WO2009088955A2 - Turbine à effet de couche limite - Google Patents

Turbine à effet de couche limite Download PDF

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Publication number
WO2009088955A2
WO2009088955A2 PCT/US2008/088687 US2008088687W WO2009088955A2 WO 2009088955 A2 WO2009088955 A2 WO 2009088955A2 US 2008088687 W US2008088687 W US 2008088687W WO 2009088955 A2 WO2009088955 A2 WO 2009088955A2
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WO
WIPO (PCT)
Prior art keywords
disks
fluid
annular
boundary layer
annular disks
Prior art date
Application number
PCT/US2008/088687
Other languages
English (en)
Other versions
WO2009088955A3 (fr
Inventor
Aaron Sandoval
Johann Wingard
Original Assignee
Energenox, Inc.
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Energenox, Inc. filed Critical Energenox, Inc.
Priority to US12/811,368 priority Critical patent/US20110097189A1/en
Publication of WO2009088955A2 publication Critical patent/WO2009088955A2/fr
Publication of WO2009088955A3 publication Critical patent/WO2009088955A3/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/34—Non-positive-displacement machines or engines, e.g. steam turbines characterised by non-bladed rotor, e.g. with drilled holes
    • F01D1/36—Non-positive-displacement machines or engines, e.g. steam turbines characterised by non-bladed rotor, e.g. with drilled holes using fluid friction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/005—Adaptations for refrigeration plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/026—Scrolls for radial machines or engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/045—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor-module
    • F02C3/05—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor-module the compressor and the turbine being of the radial flow type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/08—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
    • F02C3/09—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage of the centripetal type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/80—Size or power range of the machines
    • F05D2250/82—Micromachines

Definitions

  • the present disclosure relates to a boundary layer effect gas microturbine for the purpose of producing a torque for mechanical work or to generate electric power.
  • Reciprocating internal combustion engines have long been used to replace man power with that of the machine.
  • a linear motion is imparted to one or more reciprocating pistons by compression and ignition of a mixture of fuel and air.
  • the linear motion of the one or more pistons is converted to rotational motion by connection of a connecting rod to a crankshaft.
  • the rotation motion is then used, for example, for mechanical work or generation of electric power.
  • rotary engine An alternative to the reciprocating internal combustion engine is the rotary engine.
  • the bladed turbine engine has been utilized in several industries, including for propulsion of aircraft and watercraft and for power generation.
  • rotary engines replace the piston, connecting rod, and crankshaft with a rotor assembly, a rotating unit.
  • Rotary engines operate differently than the internal combustion engine, but also result in rotational motion that is used, for example, for mechanical work or generation of electric power.
  • 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.
  • the boundary layer effect turbine directs the operating fluid in a radially-converging spiral, or vortical, path through narrow spaces between the plurality of disks and drives the shaft for the generation of electric power or for mechanical work.
  • the boundary layer effect turbine of this disclosure provides embodiments that enhance the operation of the microturbine beyond the capabilities of the internal combustion engine or blade turbine.
  • a modified boundary layer turbine includes 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; and a plurality of annular disks within the housing, each of the disks being spaced apart from an adjacent disk by means, in some embodiments, of an airfoil shaped spacer, each spacer presenting a positive surface, which induces a near positive displacement of the fluid moving between the disks, each of the disks having an inner opening through which the central shaft extends and having an outer edge; wherein the outer edge of at least one of the of annular disks is tapered; 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 a surface of the at least one of
  • At least one of the annular disks further comprises a tapered inner edge.
  • the fluid inlet port is along the central axis, and in some embodiments with the fluid inlet port along the central axis, the fluid outlet port is adjacent an outer edge of at least one of the plurality of disks. In some embodiments, the fluid outlet port is along the central axis.
  • the modified boundary layer turbine further comprises a fluid heat exchanger in communication with the fluid outlet port and the fluid inlet port. In some embodiments, the modified boundary layer turbine further comprises a combustion chamber that directs fluid toward the fluid inlet port.
  • rotation of the plurality of annular disks is configured to transmit kinetic energy from the rotating disks to the fluid.
  • the plurality of annular disks are configured to rotate upon transmission of kinetic energy from the fluid.
  • the central shaft is supported by at least one magnetic bearing, and in some embodiments, the central shaft is supported by at least one air bearing.
  • 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; and a plurality of annular disks within the housing, each of the disks being spaced apart from an adjacent disk, each of the disks having an inner opening through which the central shaft extends and having an outer edge; wherein the inner edge of at least one of the of annular disks is tapered; 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 a surface of the at least one of the disks.
  • a modified boundary layer compressor includes 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; and a plurality of annular disks within the housing, each of the disks being spaced apart from an adjacent disk by means of an airfoil shaped spacer, each spacer presenting a positive surface, which induces a near positive displacement of the fluid moving between the disks, each of the disks having an inner opening through which the central shaft extends and having an outer edge; wherein the outer edge of at least one of the of annular disks is tapered; 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 a surface of at least one of the disks.
  • a modified boundary layer compressor comprising a housing having a fluid inlet port and a fluid outlet port; a central shaft, extending through the housing through the inlet and outlet ports, 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 a modified 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
  • At least one of the annular disks further comprises a tapered inner edge.
  • the fluid inlet port is along the central axis, and in some embodiments with the fluid inlet port along the central axis, the fluid outlet port is adjacent an outer edge of at least one of the plurality of disks.
  • a boundary layer compressor 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
  • a disk compressor assembly 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 blade member extending, in the cylindrical space, from the rotation axis toward inner edges of the annular disks, the blade member further extending helically about the rotation axis; wherein, during use, the plurality of annular disks rotates, and fluid is received into the cylindrical space, in a substantially axial direction, and the fluid flows between the annular disks, in a substantially radial direction, into the annular spaces.
  • a disk compressor assembly 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 blade member extending, in the cylindrical space, from the rotation axis toward inner edges of the annular disks, the blade member further extending helically about the rotation axis; wherein, during use, the plurality of annular disks rotates, and fluid is received into the cylindrical space, in a substantially axial direction, and the fluid flows between the annular disks, in a substantially radial direction, into the annular spaces.
  • a disk compressor assembly comprises a plurality of substantially parallel annular disks, axially spaced along a rotation axis, the annular disks having an outer edge and defining a cylindrical space extending through a center portion of the annular disks that is 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 blade member extending, in the cylindrical space, from the rotation axis toward inner edges of the annular disks, the blade member further extending helically about the rotation axis; a fluid inlet located adjacent the outer edge of at least one of the plurality of annular disks and a fluid outlet located adjacent the cylindrical space; wherein, during use, fluid travels along a vortical flow path within at least one of the plurality of annular spaces from the fluid inlet to the cylindrical space, and then along a helical, axial flow path through the cylindrical space toward the fluid outlet.
  • Described herein are embodiments of a gas compressor based on the use of a driven rotor consisting of a plurality of flat disks utilizing the boundary layer phenomenon, which relies on the cohesive and viscosity properties of a gaseous fluid, combined with aerofoil shaped spacers between said disks to give a near positive displacement effect at high rotating speeds is presented herein.
  • the disk compressor efficiently achieves high compression ratios.
  • the embodiments described herein include single, double, and multiple stage compression cycles. In the two stage versions, the gas flows radially outward accelerating the gas, converting velocity into pressure as the gas slows down in a circumferential diffuser.
  • the gas is subsequently returned in a radially inward cycle, forcing the gas into a reduced volume at high speed to increase the pressure, after which the gas is allowed to expand into the recuperator volume that acts as a pressure sink.
  • Multiple stages repeat the principles described above to obtain higher-pressure ratios.
  • the fluid inlet port is along the central axis, and in some embodiments, the fluid inlet port is adjacent to an outer edge of at least one of the plurality of disks.
  • rotation of the plurality of annular disks is configured to transmit kinetic energy from the rotating disks to the fluid.
  • the plurality of annular disks are configured to rotate upon transmission of kinetic energy from the fluid.
  • the central shaft is supported by at least one magnetic bearing, and in some embodiments, the central shaft is supported by at least one air bearing.
  • 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
  • the arcuate elevation comprises substantially an airfoil shape.
  • the arcuate elevation has a thickness equal to the space between adjacent disks, and in some embodiments, the arcuate elevation has a thickness greater than the boundary layer space between adjacent disks.
  • the arcuate elevations present a surface, which induces a near positive displacement of the fluid moving between the disks, enhancing the mechanical efficiency of the boundary layer effect.
  • at least one of the arcuate elevations comprises a thickness equal to about twice 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.
  • at least two of the disks are spaced about 0.6 mm apart, and in some embodiments, at least two of the disks are spaced about 1.2 mm apart.
  • At least one of the arcuate elevations are integrally formed with at least one of the plurality of annular disks. In some embodiments, at least one of the arcuate elevations comprises a different material than does the at least one of the disks.
  • the central shaft is supported by at least one magnetic bearing, and in some embodiments, the central shaft is supported by at least one air bearing.
  • 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
  • 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.
  • the inner edge of at least one of the plurality of the annular disks is tapered.
  • an outer edge of at least one of the plurality of the annular disks is tapered.
  • the inner edge of at least one of the plurality of the annular disks is tapered.
  • 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.
  • the boundary layer turbine further comprises 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.
  • the central shaft is supported, during rotation, by at least one magnetic bearing, and in some embodiments, the central shaft is supported, during rotation, by at least one air bearing.
  • a disk turbine assembly 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 blade member extending, in the cylindrical space, from the rotation axis toward inner edges of the annular disks, the blade member further extending helically about the rotation axis; wherein, during use, the plurality of annular disks rotates, and fluid is received into the cylindrical space, in a substantially axial direction, and the fluid flows between the annular disks, in a substantially radial direction, into the annular spaces.
  • the blade member width 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.
  • the inner edge of at least one of the plurality of the annular disks is tapered.
  • an outer edge of at least one of the plurality of the annular disks is tapered, and in some of these embodiments, the inner edge of the at least one of the plurality of the annular disks is tapered.
  • 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.
  • the disk turbine assembly 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.
  • 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.
  • the blade member has a 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.
  • the inner edge of at least one of the plurality of the annular disks is tapered.
  • an outer edge of at least one of the plurality of the annular disks is tapered, and in some of these embodiments, the inner edge of the at least one of the plurality of the annular disks is tapered.
  • 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.
  • the disk turbine assembly further comprises 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.
  • a disk turbine assembly comprises a plurality of substantially parallel annular disks, axially spaced along a rotation axis, the annular disks having an outer edge and defining a cylindrical space extending through a center portion of the annular disks that is 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 blade member extending, in the cylindrical space, from the rotation axis toward inner edges of the annular disks, the blade member further extending helically about the rotation axis; a fluid inlet located adjacent the outer edge of at least one of the plurality of annular disks and a fluid outlet located adjacent the cylindrical space; wherein, during use, fluid travels along a vortical flow path within at least one of the plurality of annular spaces from the fluid inlet to the cylindrical space, and then along a helical, axial flow path through the cylindrical space toward the fluid outlet.
  • the inner edge of at least one of the annular disks is tapered, and in some embodiments, the outer edge of at least one of the annular disks is tapered.
  • 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.
  • 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.
  • the disk turbine assembly further comprises 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.
  • Some embodiments decribed herein provide a high speed permanent magnet starter generator which is mounted on the same shaft as other rotating assemblies. Some embodiments provide for the starter generator to be water cooled by water having a temperature lower than the ambient temperature in order to reduce the compressor inlet air temperature and enhancing compressor efficiency. In some embodiments, the casing of the starter generator may be provided with extended surfaces or fins to facilitate heat exchanging.
  • a high speed hydrodynamic speed reducer that comprises a housing defining an internal chamber with a central axis; a cylindrical drive element within the internal chamber, the drive element being aligned along the central axis and having a helical recess along an outer surface of the drive element that defines a fluid drive flow path, the drive element being configured to couple with a rotatable speed reducer input; a driven element within the internal chamber, the driven element being aligned along the central axis and having a cylindrical bore with an internal surface having a helical recess that defines a fluid driven flow path, the driven element being configured to couple with a rotatable speed reducer output; a tubular divider element within the internal chamber and aligned along the central axis, the divider element having a first end and a second end and being positioned between the outer surface of the cylindrical drive element and the internal surface of the driven element; and operating fluid within the internal chamber, the fluid drive flow path, and the fluid driven flow path;
  • Some embodiments include a combustor, for a boundary layer turbine, that includes a primary venturi burner, at least one secondary venturi burner, and a controller that directs flow of fluid through the primary venturi burner, the at least one secondary venturi burner, and through a passage that is not through a burner.
  • the rotatable speed reducer input is supported by an air bearing, and some embodiments provide that the rotatable speed reducer input is supported by a magnetic bearing.
  • the cylindrical drive element comprises a plurality of helical recesses along the outer surface that defines a plurality of fluid drive flow paths.
  • the cylindrical bore of the driven element comprises a plurality of helical recesses along the internal surface that defines a plurality of fluid driven flow paths.
  • the helical recess along the outer surface of the drive element and the helical recess along the internal surface of the driven element are arranged such that rotation of the cylindrical drive element in a first rotational direction results in rotation of the driven element in a second rotation direction that is opposite the first rotation direction.
  • the operating fluid comprises a synthetic oil with spherical inorganic nanoparticle properties that cause the oil to stay cool without loosing its lubricity.
  • the drive element is configured to couple with the rotatable speed reducer input by a magnetic drive. In some embodiments, the rotatable speed reducer input rotates the drive element through a magnetic drive.
  • Figure IA is a schematic front view of embodiments of a disk used in connection with a boundary layer effect turbine.
  • Figure IB is a schematic side view of embodiments of a series of disks, such as those illustrated in Figure IA, assembled along a turbine shaft.
  • Figure 2 is a schematic side view of embodiments of airflow across a turbine disk surface, comparing the profile of laminar flow to that of turbulent flow.
  • Figure 3 is a diagram schematically showing embodiments of flow of fluid through embodiments of a boundary layer effect turbine.
  • Figure 4 depicts side, front, and rear views of embodiments of a boundary layer effect turbine.
  • Figure 5A is a partial cross-sectional view of an embodiments of a boundary layer effect turbine.
  • Figure 5B is another partial cross-sectional view of an embodiments of a boundary layer effect turbine, showing, among other things, schematic views of components of the turbine.
  • Figure 6A illustrates a partial view of embodiments of the boundary layer effect turbine of Figure 4, showing, among other things, the arrangement of the water cooled starter generator with magnetic bearings on either side of it placed in the air flow path into the compressor.
  • Figure 6B illustrates a partial view of embodiments of a boundary layer effect turbine, illustrating the direction of fluid flow through the turbine with arrows.
  • Figure 7 illustrates a schematic side view of embodiments of a compressor in connection with a boundary layer effect turbine.
  • Figure 8A illustrates a schematic front view of a portion of the compressor of Figure 7.
  • Figure 8B illustrates embodiments of a disk used in impeller embodiments described herein.
  • Figure 8C illustrates embodiments of a compressor using two sets of disks.
  • Figure 8D illustrates embodiments of a disk used in impeller embodiments described herein.
  • Figure 8E illustrates a rear view of embodiments of a compressor.
  • Figure 8F illustrates schematic embodiments of a compressor using a plurality of compressor impellors.
  • Figure 8G illustrates a schematic view of an embodiment of a three-stage compressor that can be used in connection with a boundary layer effect turbine.
  • Figure 8H illustrates a schematic view of an embodiment of a compressor that can be used in connection with a boundary layer effect turbine.
  • Figure 81 illustrates an image with schematic markings that depict the flow of fluid through a boundary layer effect.
  • Figure 8J illustrates a front view of embodiments of a first stage of a compressor in use with a boundary layer effect turbine.
  • Figure 8K illustrates embodiments of a second stage of a compressor in used with a boundary layer effect turbine.
  • Figure 9A illustrates a schematic cross-sectional view of embodiments of a pair of disks of a boundary layer effect turbine.
  • Figure 9B illustrates a schematic cross-sectional view of embodiments of a pair of disks of a boundary layer effect turbine.
  • Figure 9C illustrates a schematic cross-sectional view of embodiments of a pair of disks of a boundary layer effect turbine.
  • Figure 10 illustrates a cross-sectional view of embodiments of a boundary layer effect turbine, including a compressor, a recuperator, and turbine expander.
  • Figure 11 illustrates a partial cross-sectional side view of embodiments of a recuperator used with a boundary layer effect turbine.
  • Figure 12A illustrates a front view of embodiments of a recuperator used with a boundary layer effect turbine.
  • Figure 12B illustrates a schematic partial cross-sectional side view of embodiments of a recuperator used with a boundary layer effect turbine.
  • Figure 12C illustrates a rear view of embodiments of a recuperator used with a boundary layer effect turbine.
  • Figure 12D illustrates embodiments of a recuperator used with a boundary layer effect turbine.
  • Figure 12E illustrates embodiments of a recuperator used with a boundary layer effect turbine.
  • Figure 12F illustrates embodiments of a recuperator used with a boundary layer effect turbine.
  • Figure 12G illustrates embodiments of a recuperator used with a boundary layer effect turbine.
  • Figure 13A illustrates a schematic front view of embodiments of a turbine expander with dashed arrows representing a flow path of air through a turbine expander scroll and across a face of the disk.
  • Figure 13B illustrates a perspective view of embodiments of a turbine expander casing.
  • Figure 14 illustrates a schematic front view of embodiments of a turbine expander with arrows representing a flow path of air through a turbine expander scroll and through disks of the expander.
  • Figure 15A is a perspective view of embodiments of a back plate having center impeller vanes.
  • Figure 15B is a perspective view of embodiments of a disk of a boundary layer effect turbine.
  • Figure 16A is a perspective view of a back plate with a plurality of disks assembled thereon.
  • Figure 16B is an exploded view of the back plate and disks of Figure
  • Figure 17 A is a schematic representation of spacing between disks of the boundary layer effect turbine.
  • Figure 17B is a schematic representation of spacing between disks of the boundary layer effect turbine.
  • Figure 18 is a schematic representation of a boundary layer effect turbine and peripheral components mounted inside its weatherproof cabinet.
  • Figure 19A is a front schematic view of embodiments of a boundary layer effect turbine.
  • Figure 19B is a rear schematic view of embodiments of a boundary layer effect turbine.
  • Figure 2OA is a longitudinal sectional view of embodiments of a combustor with venturi secondary burners as well as a primary burner.
  • Figure 2OB is a partial cross sectional view of the combustor showing a plurality of venturi burners, a primary burner in the center, and an adjustable air bypass control ring around the assembly.
  • Figure 2OC is a sectional view showing a spark igniter and an axially supplied primary fuel supply and the radially supplied secondary fuel supply to the venturi burners.
  • Figure 21 is a perspective view of embodiments of a high speed reducer that is operable with a boundary layer effect turbine.
  • Figure 22 is an exploded view of embodiments of the high speed reducer of Figure 21.
  • Figure 23A depicts embodiments of a high speed reducer.
  • Figure 23B depicts embodiments of a high speed reducer.
  • Figure 24 depicts embodiments of a general assembly of a disk turbine fitted with a hydrodynamic speed reducer.
  • Figure 25 depicts an exemplary heating and air conditioning unit that can be configured to operate in connection with a boundary layer effect turbine.
  • the boundary layer effect turbine described herein has several advantages over the internal combustion engine and the blade turbine.
  • the internal combustion engine is a complex system that has several moving parts that are arranged about a rotating crankshaft. While the internal combustion engine has been used for many purposes in many industries, the complex construction presents significant maintenance complications. Additionally, the reciprocating motion between various components of the internal combustion engine (e.g., the piston within the cylinder) results in the generation of heat caused by the friction between parts. The heat results in losses that decrease the efficiency of the internal combustion engine.
  • the blade turbine is also plagued with complications arising from its principle of operation. Cavitation occurs as the operating fluid engages the blades moving at extremely high speeds. This damages the blades and presents different, but significant, maintenance complications, such as requiring replacement or resurfacing of the turbine blades. Additionally, the blades rotate at near sonic speeds and create turbulent air flow through the turbine, resulting in inherently noisy operation. The distances between turbine blades also result in a large percentage of the fluid not making contact with the blades to impart its kinetic energy to the blades, resulting in a significant loss in efficiency.
  • the boundary layer effect turbine provides a single rotation assembly that operates to compress the operating fluid prior to combustion and utilizes the inherent adhesion and viscosity qualities of the fluid to drive the turbine.
  • the total fluid flow is divided into extremely narrow segments, each segment being twice the size of the boundary layer at the disk surface, so as to maximize the transfer of kinetic energy at molecular level to the surface of the disk. Described herein are embodiments of the boundary layer effect turbine that builds upon these advantages and further enhances the operational efficiency of the boundary layer effect turbine.
  • the boundary layer effect turbine operates on properties of the operating fluid. All fluids, including a gaseous fluid, possess the two properties of viscosity and adhesion, which causes the molecules of the fluid to "stick" to the surface of the disks in a boundary layer interfacing with the body surface. At that interface, the fluid flow approaches zero relative speed to the surface, and the boundary layer is a transitional area extending from the body surface into the fluid. At the body surface the flow of the fluid with respect to the body surface approaches zero velocity, and the flow of fluid at a periphery of the boundary layer is where the flow of fluid is about 99% of the rate of the free-flowing fluid.
  • shear stresses of the fluid caused by the viscosity of the operating fluid create a drag on the body surface as the fluid on one side is pulled in one direction by the free-flowing fluid and on the other side by adherence to the body surface. These shear stresses transfer kinetic energy of the flowing fluid to the body surface as a function of the fluid's viscosity.
  • boundary layer is a broad term and is used with its ordinary meaning, which includes, without limitation, a transitional layer of fluid created when a fluid passes over a surface, the transitional layer having varying velocities ranging from a position adjacent or at the surface, where the velocity approaches zero with respect to the surface, to a position adjacent the free-flowing fluid, where the velocity of the fluid within the boundary layer approaches that of the free-flowing fluid.
  • the boundary layer extends from the surface to a distance away from the surface at which the fluid's velocity ranges from about 93% to about 99% of the velocity of the free-flowing fluid.
  • the boundary layer extends from the surface, or a point adjacent the surface, to a distance away from the surface at which the fluid's velocity is less than about 93% or greater than about 99% of the velocity of the free-flowing fluid.
  • the term free-flowing fluid is used is a broad term and is used with its ordinary meaning, which includes, without limitation, the fluid that is flowing with no or substantially no impedance caused by adjacent surfaces or structures.
  • the free-flowing fluid is that fluid that is not impeded by the stresses created by a boundary layer when fluid passes over a surface.
  • the boundary layer effect turbine utilizes the phenomena of the boundary layer to drive a rotor. As fluid is injected at high speeds directly over surfaces of a plurality of disks of the boundary layer effect turbine, energy is transferred from the fluid to the disks.
  • the boundary layer effect turbine creates a vortex flow in a turbine expansion chamber by directing high velocity gas in a radially-converging spiral path through narrow spaces between a plurality of disks axially spaced along a rotating shaft.
  • the fluid flow is introduced into the turbine expansion chamber near a periphery of the disks and is directed, in some embodiments, slightly incident to the plurality of disks.
  • the fluid passes over one or more surfaces of the disk in vortical flow and is expelled through an aperture or apertures located near or at the center of the disks.
  • Figures IA and IB illustrate embodiments of a boundary layer effect turbine disk assembly 100.
  • Figure IA illustrates a front view of a boundary layer effect turbine disk 102 having a plurality of exhaust apertures 105 positioned around a shaft 110 that extends through the center of the disk 102.
  • a face of the disk 102 is substantially smooth and provides the body surface over which the operating fluid flows and upon which the boundary layer is created to transfer kinetic energy between the disk and the operating fluid.
  • the disk edge 120 defines the outer periphery of the disk 102, and disk edges 120 of several disks 102 axially aligned along the shaft 110, as depicted in Figure IB, define the outer periphery of the disk assembly.
  • the shaft 110 defines an axis 125 that extends through the center of each of the disks 102, and the disks 102 are manufactured to be in rotational balance along the shaft 110 such that the disks 102 will be able to withstand the centripetal forces during rotation of the disks 102 at high speeds.
  • the disks 102 are configured to rotate at speeds of from about 20,000 rpm to about 100,000 rpm.
  • the disks 102 are configured to rotate at speeds of less than about 20,000 rpm or greater than about 100,000 rpm.
  • the speed of rotation is determined, at least in part, by the velocity of the fluid entering the peripheral spaces between the disks.
  • the velocity of the fluid entering the peripheral spaces is determined, at least in part, by the amount of fluid injected into the disk chamber during operation, the spacing of the disks 102, and the flow of fluid through the exhaust apertures 105.
  • the gas velocity is preferably kept below sonic speed of about 340 meters per second. Larger disk diameters will consequently rotate at slower speeds of rotation. Balancing of the disks 102 is advantageous for operation at high speeds and increases the longevity and performance of the turbine.
  • Boundary layer theory dictates that the viscosity and adhesion properties of the operating fluid cause the fluid molecules to adhere to the smooth disk surfaces in the boundary layer at the body surface.
  • the disks are spaced to reduce or limit the amount of fluid escaping between adjacent boundary layers.
  • the volume of fluid passing between the disks consists substantially of only the sum of the volume of fluid in the adjacent laminar flow boundary layers. For this reason, it is desirable in some embodiments for the fluid to flow in a laminar path upon entering the space between the disks, and embodiments provided herein are directed to facilitate the creation of laminar flow boundary layers that improve or maximize the operational efficiency of the boundary layer turbine.
  • the disks are spaced along the shaft at a distance equal to about twice the width of the boundary layer.
  • the boundary layer of each disk does not substantially interfere with the boundary layer of adjacent disks, and the distance between the boundary layers limits the flow of turbulent or free-flowing fluid between the disks. This facilitates in maximizing, increasing, or improving the transfer of kinetic energy between the disks and the operating fluid.
  • This boundary layer effect turbine has an extremely favorable horsepower-to-weight ratio when compared to any other internal combustion or turbine engines of comparable output. It also provides a high speed electric generator that can be configured to be coupled directly to a common shaft with the turbine, thus obviating expensive gear boxes. This disclosure further provides a boundary layer effect turbine that lends itself to scale-ups that may range from about 50 kWe to more than about 2000 kWe power outputs. In some embodiments, the boundary layer effect turbine disclosed herein can also generate energies below about 50 kWe or greater than about 2000 kWe.
  • FIG. 3 a block diagram is illustrated that depicts embodiments of boundary layer effect turbines 200 described herein.
  • the arrows of Figure 3 depict the flow of the operating fluid as it passes through the boundary layer effect turbine 200.
  • Illustrated in Figure 3 is a starter or generator 205 that is coupled to a compressor 210.
  • the coupling between the starter or generator 205 and the compressor 210 can be through the shaft 110 of the turbine, and the coupling can include a magnetic coupling. This coupling can reduce inefficiencies in the turbine 200 that may be caused by some mechanical couplings.
  • the compressor 210 can include a cold fog injection 215 for treating operating fluid introduced from an inlet prior to compression by the compressor 210.
  • Some embodiments employ a cold water cooling system to cool the starter generator 205 and to reduce the air inlet temperature into the compressor 210 for greater efficiency.
  • the compressor 210 can include a reverse-boundary layer effect turbine disk assembly, as described below, which includes a plurality of disks 102 that operate in reverse fashion to that of the boundary layer effect turbine impellers.
  • the compressor 210 can compress the operating fluid in a plurality serial of stages.
  • the compressor 210 is preferably operated by rotation of the shaft 110, which passes through the compressor 210.
  • the reverse-boundary layer effect turbine compressor 210 can be driven by rotation of the shaft 110.
  • a recuperator 220 is provided in line with the compressor 210 to utilize exhaust heat from spent operating fluid, or exhaust, by preheating the operating fluid before the operating fluid passes through a combustor 225 or solid oxide fuel cell.
  • the recuperator 220 can provide a crossing flow path of incoming fluid, or fluid coming from the compressor 210, and outgoing fluid, or spent fluid to transfer energy from the spent fluid to the incoming fluid.
  • the recuperator 220 can provide a double cross flow path, in which the incoming fluid crosses paths, through different channels or pathways, with the outgoing fluid twice while flowing through the recuperator 220. This double counter (cross) flow path can enhance the transfer of energy between the outgoing fluid and the incoming fluid, and can increase the operation efficiency of the turbine 200 by preheating the incoming fluid prior to the combustion stage.
  • the fluid is introduced into the combustor 225, or solid oxide fuel cell, to provide heat to the operating fluid.
  • the combustor 225 includes a plurality of venturi burners with an adjustable air bypass control ring.
  • the combustor 225 preferably operates to mix fuel, or some combustible content, with the operating fluid, and to ignite the fuel to input energy into the operating fluid.
  • the hot operating fluid is directed through a nozzle directed into a turbine expander 230.
  • the pressurized and heated operating fluid is introduced into the turbine expander 230 along a perimeter of a disk assembly 100 that includes a plurality of boundary layer effect turbine disks 102.
  • the fluid is directed substantially tangentially in the turbine expander 230 in a vortical flow path from an outer periphery of the disks 102, between the space between the disks 102, and through an exhaust port 105 toward the center of the disks 102.
  • the fluid drives the disk assembly 100 and transfers kinetic energy to the disk assembly 100, generating a torque, or moment, about the central axis 125 of the shaft 110 extending through the turbine expander 230.
  • the torque causes the disk assembly 100 and shaft 110, which is coupled with the disk assembly 100, to rotate.
  • the operating fluid is directed from the exhaust port 105 in the turbine expander 230 back into the recuperator 220.
  • the recuperator 220 directs the flow of the exhaust fluid to cross paths with incoming fluid that has been compressed by the compressor 210.
  • the recuperator 220 preferably separates the flow of the exhaust flow and the incoming fluid by a plurality of thin walls that are configured to conduct heat from fluid on one side to fluid on the opposite side of the wall.
  • the recuperator 220 can provide a double cross-flow path that enhances the heat transfer from the exhaust fluid to the incoming fluid.
  • the exhaust fluid After passing through the recuperator 220, the exhaust fluid is discharged from the turbine 200.
  • the exhaust fluid can then be used from other applications.
  • the exhaust fluid can then be used for space heating, process heating, or steam generation for further power generation and/or heating ventilation and air conditioning (HVAC).
  • HVAC heating ventilation and air conditioning
  • Figure 4 illustrates side, front, and rear views of embodiments of an assembled boundary layer effect turbine 200 having seven sections: an inlet section 250, a compression section 260, a recuperator section 270, a combustion section 280, a turbine expansion section 290, an exhaust section 295, and a speed reducer section 298.
  • FIG. 5A is a partial cross-sectional view of the boundary layer effect turbine 200, showing embodiments of the seven sections.
  • a shaft 110 extending through the boundary layer effect turbine 200 defines an axis 125 of the turbine 200.
  • One end of the shaft 110 is positioned in the inlet section 250.
  • the shaft 110 is supported by one or more bearings 300, which are magnetic bearings in the illustrated embodiments, and is coupled to a starter motor or generator 205.
  • the central shaft 110 can be supported by at least one magnetic bearing 300, and in some embodiments, the central shaft 110 is supported by at least one air bearing 300. In some embodiments, the shaft 110 may be supported by roller bearings 300.
  • the turbine 200 can be fitted with airfoil or magnetic bearings 300 to facilitate operation and improve efficiency. Although embodiments of boundary layer effect turbines 200 can operate with mechanical roller bearings 300, operation with mechanical roller bearings 300 can increase maintenance and decrease both longevity of the turbine and efficiency, while limiting the rotating speed of the shaft to the capacity of the bearing 300.
  • Magnetic bearings 300 used in embodiments of boundary layer effect turbines 200 can be operated by permanent or electric magnets. In some embodiments, the electric magnets are powered by the turbine 200 during operation. Additionally or alternatively, the turbine 200 can include at least one air foil bearing 300. Air foil bearings 300 operate with the pressurized fluid flowing through the turbine 200 and can increase efficiency and operational longevity of the turbine, without limiting the rotating speed of the turbine 200. With magnetic and air bearings 300, the turbine 200 can be constructed with substantially only one moving part, the shaft 110, extending through the magnetic bearing 300 and the air foil bearing 300. This construction can decrease maintenance requirements and improve operational efficiency.
  • the shaft 110 extends through the compressor section 260, where two compressor assemblies 305, or compressor impellers, are depicted in Figure 5A and are coupled to and driven by rotation of the shaft 110.
  • the compressor 210 can have one compressor assembly 305, or compressor impeller, or more than two compressor assemblies 305, or compressor impellers.
  • the shaft 110 further extends through the recuperator section 270, which includes an air foil bearing 300 about the shaft 110.
  • the shaft 110 extends into the turbine expander 230, where it is coupled to one or more turbine expander assemblies 310, or turbine impellers.
  • FIG. 5B illustrates a partial cross-sectional view of embodiments of the boundary layer effect turbine 200.
  • the shaft 110 extends from the speed reducer 298, through the starter 205, and into the compressor section 260.
  • the recuperator section 270 and the turbine expander 230 can be modified from that depicted in Figure 5 A.
  • the recuperator section 270 is shown as having a plurality of pathways leading to multiple combustors 280.
  • the recuperator section 270 in some embodiments, can have a plurality of exhaust outlets 295. Four combustors and/or four outlets are more efficient than one large burner, as it allows for a more even tangential entry of the operating fluid into the turbine expander 230.
  • Figure 6A is a partial side view of the boundary layer effect turbine 200 further isolating components of sections separated from the respective section housing.
  • the shaft 110 that extends from the inlet section 250, through the compressor section 260 and recuperator section 270, and into the turbine expander section 290.
  • the shaft 110 can be a unitary component that is integrally formed and extends through all sections of the turbine 200.
  • the shaft 110 can be manufactured in separate portions and can be interlinked or coupled during assembly of the turbine 200.
  • the coupling of the shaft 110 can be an interlocking configuration of mating ends of the shaft 110, and in some embodiments, the shaft 110 can be coupled by magnetic couplings.
  • Figure 6B depicts some embodiments of the turbine 200 with embodiments of fluid paths through the turbine 200.
  • the fluid enters into the compressor section 260 from the left.
  • the compressor assembly 305 or rotating disks in a rotor- stator cavity, creates a radial outflow of fluid within the boundary layer along the disks 102.
  • the compressor section 260 can have repeated portions that compress the fluid before introducing the fluid into the recuperator section 270 to receive heating from the exhaust of the turbine expander section 290.
  • the compressor section 260 can include expanded portions that function as a diffuser to allow the fluid to decrease velocity and increase pressure.
  • the compressed fluid can be scavenged, or drawn, from the diffuser, or expanded portion, into a second stage, where the disk assemblies 305 are configured to have thicker protrusions, or spacers, between the disks 102.
  • these spacers, or blades are shaped to present a larger cavity at the center of the disk 102 that at the periphery, to reduce any pinching effect that could create a drop in pressure.
  • the larger cavities between the disks 102 of the assembly 305 can permit the fluid to move freely toward the center of the disk 102 to counteract the centrifugal force imposed by the rotating disk 102, which could contribute to a stalling condition.
  • the fluid is directed outward again in a similar manner as in the first stage.
  • the compressed fluid is then directed into a plurality of thin-walled tubes of the recuperator section 270 to receive heat from cross-flowing heated fluid.
  • the operating fluid is directed into at least one or more combustion sections 280, where the fluid is further heated by a combustor 225 before being introduced into the turbine expander section 290.
  • the fluid After the fluid is expanded in the turbine expander section 290, the fluid is directed through the recuperator section 270 to preheat incoming compressed fluid from the compressor section 260 through a double cross-flow path. After preheating the cooler compressed fluid, the exhaust fluid is then directed through exhaust ports 295.
  • Illustrated in Figure 7 are embodiments of a compressor 210 having two compressor impellers 305 in series.
  • the compressor 210 operates in reverse to the methods of the turbine impellers 310.
  • the compressor 210 includes a plurality of boundary layer effect turbine disks 102 that are driven to move the operating fluid.
  • Figure 7 illustrates the compressor 210 as having two compressor impellers 305, with the same diameters, in series to compress the fluid
  • the compressor 210 could be configured with a single compressor impeller 305.
  • the compressor can include more than two compressor impellers 305.
  • the compressor 210 can include compressor impellers 305 with varying size of disks 102.
  • the compressor impeller 305 can include disks 102 that have different diameters.
  • a compressor impeller 305 has a plurality of disks 102 that each have increasing diameters as the disks 102 are assembled along the shaft 110, such that the disks 102 of the impeller 305 have an increasing diameter along the fluid path from the inlet 350 of the compressor 210 toward the recuperator 220.
  • a compressor impeller 305 has a plurality of disks 102 that each have decreasing diameters as the disks 102 are assembled along the shaft 110, such that the disks 102 of the impeller 305 have a decreasing diameter along the fluid path from the inlet 350 of the compressor 210 toward the recuperator 220.
  • the diameter of the disks 102 within each compressor impeller 305 are the same, but the diameter of each compressor impeller 305 is different.
  • a first compressor impeller 305 can have a first diameter
  • a second compressor impeller 305 can have a second diameter.
  • the first diameter is greater than the second diameter
  • the second diameter is greater than the first diameter.
  • the decreasing volume directs the fluid from the compressor inlet 350 to spaces between the compressor disks 102.
  • the decreasing volume is, in part, created by a semi-frustoconical member 365 within the compressor impeller inlet 350.
  • the member 365 can include one or a plurality of vanes 366 ( Figure 8A) that direct fluid into the inlet 350 and through spaces between the compressor disks 102.
  • the member 365 enhances the equal distribution of fluid through the spaces between the disks 102.
  • Embodiments of the boundary layer compressors 210 described herein can be used in conjunction with the boundary layer turbine 200, or can be used for other purposes that are independent of the turbine 200.
  • the compressors 210 are suitable as small lightweight compressors and as very large industrial compressors for new applications, such as carbon dioxide compression for subsequent underground sequestering in aquifers.
  • These embodiments describe new high efficiency gas compressors that operate at high speed, in which improved compression performance and functional durability are attained by the use of boundary layer principles, which, as described elsewhere herein, utilize the adhesive and viscosity properties of gaseous fluids employed, combined with specially shaped spacers to provide efficient compression of said fluids.
  • Compressors so constructed are particularly useful for compression of air, carbon dioxide, refrigerants, steam, hydrocarbons, and other compressible fluids in either freestanding mode or as integrated elements of turbo-machinery.
  • Described herein are embodiments of simple, highly efficient and inexpensive gas compressors 210 for a wide variety of gas compression applications.
  • Gas compression uses considerable amounts of energy, and applications and embodiments of the compressors described herein can provide significant efficiency improvements over other designs.
  • the compressor section 260 can use more than about 50% of the gross power developed by the turbine.
  • the embodiments of compressors 210 described herein offer increased efficiency, reduced operating costs, reduced first cost for the equipment, reduced maintenance costs, and are able to operate at very high shaft 110 speeds so as to be able to operate off the same shaft 110 as a turbine 200 without the use of a gear box.
  • microturbines powered by microturbines
  • the application of microturbines for automotive and marine craft application can benefit from a compact compressor capable of operating at rotating speeds in the range of 20,000 to 150,000 rpm, which are the normal operating speeds of microturbines.
  • the important advantages of the gas compressors described herein can be employed for micro turbine applications as well as for major industrial scale applications, and the myriad of sizes between.
  • FIGS. 8A-8K Illustrated in Figures 8A-8K are embodiments of impellers 305, 310, e.g., for fluid compressors 210, such as gas compressors, based on the use of a driven impeller 305, 310 consisting of a plurality of flat disks 102, spaced apart by spacers 420 that can also act as flow resistance elements to guide the fluid, or gas, flow between disks 102 into a predetermined flow path to enhance energy transfer between the fluid and the disks 102.
  • the impeller 305, or rotor, of the boundary layer effect compressor 210 drives the disks 102, which moves the operating fluid in a radially vortical path through narrow spaces between the disks 102.
  • the fluid is driven by adhesion of the fluid to the surface, or face 115, of the disks 102, e.g., in the boundary layer, as well as being driven by the spacers 420, which function similar to vanes to positively displace the fluid.
  • Embodiments of the compressors described herein can move large quantities of fluids at relatively low pressure ratios and are, apart from air compression, also effective in compressing heavier gases such as carbon dioxide, ammonia or methane.
  • Figure 8 A depicts a front view of embodiments of the compressor impeller 305 with a bold arrow 405 depicting that rotation of the impeller 305 is in the clockwise direction and a smaller arrow 410 depicting the direction of air flow as a consequence of rotation of the compressor impeller 305.
  • the compressor impeller 305 includes a center vane section 415 oriented immediately around the shaft 110 as it extends through the impeller 305, as mentioned above with respect to Figure 7. Ambient air is drawn into the center vane section 415 and allowed to disperse in the voids between the axially spaced disks 102.
  • the spacers 420 of the compressor disks 102 include one or more, or at least one, elevated vane 420, as shown in Figure 8A, on the face 115 of the disk 102 to further capture and move the working fluid along the disk face 115.
  • the vanes 420 can, in some embodiments be formed in an aerofoil shape so as to limit disturbance of laminar flow of the working fluid along the face 115 of the disk 102.
  • the elevated vanes 420 drive the working fluid to the outer edge 120 of the compressor impeller 305, where the fluid is compressed and directed to the next section of the boundary layer effect turbine 200.
  • Aerofoil sections can be used in centrifugal rotors, such as in vane pumps and compressors, and the aerofoil sections can be integrally formed on the disk 102 or affixed to the disk 102 through two or more locating holes 425 to obviate welding spacers to the disks.
  • some embodiments of the present disclosure are configured to accommodate aerofoil sections that are welded, some embodiments are configured without welding, as welding can create stress raisers that can cause the disks to fail because of the forces involved when the impeller 305 spins at speeds from about 20,000 rpm to about 100,000 rpm. Utilization of only one fixing point without welding can cause the spacer 420 to swing open at high temperatures and under full load conditions should the disks 102 start to expand or distort.
  • washer shaped spacers can be used to separate the disks 102.
  • ambient air is drawn around the starter/generator into the inlet vanes 365 at the inlet port 350 of the compressor 210 and distributed evenly into the narrow spaces between the disks 102, causing air to move radially outwards in an outward spiral, to be discharged at the periphery into a diffuser 430 where the velocity is reduced causing the gas to present at higher pressures than ambient.
  • the air is then directed to the inlet of a second compressor and is compressed as discussed above. Upon discharge of the air into a second diffuser, the air is then directed to an inlet of a recuperator 220.
  • Figure 8B illustrates another embodiment of the compressor impeller 305 with a bold arrow 460 depicting rotation of the impeller 305 in the counter-clockwise direction.
  • the elevated vanes 420 extend from a point near or at the inner edge 465 of the disks 102 to a point near or at the outer edge 120 of the disks 102.
  • the compressor impeller 305 can have a first plurality of disks that operate to direct fluid from the inner edge 465 of the disks 102 to the outer edge 120 of the disks 102 and a second plurality of disks 102 that operate to direct fluid from the outer edge 120 of the disks to the inner edge 465 of the disks.
  • the first and second plurality of disks 102 can be separated by a central disk, which also operates to separate the fluid inlet from the fluid outlet.
  • the compressor impeller 305 can have a first plurality of disks 470 that operate to direct fluid from the inner edge 465 of the disks 102 to the outer edge 120 of the disks 102 and a second plurality of disks 480 that operate to direct fluid from the outer edge 120 of the disks 102 to the inner edge 465 of the disks 102.
  • the first and second plurality of disks 470, 480 can be separated by a central disk 490, which also operates to separate the fluid inlet 350 from a fluid outlet 352, as shown in Figure 8C.
  • Certain embodiments include a plurality of disk stacks 470, 480, one stack 470 forming a first phase 510 of the compressor 210, the second stack 480 comprising a second phase 520 of the compressor 210, both stacks 470, 480 being mounted on a common shaft 110 with a sturdy dividing disk, or central disk 290, between the stacks 470, 480 and onto which fixing pins 525, which hold the disks 102 together as a single composite stack, are affixed.
  • the disks 102 have elevated vanes 420, in of the first phase 510, that have widths that extend from an inner region adjacent the interior edge 465 of the disk 102, which is located near the rotation axis 530, about which the disks 102 rotate, to a region adjacent the outer edge 120 of the blade member 102.
  • the blade member, spacer blade, or elevated vane 420 is curved along its width so as to gently drive the fluid along a leading edge 461 from the inner region adjacent the interior edge 465 toward the outer edge 120 of the disk 102.
  • the curvature of the spacer blades 420 mounted between the disks 102 of the second phase 520 face in the opposite direction as the spacers 420 of the first phase 510, acting, when the shaft 110 is rotated, to drive the fluid towards the shaft 110 in a decreasing space to further increase its pressure.
  • the member 365, or central boss, which extends axially along the rotor or shaft 110 from the central dividing disk 490, is shaped to compensate for the reducing volume of gaseous fluid entering the central stacks of the first phase 510.
  • the central boss, or axially extending member 365 can be concave with an increasing radial dimension as the member 365 is closer to the central disk 490, and thus reduces the volume between the inner edge 465 of the disks as the fluid is drawn closer to the central dividing disk 490.
  • the central boss 365 of the central dividing disk 490 is also shaped in the second phase to compensate for the increasing volume of gaseous fluid, which fluid leaves the disks 102 via the cylindrical space around the shaft 110.
  • Figure 8C illustrates an embodiment of a compressor impeller 305 with a first plurality of disks 470 that move fluid from the fluid inlet 350, along the shaft or rotor 110 of the compressor 210, between the disks 102 to a diffuser 430.
  • a second plurality of disks 480 of the compressor impeller 305 operate to move the fluid from the diffuser 430 toward the center of the disks and toward a fluid outlet 352.
  • the impeller 305 may include a plurality of radially extending diffuser vanes 540 that extend from a position near or at the outer edge 120 of at least one of the disks 102 into the diffuser 430.
  • the diffuser vanes 540 are preferably configured to move fluid through the diffuser 430, from the first plurality of disks 470, to the second plurality of disks 480. In some embodiments, the diffuser vanes 540 are configured to direct the movement of air from the diffuser 430 toward the second plurality of disks 480. In some embodiments, the diffuser vanes 540 extends radially from the compressor impeller 305, and in some embodiments, the diffuser vanes 540 are coupled to the central disk 490.
  • the diffuser vanes 540 are configured to be stationary with respect to the rotating disks 102.
  • the diffuser vanes 540 can extend into the diffuser volume from the compressor housing 359 ( Figure 7), thus impeding the rotational spin of the fluid, and guiding the fluid to a second portion of the diffuser 430.
  • the velocity of the fluid is decreased, thus converting the kinetic energy of the fluid into pressure and allowing the air in the second portion of the diffuser to be directed into the second plurality of disks 480.
  • the second plurality of disks 480 may be slightly modified from that of the first plurality of disks 470 illustrated in Figure 8B.
  • the compressor impeller rotates in the counter-clockwise direction as indicated by a bold arrow 545.
  • the elevated vanes 420 can extend from a point near or at the inner edge 465 of the disks 102 to a point near or at the outer edge 120 of the disks 102.
  • a curvature of the elevated vanes 420 of the second plurality of disks 480 can be substantially opposite a curvature of the elevated vanes 420 of the first plurality of disks 470.
  • the curvature may vary between the first and second plurality of disks 470, 480.
  • a leading edge 461 of the elevated vanes 420 of the first plurality of disks 470 is depicted as having a convex curvature.
  • a leading edge 550 of the elevated vanes 420 of the second plurality of disks 480 is depicted as having a concave curvature. Alteration of the curvature between the first and second plurality of disks 470, 480 can serve to facilitate flow of the fluid through the compressor 210.
  • the concave curvature of the elevated vane's 420 leading edge 550 can function to draw fluid into the plurality of disks and direct the flow of fluid toward the center of the disks and toward the fluid outlet 352.
  • At least one of the arcuate elevations, spacers, or elevated vanes 420 comprises a different material than does at least one of the disks 102.
  • the selection of materials and the mechanical design of rotating components in the embodiments envisioned herein limit or reduce use of excessive quantities or weights of materials, but the design provides the strength where desired in the rotor, commensurate with the centrifugal forces acting on the rotating components.
  • Figure 8E depicts a rear view of some embodiments of the compressor impeller 305.
  • the diffuser vanes 540 are depicted as extending into the diffuser 430 from a location near or at the outer edge 120 of the first or second plurality of disks 470, 480, and the elevated vanes 420 on the face 115 of the disks 102 are illustrated as extending from the outer edge 120 of the disk 102 to the inner edge 465 of the disk 102.
  • more than one stage of the compressor can be employed, with the gaseous fluid flowing from one compressing stage to the next, undergoing multiple distinct treatments to increase pressure of the fluid.
  • the fluid, or gas will first be drawn axially into the inlet 350 at a center of the compressor 210 and directed radially outward by centrifugal force and rotation of the disks 102.
  • the speed, or velocity, of the fluid can approach near sonic speed upon being discharged from the outer edges 120 of the disks 102.
  • the fluid is then allowed to slow down in a circumferential diffuser 430 presenting an increased volume.
  • the diffuser 430 is shaped in such a way that the fluid is re-injected tangentially into the spaces between the disks 102, where it is driven radially inward mostly by the reaction force against the spacers 102, which act as vanes to direct the fluid toward the central outlet port 352.
  • the diffuser vanes 540 in the diffuser 430 change the direction of the moving fluid from one phase to the next and, in some embodiments, further slows down the moving fluid to allow the aerofoil spacers 420 to draw in the fluid, or gas, and to drive it inwards.
  • Centrifugal force counteracts the movement of the fluid inwards, thus increasing the pressure of the fluid, with centrifugal force acting radially outwards and with positive displacement force acts inwards. Simultaneously, the fluid passes through a decreasing volume, which further increases the pressure.
  • the spaces between the second plurality of disks 480, or second phase of disks 520 are larger than the spaces between the first plurality of disks 470, or first phase of disks 510, causing the gaseous fluid to travel more freely through the turbulent zone, somewhat away from the laminar flow zone (as shown in Figure 17B).
  • Third, fourth, and further additional stages can be added in series according to the desired pressure ratios.
  • Figure 8F depicts a plurality of compressor impellers arranged in series for providing sequential compression of the fluid. Not depicted in Figure 8F are the diffuser vanes 540, although some embodiments of compressors 210, having a plurality of compressor impellers 305, also include diffuser vanes 540. The arrows in Figure 8F depict the flow path of the fluid as it travels through multiple stages of the compressor 210.
  • Figures 8G and 8H depict embodiments of compressors 210 that are configured to direct the operating fluid to an outer periphery of the recuperator 220 instead of through a central portion, as depicted, for example, in Figure 8F.
  • the fluid follows a similar path through the compressor 210 as described with other embodiments, and is directed to the recuperator through an outlet 352 that can include, for example, a plurality of tubes circumferentially arranged around the recuperator 220 to direct flow of the compressed fluid.
  • the outlet 352 can include an annular passageway that is open to the diffuser 430, as illustrated in Figure 8H.
  • the shape of the elevated vanes 420 can be adjusted to align closely with the flow of fluid through the compressor 210 when the turbine 200 is operating under normal operating conditions. In some embodiments, adjustments to the vanes can be made to slightly impose a displacement force on the fluid flowing past the vanes 420.
  • Figure 81 Depicted in Figure 81 is one embodiment of a method of determining the alignment of the vanes 420.
  • Figure 81 shows the flow of fluid along a disk similar to that used in embodiments of the turbine 200.
  • a first radius B corresponds to an inner disk radius
  • a second radius A corresponds to an outer disk radius.
  • the white fluid lines illustrate the natural flow of fluid as it is acted upon by a face of the disk.
  • Solid line 531 corresponds to the natural flow of fluid
  • dashed line 533 corresponds to an exemplary alignment of the elevated vane 420 that will further act upon the fluid with a displacement force.
  • Some embodiments of a method of aligning the vanes 420 includes identifying an unimpeded flow of fluid over a disk 102 of the turbine 200 at normal operating conditions and identifying a desired alignment of an edge of a vane 420 that will impose a displacement force upon the fluid.
  • the method can further include adjusting the vane 420 to the desired alignment. In some embodiments, these methods are used to adjust the vanes 420 in at least one of the compressor 210 and the turbine expander 230.
  • Figures 8J and 8K depict various embodiments of elevated vanes 420 in connection with, for example, embodiments of the compressor 210.
  • Figure 8J depicts a front axial view of an embodiment of the compressor 210, showing a disk 102 and elevated vanes 420 arranged to move fluid to an outer periphery of the disk 102.
  • Figure 8K depicts a rear axial view of an embodiment of the compressor 210, showing how the rear elevated vanes 420 can be configured to increase the flow area along the disk from the outer periphery of the disk toward the inner portion of the disk 102.
  • a relative size of the outlet port 352 on the periphery can be about 300% larger than the inlet ports 350 at the center, to allow the fluid to increase its pressure by occupying a greater volume.
  • the outlet ports 352 in the center of the disks 102 are about 130% of the inlet ports 350 at the periphery.
  • Some embodiments include a gas bypass arrangement, which can permit part of the compressed gas output between phases or stages to be vented as desired, while maintaining high rotating velocity when utilizing the compressor drive apparatus and while maintaining minimal output loads.
  • Parameters that can determine the performance characteristics of a disk turbine design include a diameter of compressor and turbine disks 102, the rotor speed, the gaps between the disks 102, the number of disks 102, the shape of the elevated spacers 420, and the inlet nozzle (directing fluid into the turbine expander 230) design.
  • Embodiments described herein provide theoretical and empirical parameters that are configured to optimize operational performance of the boundary layer effect turbine.
  • the compressor 210 includes compressor disks 102 having a diameter of about 25 cm.
  • the compressor 210 can have disks 102 with diameters ranging from about 20 cm to about 30 cm.
  • Some embodiments include compressors 210 with disks 102 having diameters ranging from about 15 cm to about 35 cm, and some embodiments include compressors 210 with disks 102 having diameters less than about 15 cm or greater than about 35 cm.
  • a compressor impeller 305 can include about 24 disks 102. In some embodiments the compressor impeller 305 can have from about 18 disks 102 to about 30 disks 102, and in some embodiments, the compressor impeller 305 can have from about 12 disks 102 to about 36 disks 102. In some embodiments, the compressor impeller 305 can have less than about 12 disks 102 or greater than about 36 disks 102.
  • the number of compressor disks is dependent upon the number of turbine disks, or the number of compressor disks is determined by a ratio with respect to the turbine disks.
  • the ratio of compressor disks to turbine expander disks is about 2.5:1.
  • the ratio ranges from about 2.3 and about 2.7 compressor disks to each turbine expander disk, and in some embodiments, the ratio ranges from about 2.0 and about 3.0 compressor disks to each turbine expander disk.
  • the ratio is less than about 2.0 or greater than about 3.0 compressor disks to each turbine expander disk.
  • the ratio is about 3.5, about 4.0, about 5.0, about 7.5, and about 10.0 compressor disks to each turbine expander disk.
  • the rotational speed of the compressor 210 is the same as that of the shaft 110, as driven by the turbine expander disks 102. In some embodiments, the rotational speed of the compressor is about 20,000 rpm. In some embodiments, the rotational speed of the compressor ranges between about 15,000 rpm and about 25,000 rpm. In some embodiments, the rotational speed of the compressor ranges from about 10,000 rpm to about 30,000 rpm. In some embodiments, the rotational speed of the compressor is less than about 10,000 rpm or greater than about 30,000 rpm. For example, in some embodiments, the rotational speed of the compressor can be about 40,000 rpm, about 50,000 rpm, about 75,000 rpm, and about 100,000 rpm. In some embodiments, the rotational speed of the compressor can be variable depending on the desired output of the turbine 200.
  • the compressor disks 102 are spaced at a distance to enhance the efficiency of the compressor 210. In some embodiments, the compressor disks are spaced about 1.2 mm apart. In some embodiments, the compressor disks are spaced between about 1.1 mm and about 1.3 mm apart, and in some embodiments, the compressor disks are spaced between about 1.0 mm and about 1.4 mm apart. In some embodiments, the compressor disks are spaced less than about 1.0 mm or greater than about 1.4 mm apart. In some embodiments, the compressor disks are spaced a various distances apart depending on the desired flow characteristics through that portion of the compressor 210.
  • the inlet and exhaust ports 350, 352 or apertures 105 are configured to be a substantially annular shape concentrically oriented about the shaft 110, as illustrated in Figures 8A-8H. Alteration of the inlet and exhaust apertures to an annular passageway, which forms an annular channel when a plurality of disks are assembled, reduces flow restrictions of the fluid during operation and increases efficiency of flow through the compressor and expander.
  • the disks 102 are affixed around a set of vanes 366, with the vanes 366 offering an unobstructed inlet or outlet port of the impeller 305, making possible a streamlined and continuous spiral flow of the fluid.
  • the disks 102 used in the impellers 305 have a cross-sectional profile with flat and abrupt outer edges, as depicted in Figure 9A. While the boundary layer effect turbine 200 is operational with such disks 102, these disks 102 can increase the creation of turbulent flow through the impellers, creating eddies and decreasing operation efficiency of the turbine.
  • the outer edge 120 of the disks 120 can have a streamlined cross-sectional profile that enhances the flow of laminar flow over the surface of the disk.
  • the disks 102 can have tapered edges that resemble the front of an airfoil. This shape enhances the flow of laminar flow between the disks 102 as the fluid is guided through the impellers 305.
  • the disk 102 has an edge portion in which, moving inward from an edge 120 of the disk 102, a cross-sectional thickness of the disk increases at a decreasing rate along an edge portion length.
  • the disks can have a streamlined interior portion along the inner edge 465 where the exhaust aperture is located in addition to the streamlined portion along the outer edge 120 of the disk 102.
  • the streamlined edges of the disks 102 allow the fluid to flow more freely between the narrow spaces between the disks 102 in a laminar flow pattern, thus imparting the molecular energy of the fluid to the disk surface and reducing slippage between the fluid and the disk surface as a consequence of turbulent flow.
  • the boundary layer effect turbine 200 described in this disclosure enables the fast-moving fluid to transfer more gently into and out of the impellers 305, thus avoiding turbulent flow and yielding higher efficiencies.
  • Figure 10 shows embodiments of the assembly of a boundary layer effect turbine 200 for generating power with arrows depicting the path of the operating fluid through portions of the stages shown. Illustrated are three stages, namely the compressor 210, recuperator 220, and the turbine expander 230.
  • the operating fluid is compressed in the compressor 210, preheated in the recuperator 220, introduced into the combustion chamber 230, and mixed with the hot gases from the burners.
  • the hot and pressurized gas is then introduced into the turbine expander.
  • FIG. 11 illustrates embodiments of the recuperator 220.
  • fluid enters the recuperator 220 from the turbine expander 230 it flows around a concentric passage 620 around a bearing capsule 630.
  • the fluid enters a plenum chamber 640 from whence it is distributed into a plurality of small diameter, thin- walled, creep-resistant stainless steel tubes 650, such as of grade 321.
  • the voids between the stainless steel tubes 650 are preferably filled with long fiber stainless steel wool 660, that presents a low-pressure drop to the compressed air passing through it, while increasing the effective surface area.
  • this stainless steel finned plates are provided to transfer energy.
  • Compressed air enters a first concentric passage 660, from the compressor 210, and flows around the bearing capsule 630, flowing towards the hot side in a counter flow mode. This flow keeps the bearing capsule 630 cool, and the compressed fluid starts to accept heat from the hot outer passage 620 before the fluid is distributed to the voids between the tubes 650 by means of a multitude of inlet ducts 665.
  • the compressed air is allowed to travel, in a second cross-flow path, at a reduced speed through the stainless steel wool 660, or other transfer medium, around the tubes 650, allowing for ample time to absorb the heat from the thin walled tubes 650. It is conservatively estimated that the recuperator 220 can recover more than about 80% of the heat from the counter flowing exhaust gas.
  • the recuperator 220 recovers between about 70% and about 90% of the heat from the counter flowing exhaust gas. In some embodiments, the recuperator recovers greater than about 90% of the heat from the counter flowing exhaust gas. In some embodiments, the recuperator 220 recovers between less than about 70% of the heat from the counter flowing exhaust gas. In some embodiments, the recovery of heat is determined by a change in temperature of both the exhaust and compressed fluid from when the fluid enters the recuperator and the temperature of the fluid leaving the recuperator in the exhaust and the temperature of the fluid leaving the recuperator toward the combustion chamber. In some embodiments, a recovery of 70% corresponds to a 70% reduction in temperature difference between the compressed fluid and the exhaust fluid from the time the fluid enters the recuperator until the time the fluid exits the recuperator.
  • Figures 12A-12C depict various views of embodiments of the recuperator 220.
  • Figure 12A shows a perspective view of embodiments of the recuperator 220 in which the fluid enters the recuperator in a center portion of the recuperator through the first concentric passage 660.
  • Figure 12B illustrates a partial cross-sectional schematic view of the recuperator 220, showing the first concentric passage 660 that directs fluid through the inlet ducts 665 to the interstitial spaces between the tubes 650 and toward the combustion chamber.
  • Figure 12B Also depicted in Figure 12B is the outer passage 620, which conducts exhaust fluid in a first cross-path around the first concentric passage 660, and which is in communication with the tubes 650, through which the exhaust fluid flows in a second cross- path past the compressed fluid toward the exhaust outlet port 235.
  • Figure 12C depicts an axial view of embodiments of the recuperator 220, showing the thin walled tubes 650 and the first concentric passage 660.
  • Figures 12A-12C also depict a central passageway 651, through which the shaft 110 can extend and rotate.
  • Figure 12D-12F depict embodiments of the recuperator 220 that include a plurality of outlet ports 662 positioned about a periphery of the recuperator 220. Also depicted are inlets, or entry ports 663 about the periphery of the recuperator 220. Figure 12D also depicts a discharge manifold 664 and a return manifold 665 on opposing ends of the recuperator 220. Figures 12E-12F depict embodiments of the recuperator having a plurality of exhaust ports 235 positioned around the periphery of the recuperator 220. Figure 12F also depicts the recuperator 220 having the plurality of outlet ports 662 in communication with a plurality of combustors 225.
  • the recuperator 220 includes an air foil bearing 668.
  • the bearing 668 is configured to provide support to the shaft 110 during rotation of the shaft 110 and when the turbine 200 is in operation.
  • FIG. 13A shows embodiments of a turbine expander 230 that has a variant of aerofoil shaped spacers 420 affixed to, or integral with, a disk 102 embodied in the turbine expander impeller 700.
  • Hot fluid is injected nearly tangentially and is directed in a circular, vortical path, as indicated by arrow 710.
  • the hot fluid is allowed to expand in the spaces between the disks 102.
  • the fluid impinges upon the spacers 420, imparting its kinetic energy by boundary layer adhesion as well as by reaction force. Leaving the spacers 420, the gas expands to the center outlet port 105, releasing further energy via the boundary layer effect to the disk surface and finally to the vanes 730 at the center outlet port 105.
  • the turbine expander impeller 700 includes a plurality of annular disks 102, and each of the disks have a face 115.
  • the disks 102 are preferably spaced apart from an adjacent disk, such that planes containing the surfaces or faces 115 of adjacent disks 102 are substantially parallel.
  • each disk 102 has an outer edge 120 and an inner opening 465, through which the central shaft 110 extends. As depicted in Figure 13, the disks 102 are configured to transmit kinetic energy between the disks 102, as they rotate about the shaft 110, and fluid introduced into the turbine expander 230 through a fluid inlet port 740.
  • each disk 102 includes a plurality of elongate, arcuate elevations 420 that extend along the face 115 of the disk 102.
  • the arcuate elevations 420 preferably include a first region 750 and a second region 760.
  • the first region 750 is located closer to the shaft 110, or central axis 125 of the shaft 110, than is the second region 760 of the same arcuate elevation 420.
  • the arcuate elevation 420 tapers in width as it extends from the first region 750 to the second region 760, such that a width of each of the arcuate elevations 420 at its first region 750 is greater than a width of the same arcuate elevation at its second region 760.
  • Figure 13B illustrates embodiments of the turbine expander 230 having a plurality of fluid inlet ports 740.
  • Embodiments with a plurality of fluid inlet ports 740 can distribute the working fluid into the turbine expander 230 more evenly about the turbine impeller 700 than expanders 230 having a single inlet port 740.
  • some embodiments have one inlet port 740 and some embodiments have a plurality of inlet ports 740.
  • the turbine impeller 700 is shown with arrows depicting the flow of operating fluid into and through the turbine expander 230.
  • a pressurized fluid is tangentially injected at the circumference, perimeter, or outer edge 120 of the disks 102 and dispersed at high pressure and velocity between the disks 102, moving over the smooth surface in the boundary layer on the surfaces of every disk 102.
  • the spaces between disks 102 are sized to be the sum of the two laminar flow regions of the boundary layers, where the relative speed between fluid and surface approaches zero. Fluid molecules are forced in a spiral path between the disks 102, clinging to the surface to transfer the molecular energy of the hot fluid in a shearing action to the surface.
  • the spent fluid then exits at the center of the disks 102 through an outlet 770, which is in communication with the recuperator 220, driving axial vanes 730 of the impeller 700 upon leaving the impeller 700.
  • the flow of fluid along the surface of the faces 115 of the disks 102 combines with the reaction force against the aerofoil spacers 420 and induces the disks 102 to move with the fluid in accordance with the boundary layer effect described above.
  • an amount of slip has a tendency to occur without the airfoil shaped spacers 420 and has been found to be proportional to the workload.
  • the greater the load the more direct the route taken by the expanding gas from the outer edge 120 to exit 105, until stalling conditions become manifest.
  • the introduction of aerofoil shaped spacers 420 assists in maintaining a constant flow pattern to maintain a constant speed and torque and to reduce the amount of slip.
  • the disk tip speed (or the speed of the outer edge 120 of the disks 102) approaches the fluid velocity, according to boundary layer theory, the geometry of the inlet and outlet edges 120 of the disks 102, the space between the disks 102, the number and size of the disks 102, the shape of the spacers 420, and the operating speed of the disk impellers 700 and the angle of attack (or orientation) of the aerofoil shaped spacers 420.
  • a compressor 210 using boundary layer drag theory operates differently from a turbine expander 230.
  • the driven surfaces move at high speeds over low speed ambient air. Centrifugal force forces the fluid to the edge 120 of the disk 102 and creates a low pressure region between the disks 102 with the ejection of the air in the turbulent flow region slightly away from the disk surface 115.
  • the relative velocity of the gas and surface approaches zero at the surface interface (laminar flow region). It is therefore more difficult to rapidly transfer the air in the laminar flow region.
  • a compressor 210 therefore displaces the air in the turbulent flow region, directly adjacent to the laminar flow region at the surface. Slightly wider spaces between disks 102 are therefore needed for compressors 210 than for turbine expanders 230.
  • Figures 17A and 17B describe this in further detail below.
  • the fluid Upon leaving the vaned axial port 770 of the turbine expander 230 at the center of the impeller 700, the fluid is directed back to the recuperator 220 where it flows inside the creep-resistant thin-walled stainless steel tubes 650 in a double counter-flow mode and in close proximity to the cooler compressed air in substantially parallel paths inside the voids between the tubes 650.
  • the entire flow path of the fluid is able to retain a streamlined spiral shape from the compressor inlet 350 through the turbine 230 through the recuperator 220 to the exhaust outlet 235.
  • FIG. 15A depicts a back plate 800 that is used in connected with the disks 102 of the turbine expander 230 and the compressor 210.
  • the back plate 800 has a central core 810 (which, in some embodiments, is member 365), through which the shaft 110 can extend, and around which are configured the center axial vanes 366, which are preferably coupled to core 810.
  • Positioned around a face 820 of the back plate 800 are aligning rods, or fixing pins 525, that extend from the face 820 in a direction substantially parallel to a central axis of the central core 810.
  • the core 810 preferably includes at least one spline 830 for increasing a friction fit between the core 810 and the shaft 110 .
  • Figure 15B illustrates an annular disk 102 that is configured to be used in connection with the back plate 800 of Figure 15A.
  • the disk 102 includes a plurality of apertures 840, through which the aligning rods 525 of the back plate 800 may be inserted to orient the disk 102 with the back plate 800, the central core 810, and the center vanes 366.
  • the disk 102 further includes a central aperture 850 that can accommodate insertion of the central core 810 and center vanes 366.
  • the disk 102 includes elevated portions 420 that can be shaped, in some embodiments, as an airfoil. Some embodiments provide that the elevated portions 420 are the width of the boundary layer of the operating fluid when the turbine 200 is in use.
  • Figures 16A and 16B depict a plurality of disks 102 assembled on a back plate 800 and described with reference to Figures 15A and 15B.
  • parameters that influence the performance characteristics of a disk turbine design include a diameter of compressor and turbine disks 102, the rotor speed, the gaps between the disks 102, the number of disks 102, the shape of the spacers 420, and the inlet nozzle 744 design.
  • the turbine 200 includes turbine impeller disks 102 having a diameter of about 25 cm.
  • the turbine impeller 700 can have disks 102 with diameters ranging from about 20 cm to about 30 cm.
  • Some embodiments include a turbine impeller 700 with disks 102 having diameters ranging from about 15 cm to about 35 cm, and some embodiments include turbine impellers 700 with disks 102 having diameters less than about 15 cm or greater than about 35 cm.
  • the turbine impeller 700 can include about 60 disks. In some embodiments the turbine impeller 700 can have from about 50 disks to about 70 disks, and in some embodiments, the turbine impeller 700 can have from about 40 disks to about 80 disks. In some embodiments, the turbine impeller 700 can have less than about 40 disks or greater than about 80 disks.
  • the number of turbine impeller disks 102 is dependent upon the number of compressor impeller disks 102, or the number of compressor disks 102 is determined by a ratio with respect to the turbine disks 102, as discussed above.
  • the ratio of compressor disks to turbine expander disks is about 2.5:1.
  • the operational speed of the turbine impeller 700 is the same as that of the shaft 110.
  • the rotational speed of the turbine impeller 700 is about 20,000 rpm.
  • the rotational speed of the turbine impeller 700 ranges between about 15,000 rpm and about 25,000 rpm.
  • the rotational speed of the turbine impeller 700 ranges from about 10,000 rpm to about 30,000 rpm.
  • the rotational speed of the turbine impeller 700 is less than about 10,000 rpm or greater than about 30,000 rpm.
  • the rotational speed of the turbine impeller 700 can be about 40,000 rpm, about 50,000 rpm, about 75,000 rpm, and about 100,000 rpm.
  • the turbine impeller disks 102 are spaced at a distance to enhance the efficiency of the turbine impeller 700. In some embodiments, the turbine impeller disks 102 are spaced about 0.6 mm apart. In some embodiments, the turbine impeller disks 102 are spaced between about 0.4 mm and about 0.8 mm apart, and in some embodiments, the turbine impeller disks 102 are spaced between about 0.2 mm and about 1.0 mm apart. In some embodiments, the turbine impeller disks 102 are spaced less than about 0.2 mm or greater than about 1.0 mm apart. [0194] Figures 17A-17B illustrate schematic representations of the flow past two disks. The laminar flow regions are represented by D and E in Figure 17A.
  • the length A is the distance that the fluid flows along the surface of the disk.
  • a space represented by Y represents a space through which the majority of flow passes with laminar flow, as depicted in Figure 17A.
  • Energy is transferred to or from the disks via the laminar flow boundary layer regions of Figure 17A.
  • the distance between the disks, X is increased to allow turbulent fluid flow in the region B between the boundary layers.
  • the majority of flow due to laminar flow occurs in a space represented by ⁇ .
  • Figure 17B illustrates the different in flow area by separating the disks and permitting flow in the additional space represented by B.
  • the turbulent fluid intermixes and separates, increasing the kinetic energy of the air, to be subsequently converted to pressure in the circumferential axial flow diffuser.
  • the continuous stream of separated fluid molecules are propelled at high speeds into the circumferential diffuser, where they are compressed with other fluid molecules and slow down, increasing the pressure.
  • the pressure increase depends upon the velocity with which the air leaves the circumference of the disks.
  • the flow of compressed air is calculated as a positive displaced volume of the active turbulent space between the disks.
  • the distance between the total boundary layers i.e., the laminar flow plus the turbulent flow regions, should be zero (represented by the dotted rectangle below point B in Figure 17A). When this distance becomes a minus number, inadequate space is presented to the turbulent air to mix, resulting in undue slippage and a reduction in compressor efficiency.
  • point B becomes greater than zero, introducing a doldrums effect, which dissipates the energy and reduces the efficiency.
  • Figure 18 depicts the boundary layer effect turbine in connection with peripheral devices that can be used to control or regulate operation of the turbine 200.
  • peripheral devices that can be used to control or regulate operation of the turbine 200.
  • a power inverter 863 for example, illustrated in Figure 18 is a power inverter 863, power conditioning system 867, and turbine controls 869.
  • These peripheral devices can be part of a single unit that includes the boundary layer effect turbine.
  • Figures 19A and 19B respectively depict a schematic front view and rear view of the boundary layer effect turbine 200, which highlight the compact configuration of the turbine 200.
  • FIGS 20A-C depict a combustor 225, which accepts preheated air from the recuperator 220 in an air to fuel ratio of, for example, about 30:1 and a pressure of, for example, about 2.1 kPa.
  • the combustor 225 comprises a primary 910 and a secondary burner 915, the primary burner 910, which represents the minimum operating capacity of 10%, is situated in the center. It is surrounded by a plurality of Venturis 920 that are part of the secondary burners 915.
  • the Venturis 920 of the secondary burners 915 draw fuel from a fuel line 927 at the rate determined by the flow of air through the throats 925 of the Venturis 920.
  • the Venturis 920 therefore, in some embodiments, obviate the need for a separate gas compressor to compress the fuel before injection into the combustor 225.
  • the primary burner 910 stabilizes the flames of the surrounding burners 915 and likewise draws fuel from a primary fuel line 929, which can include an axial fuel line 931. Excess air is bypassed around the burner casing to cool the casing before it is subsequently mixed with the hot gas emanating from the venturi burners.
  • An annular excess air bypass control system 936 facilitates burner management by either sending air through the Venturis or bypass it around the combustor through, for example, a plurality of apertures 934.
  • the shape of the burner casing accelerates the hot gas prior to entering the turbine expander 230.
  • a spark plug 937 that can be used, in some embodiments, to ignite the burners.
  • the boundary layer effect turbine 200 described herein can be operated on any credible form of combustible liquid or gaseous fuels, as long as the burner arrangement and fuel air ratio are properly designed to match the specific fuel. It can further be utilized with natural sources of heat, such as a geothermal source.
  • the boundary layer effect turbine 200, microturbine, or DiskTurbine ⁇ can also run as an unfired turbine by sharing the same fuel supply with fuel cells, or it can be driven by the pressurized off gases of solid oxide fuel cells. In such applications, the combined power conversion efficiency could exceed 70%.
  • the boundary layer effect turbine can operate with various fuel cell technologies and fuel types, including but not limited to the following: bio-diesel, ethanol, natural gas, liquid propane gas, kerosene, diesel or any other gaseous or liquid hydrocarbon, coal bed methane or methane from municipal waste dumps (fuels are not universally interchangeable with the same burners) and operates on renewable plant alcohol and oils or straight hydrogen.
  • the coal can be fired in a fluidized bed combustor (FBC).
  • FBC fluidized bed combustor
  • Lime is added to neutralize the sulfur to improve the chimney stack emission.
  • Heat resistant heat exchanger tubes are inserted in the firing zone of the FBC and internally pressurized by the compressed air from the compressor. The heated compressed air is allowed to expand in the turbine to generate power. The clean hot exhaust air is then used for space heating, process heating, or steam generation for further power generation and/or HVAC.
  • FIG. 21-24 Illustrated in Figures 21-24 are embodiments of a high speed reducer 1000 that can be used in connection with turbines, for example, a boundary layer effect microturbine 200, to transmit the rotary motion of the shaft 110.
  • the high output speeds (usually more than about 20,000 up to 100,000 rpm and more ) at which microturbines operate makes the turbines ill-suited for applications other than power generation purposes.
  • Use of microturbines in automotive, marine, or aircraft applications can be problematic because of limitations of roller type bearings and reduction gearboxes.
  • HSR high-speed hydrodynamic speed reducer 1000
  • hybrid passenger vehicles may operate within this range.
  • the HSR 1000 illustrated in Figures 21 and 22, operates on the displacement of a special hydraulic fluid being recirculated at high speeds between an inner drive and an outer multiple spiraled helix drive 1010 and a single spiraled circumferential volute 1020.
  • the volute comprises an inside portion 1015 that has an outer diameter greater than the outer diameter of the volute 1020, such that the volute 1020 can be inserted into the inside portion 1015.
  • a sleeve 1030 Between the outer diameter of the volute 1020 and the outer diameter of the insider portion 1015 of the helix drive 1010 is positioned a sleeve 1030, such that, when assembled, the volute 1020 is positioned within the sleeve 1030, and the sleeve 1030 is positioned within the inside portion 1015 of the helix drive 1010.
  • the arrangement of the volute 1020, sleeve 1030, and the drive 1010 are substantially concentric.
  • the volute 1020, sleeve 1030, and drive 1010 are preferably encased in a casing 1040 that can include a first portion 1045 and a second portion 1050.
  • the first and second portions 1045, 1050 when coupled together form a hollow interior, which is configured to contain the volute 1020, sleeve 1030, drive 1010, and operating oil.
  • Each of the first and second portions 1045, 1050 preferably accommodate coupling with a shaft.
  • the first portion 1045 can include an aperture 1047 through which an output shaft 1110 can extend.
  • the output shaft 1110 can be supported by a boss 1048 that contains a supporting bearing 1049.
  • the second portion 1050 can be configured to couple with embodiments of the turbine 200 described herein.
  • the second portion 1050 can include a plurality of fins 1051 that disperse heat from the HSR 1000 and direct fluid flow into a compressor 210.
  • the helix drive 1010 conveys a specially designed synthetic oil axially along the thread cavity of the inside portion 1015, the oil being discharged into the multiple spiraled volutes of an outer element over the sleeve 1030, which is a concentric tubular divider.
  • Four or more spiral shaped volutes of the outer element has only one spiral turn from end to end.
  • a constant volume of fluid, which is supplied by the volute 1020, which operates as a worm drive, is divided equally between the number of spiral volutes, each volute having a similar cross sectional area as that of the volute 1020.
  • the reaction forces that are created are axial in nature.
  • the drive element 1010 will tend to move to the opposite side the fluid would be traveling. Since the fluid is recirculated, it re-enters the drive element 1010 at the bottom of the drive element 1010 to balance that axial force.
  • the same situation arises with the tubular divider, or sleeve 1030, which is being kept in an equilibrium position between the drive, or volute 1020, and driven elements 1010.
  • the driven element 1010 will however tend to move axially towards the output shaft 1110.
  • a slow speed thrust bearing may be fitted.
  • the output shaft 1110 is an inherent part of the driven element 1010.
  • the driven element 1010 is shown with four spiraled volutes each with a single turn.
  • the geared teeth at the skirt of the driven element 1010 act as an oil pump to drive a small percentage of the oil to an external oil cooler via a tangential outlet.
  • the volute 1020 is depicted with a single spiral with three turns, followed by the concentric tubular divider, or sleeve 1030.
  • the main casing is shown with its connecting fins 1051, which can also be structural members to support the HSR 1000 and the compressor.
  • the speed reducer 1000 includes a housing defining an internal chamber with a central axis, a cylindrical drive element within the internal chamber, the drive element being aligned along the central axis and having a helical recess along an outer surface of the drive element that defines a fluid drive flow path, the drive element being configured to couple with a rotatable speed reducer input.
  • the speed reducer can also include a driven element within the internal chamber, the driven element being aligned along the central axis and having a cylindrical bore with an internal surface having a helical recess that defines a fluid driven flow path.
  • the driven element is configured to couple with a rotatable speed reducer output.
  • a tubular divider element within the internal chamber and aligned along the central axis, the divider element can have a first end and a second end and being positioned between the outer surface of the cylindrical drive element and the internal surface of the driven element.
  • the reducer 100 includes operating fluid within the internal chamber, the fluid drive flow path, and the fluid driven flow path, and rotation of the speed reducer output is achieved by rotating the speed reducer input, which rotates the drive element and drives the operating fluid in a first axial direction along the fluid drive flow path, around the first end of the tubular divider, in a second axial direction along the fluid driven flow path, rotating the driven element, around the second end of the tubular divider, and into the fluid drive flow path.
  • a magnetic drive 1018 which drives a central element 1020, similar to a worm drive, and typically has three or more spiral turns of adequate thread diameter.
  • a magnetic drive is used. This drive has the capability of transferring mechanical power through a nonmagnetic sleeve, making it possible to transfer horsepower from one compartment to the adjacent one with out any physical contact.
  • FIGs 23A and 23B depict embodiments of driving the main element, previously referred to as the volute 1020.
  • Powerful permanent magnets 1021 such as Alnico magnets, which possess a tolerance for temperatures up to 300 0 C, are inserted with opposing poles into the drive element 1020 in such a manner that they will be attracted by the powerful permanent magnets, which are inserted into the non-magnetic stainless steel drive shaft 110.
  • the permanent magnets 1021 maintain the concentricity of the drive shaft 110 and the drive element 1020 to maintain a constant air gap 1022 around the shaft 110.
  • Figure 24 depicts embodiments of the turbine 200 coupled to embodiments of the HSR 1000.
  • the turbine 200 and HSR 1000 can be used in connection with commercially available air conditioning systems 1100, such as that depicted in Figure 25, which normally run on natural gas, but which can readily be adapted to use the exhaust gas of the turbine 200 to provide free air conditioning and heating to commercial or industrial complexes.
  • Air conditioning systems 1100 such as that depicted in Figure 25, which normally run on natural gas, but which can readily be adapted to use the exhaust gas of the turbine 200 to provide free air conditioning and heating to commercial or industrial complexes.
  • Overall thermal efficiencies of greater than 75% could be achieved, making the combination an environmentally preferred low operating cost system.
  • the system consists of a reversible absorption heat pump unit for production of hot water up to 140 0 F and chilled water to 37.4 0 F, using waste energy.
  • extremely high energy efficiency can be achieved by means of recovering 34% of the energy from the renewable source (air).

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Adhesives Or Adhesive Processes (AREA)

Abstract

La présente invention concerne les modes de réalisation d'une turbine à effet de couche limite et d'un réducteur de vitesse hydrodynamique. L'invention concerne une turbine à effet de couche limite utilisant le phénomène de couche limite pour entraîner une pale de turbine constituée d'une pluralité de disques espacés orientés le long d'un arbre rotatif. Lorsqu'un fluide d'actionnement est dirigé en direction des surfaces de la pluralité de disques de la turbine à effet de couche limite, l'énergie est transférée du fluide vers les disques du fait des propriétés d'adhérence et de viscosité du fluide.
PCT/US2008/088687 2007-12-31 2008-12-31 Turbine à effet de couche limite WO2009088955A2 (fr)

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US12/811,368 US20110097189A1 (en) 2007-12-31 2008-12-31 Boundary layer effect turbine

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US1808907P 2007-12-31 2007-12-31
US61/018,089 2007-12-31
US3091708P 2008-02-22 2008-02-22
US61/030,917 2008-02-22

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WO2009088955A3 WO2009088955A3 (fr) 2010-01-07

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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011057019A1 (fr) * 2009-11-04 2011-05-12 Wilson Erich A Turbine à couche limite composite
CN102080576A (zh) * 2010-12-16 2011-06-01 清华大学 一种边界层透平发电装置
DE102010017733A1 (de) * 2010-07-05 2012-01-05 Robert Stöcklinger Tesla-Turbine und Verfahren zur Wandlung von Strömungsenergie eines Fluids in kinetische Energie einer Welle einer Tesla-Turbine
US8822468B2 (en) 2008-02-28 2014-09-02 Novartis Ag 3-Methyl-imidazo[1,2-b]pyridazine derivatives
EP2775095A1 (fr) * 2013-03-04 2014-09-10 Piotr Jeute Turbine radiale
US9657594B2 (en) 2013-03-12 2017-05-23 Rolls-Royce Corporation Gas turbine engine, machine and self-aligning foil bearing system
WO2021105293A1 (fr) * 2019-11-29 2021-06-03 Xeikon Manufacturing N.V. Appareil d'impression à rouleau de transfert de chaleur
WO2021128283A1 (fr) * 2019-12-23 2021-07-01 长江大学 Turbine annulaire circulaire modifiée
WO2023089331A1 (fr) * 2021-11-18 2023-05-25 Tree Associates Ltd. Moteur comprenant une turbine à couche limite

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0818825D0 (en) * 2008-10-14 2008-11-19 Evans Michael J Water turbine utilising axial vortical flow
US11098722B2 (en) * 2011-04-20 2021-08-24 Daniel Woody Internal combustion boundary layer turbine engine (BLTE)
WO2013023147A1 (fr) * 2011-08-11 2013-02-14 Beckett Gas, Inc. Chambre de combustion
WO2013029010A1 (fr) * 2011-08-24 2013-02-28 Qwtip Llc Système et procédé de traitement d'eau
MX344565B (es) 2011-09-15 2016-12-20 Leed Fabrication Services Inc Sistemas de turbina de disco de capa límite para controlar dispositivos neumáticos.
MX344566B (es) 2011-09-15 2016-12-20 Leed Fabrication Services Inc Sistemas de turbina de disco de capa límite para recuperación de hidrocarburos.
CN104246177A (zh) * 2012-02-21 2014-12-24 巴布科克·博西格·施泰因米勒有限公司 具有管状同流换热器的微型燃气涡轮机设备
WO2014160270A1 (fr) 2013-03-14 2014-10-02 Leed Fabrication Services, Inc. Procédés et dispositifs pour le séchage de gaz contenant des hydrocarbures
US9951620B1 (en) * 2014-04-03 2018-04-24 David A Shoffler Working fluid turbo
US20170356459A1 (en) * 2016-06-08 2017-12-14 Nidec Corporation Blower apparatus
GB2551181A (en) * 2016-06-09 2017-12-13 Hieta Tech Limited Radial flow turbine heat engine
GB201710076D0 (en) * 2017-06-23 2017-08-09 Rolls Royce Plc Secondary flow control
US10830141B2 (en) * 2017-12-15 2020-11-10 General Electric Company Recuperator for gas turbine engine
US20230279858A1 (en) * 2020-11-04 2023-09-07 John Lloyd Bowman Boundary-Layer Pump and Method of Use

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3898793A (en) * 1972-08-17 1975-08-12 Toyota Motor Co Ltd Bearing system for gas turbine engine
US4402647A (en) * 1979-12-06 1983-09-06 Effenberger Udo E Viscosity impeller
US5932940A (en) * 1996-07-16 1999-08-03 Massachusetts Institute Of Technology Microturbomachinery
US5977677A (en) * 1996-06-26 1999-11-02 Allison Engine Company Combination bearing for gas turbine engine
US6327860B1 (en) * 2000-06-21 2001-12-11 Honeywell International, Inc. Fuel injector for low emissions premixing gas turbine combustor
US6334299B1 (en) * 1996-12-16 2002-01-01 Ramgen Power Systems, Inc. Ramjet engine for power generation
US20030053909A1 (en) * 2001-07-09 2003-03-20 O'hearen Scott Douglas Radial turbine blade system
US20040009063A1 (en) * 2002-07-12 2004-01-15 Polacsek Ronald R. Oscillating system entraining axial flow devices
US20050169743A1 (en) * 2002-10-02 2005-08-04 Centripetal Dynamics, Inc. Method of and apparatus for a multi-stage boundary layer engine and process cell
US20070092369A1 (en) * 2005-10-25 2007-04-26 Erich Wilson Bracket/Spacer Optimization in Bladeless Turbines, Compressors and Pumps

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3898793A (en) * 1972-08-17 1975-08-12 Toyota Motor Co Ltd Bearing system for gas turbine engine
US4402647A (en) * 1979-12-06 1983-09-06 Effenberger Udo E Viscosity impeller
US5977677A (en) * 1996-06-26 1999-11-02 Allison Engine Company Combination bearing for gas turbine engine
US5932940A (en) * 1996-07-16 1999-08-03 Massachusetts Institute Of Technology Microturbomachinery
US6334299B1 (en) * 1996-12-16 2002-01-01 Ramgen Power Systems, Inc. Ramjet engine for power generation
US6327860B1 (en) * 2000-06-21 2001-12-11 Honeywell International, Inc. Fuel injector for low emissions premixing gas turbine combustor
US20030053909A1 (en) * 2001-07-09 2003-03-20 O'hearen Scott Douglas Radial turbine blade system
US20040009063A1 (en) * 2002-07-12 2004-01-15 Polacsek Ronald R. Oscillating system entraining axial flow devices
US20050169743A1 (en) * 2002-10-02 2005-08-04 Centripetal Dynamics, Inc. Method of and apparatus for a multi-stage boundary layer engine and process cell
US20070092369A1 (en) * 2005-10-25 2007-04-26 Erich Wilson Bracket/Spacer Optimization in Bladeless Turbines, Compressors and Pumps

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8822468B2 (en) 2008-02-28 2014-09-02 Novartis Ag 3-Methyl-imidazo[1,2-b]pyridazine derivatives
WO2011057019A1 (fr) * 2009-11-04 2011-05-12 Wilson Erich A Turbine à couche limite composite
DE102010017733A1 (de) * 2010-07-05 2012-01-05 Robert Stöcklinger Tesla-Turbine und Verfahren zur Wandlung von Strömungsenergie eines Fluids in kinetische Energie einer Welle einer Tesla-Turbine
WO2012004127A1 (fr) 2010-07-05 2012-01-12 Stoecklinger Robert Turbine de tesla et procédé pour faire fonctionner une turbine de tesla
DE102010017733B4 (de) * 2010-07-05 2013-08-08 Robert Stöcklinger Tesla-Turbine und Verfahren zur Wandlung von Strömungsenergie eines Fluids in kinetische Energie einer Welle einer Tesla-Turbine
CN102080576A (zh) * 2010-12-16 2011-06-01 清华大学 一种边界层透平发电装置
EP2775095A1 (fr) * 2013-03-04 2014-09-10 Piotr Jeute Turbine radiale
WO2014135231A1 (fr) 2013-03-04 2014-09-12 Piotr Jeuté Turbine radiale
US9657594B2 (en) 2013-03-12 2017-05-23 Rolls-Royce Corporation Gas turbine engine, machine and self-aligning foil bearing system
WO2021105293A1 (fr) * 2019-11-29 2021-06-03 Xeikon Manufacturing N.V. Appareil d'impression à rouleau de transfert de chaleur
WO2021128283A1 (fr) * 2019-12-23 2021-07-01 长江大学 Turbine annulaire circulaire modifiée
WO2023089331A1 (fr) * 2021-11-18 2023-05-25 Tree Associates Ltd. Moteur comprenant une turbine à couche limite

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