2 to 5 times the boundary layer thickness. 
     
     
         23 . (canceled) 
     
     
         24 . A partition for a boundary layer turbomachine, comprising:
 a first partition member having a first surface; and   a second partition member having a second surface spaced apart from the first surface to form a partition opening that includes an inlet and an outlet, the second surface having an inlet surface to form a portion of the partition opening inlet, and an outlet surface to form a portion of the partition opening outlet,   wherein the inlet surface has a radius within 5% of 1.5 times a radial thickness of the second partition member.   
     
     
         25 . The partition of  claim 24 , wherein the radius of the inlet surface is within 1% of 1.5 times the radial thickness of the second partition member. 
     
     
         26 . The partition of  claim 24 , wherein the outlet surface has a radius within 20% of one-third of the inlet surface radius. 
     
     
         27 . (canceled) 
     
     
         28 . The partition of  claim 24 , wherein the first surface comprises a planar portion. 
     
     
         29 . The partition of  claim 24 , wherein the partition openings have an injection angle of 25 to 55 degrees or 35 to 65 degrees.