EP3103961B1 - Turbomachine à couche limite et procédé de fonctionnement associé - Google Patents

Turbomachine à couche limite et procédé de fonctionnement associé Download PDF

Info

Publication number
EP3103961B1
EP3103961B1 EP15171530.7A EP15171530A EP3103961B1 EP 3103961 B1 EP3103961 B1 EP 3103961B1 EP 15171530 A EP15171530 A EP 15171530A EP 3103961 B1 EP3103961 B1 EP 3103961B1
Authority
EP
European Patent Office
Prior art keywords
boundary layer
fluid
disks
turbomachine
partition
Prior art date
Legal status (The legal status 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 status listed.)
Active
Application number
EP15171530.7A
Other languages
German (de)
English (en)
Other versions
EP3103961A1 (fr
Inventor
Bill HELTON
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Green Frog Turbines (uk) Ltd
Original Assignee
Green Frog Turbines (uk) Ltd
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 Green Frog Turbines (uk) Ltd filed Critical Green Frog Turbines (uk) Ltd
Priority to EP15171530.7A priority Critical patent/EP3103961B1/fr
Priority to US14/991,228 priority patent/US11208890B2/en
Priority to JP2018516648A priority patent/JP2018521268A/ja
Priority to US15/735,510 priority patent/US20200256191A1/en
Priority to AU2016276259A priority patent/AU2016276259A1/en
Priority to CN201680043992.3A priority patent/CN109983202A/zh
Priority to PCT/IB2016/001360 priority patent/WO2016198962A2/fr
Priority to CA2989093A priority patent/CA2989093A1/fr
Priority to KR1020187000709A priority patent/KR20180098215A/ko
Priority to MX2017016039A priority patent/MX2017016039A/es
Publication of EP3103961A1 publication Critical patent/EP3103961A1/fr
Priority to PH12018500094A priority patent/PH12018500094A1/en
Application granted granted Critical
Publication of EP3103961B1 publication Critical patent/EP3103961B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/16—Centrifugal pumps for displacing without appreciable compression
    • F04D17/161—Shear force pumps
    • 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
    • F05D2210/00—Working fluids
    • F05D2210/40—Flow geometry or direction
    • F05D2210/42—Axial inlet and radial outlet
    • 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
    • F05D2210/00—Working fluids
    • F05D2210/40—Flow geometry or direction
    • F05D2210/43—Radial inlet and axial outlet
    • 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
    • F05D2210/00—Working fluids
    • F05D2210/40—Flow geometry or direction
    • F05D2210/44—Flow geometry or direction bidirectional, i.e. in opposite, alternating directions
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/25—Three-dimensional helical
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/292—Three-dimensional machined; miscellaneous tapered
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced

Definitions

  • the present invention relates to boundary layer machines and rotor assemblies therefor.
  • Tesla can be used as a pump or as a motor.
  • Such devices take advantage of the properties of a fluid when in contact with the rotating surfaces of the disks. If the disks are driven by the fluid, then as the fluid passes between the spaced apart disks, the movement of the fluid causes the disks to rotate thereby generating power which can be transmitted external to the device via a shaft to provide motive force for various applications. Accordingly, such devices function as a motor or turbine.
  • the fluid is essentially static, rotation of the disks will cause the fluid to commence rotating in the same direction as the disks and to thus draw the fluid through the device, thereby causing the device to function as a pump or a fan.
  • boundary layer turbomachines all such devices, whether used as a motor or as a pump or fan, are referred to generically as "boundary layer turbomachines.”
  • a typical boundary layer turbomachine has several shortcomings.
  • the thin disks of a typical boundary layer turbomachine tend to deflect under operating loads, which can cause contact with other disks and/or other structures, such as a housing that encloses the disks.
  • some boundary layer turbomachines include features such as dimples incorporated into the housing or through-bolts which act as spacers.
  • efficiencies of typical boundary later turbomachines can be limited. Accordingly, improvements in boundary layer turbomachine design continue to be sought.
  • US 4534699 A relates to a coal fired turbine having a rotor assembly comprising a plurality of discs.
  • US 2005/019154 A1 relates to an impeller system comprising a plurality of discs.
  • WO 2008/070369 A2 relates to a wind turbine including a stick of substantially parallel discs.
  • WO 2005/081766 A2 relates to a bladeless conical radial turbine comprising a plurality of spaced apart conical elements.
  • GB 2226081 A relates to a fluid friction pump or turbine comprising a rotor assembly with a continuous helix.
  • a boundary layer turbomachine is disclosed herein that can minimize or eliminate disk deflections that tend to cause contact between adjacent disks and/or a housing. In one aspect, principles are disclosed herein that also provide increased efficiency of the boundary layer turbomachine.
  • the present invention provides a boundary layer turbomachine, as set forth in claim 1.
  • the plurality of disks are oriented perpendicular to the axis of rotation.
  • the axis of rotation extends through the interior opening.
  • the outer edges of the disks are tapered.
  • the interior opening is defined at least in part by a helical baffle to facilitate movement of the fluid through the rotor assembly.
  • the extension member includes a vent port extending therethrough in fluid communication with the interior opening.
  • vent port is oriented along the axis of rotation and wherein the vent port is defined at least in part by a helical baffle to facilitate movement of the fluid through the vent port.
  • the inlet opening is associated with the outer chamber such that the outer chamber serves as an expansion chamber for the fluid.
  • the fluid is a gas, a liquid, or a combination thereof.
  • the partition openings are defined by two or more partition members.
  • the partition openings have a tangential cross-sectional area that increases in a radially inward direction.
  • the partition openings comprise a venturi configuration.
  • the partition openings are equally spaced circumferentially around the partition.
  • the turbomachine is configured such that fluid moving through the housing is guided into the gaps at a plurality of locations circumferentially spaced around the rotor assembly at an angle in the range of 40° to 60°, optionally 45° to 55°, for example 51° or 52° relative to a radius of the discs.
  • turbomachine further comprising a debris trap.
  • the debris trap is formed by a groove along an inner radial surface of a portion of the partition.
  • the interior opening defines a fluid flow path coinciding with the axis of rotation.
  • the disks are spaced apart by a plurality of spacers. Further preferably the spaces have an airfoil cross-section or the disks and spacers form a monolithic structure.
  • the disks are permanently coupled to one another by the plurality of spacers.
  • the disks are permanently coupled to one another with a resin.
  • the spacers are arranged in a ring configuration across each disk.
  • the ring configuration comprises a plurality of rings concentric about the axis of rotation.
  • a radial relationship of the plurality of rings may correspond to the Fibonacci ratio or the Golden ratio.
  • the spacers are arranged with a longitudinal axis at an angle in the range of 40° to 60°, optionally 45° to 55°, for example 51° or 52° relative to a radius of the discs.
  • the interior opening defines a helical baffle to facilitate movement of the fluid through the rotor assembly.
  • the present invention also provides a method of operating the boundary layer turbomachine of the present invention, the method comprising feeding a mixture of gas and liquid through the one or more inlet openings to drive the boundary layer turbomachine, as set forth in claim 18.
  • substantially refers to a degree of deviation that is sufficiently small so as to not measurably detract from the identified property or circumstance.
  • the exact degree of deviation allowable may in some cases depend on the specific context.
  • adjacent refers to the proximity of two structures or elements. Particularly, elements that are identified as being “adjacent” may be either abutting or connected. Such elements may also be near or close to each other without necessarily contacting each other. The exact degree of proximity may in some cases depend on the specific context.
  • the term "at least one of' is intended to be synonymous with “one or more of.”
  • “at least one of A, B and C” explicitly includes only A, only B, only C, or combinations of each.
  • Numerical data may be presented herein in a range format. It is to be understood that such range format is used merely for convenience and brevity and should be interpreted flexibly to include not only the numerical values explicitly recited as the limits of the range, but also to include all the individual numerical values or sub-ranges encompassed within that range as if each numerical value and sub-range is explicitly recited. For example, a numerical range of about 1 to about 4.5 should be interpreted to include not only the explicitly recited limits of 1 to about 4.5, but also to include individual numerals such as 2, 3, 4, and sub-ranges such as 1 to 3, 2 to 4, etc.
  • FIGS. 2A-2B illustrate exploded views of the boundary layer turbomachine 100 for further reference.
  • the boundary layer turbomachine includes a housing 110, which can include complimentary housing portions 111a, 111b.
  • the housing also has an inlet opening 112 and an outlet opening 113 to facilitate movement of a fluid (i.e., a gas and/or a liquid) through the housing.
  • the outlet opening 113 can be located at or near a rotational axis 101 of a rotor assembly 120 while the inlet opening 112 can be located on the housing 110 radially outward from the rotational axis 101.
  • opening 113 can be an inlet opening and opening 112 can be an outlet opening based on operation of the boundary layer turbomachine.
  • the boundary layer turbomachine can be designed and operated as "directional" in that the flow of fluid always enters the housing via the same inlet opening and exits the housing via the same outlet opening.
  • the boundary layer turbomachine can be designed and operated as "bidirectional" in that the flow of fluid can be switched to enter the housing via either opening 112, 113 and exit the housing via the other opening to obtain forward and reverse fluid flow.
  • the housing can include an opening 114 ( FIG.
  • opening 112 can serve as an inlet opening
  • opening 113 and/or opening 114 can serve as outlet openings
  • opening 113 and/or opening 114 can serve as inlet openings
  • opening 112 can serve as an outlet opening.
  • multiple openings, which can serve as inlet and/or outlet openings can be located on the housing 110 radially outward from the rotational axis similar to opening 112.
  • the housing 110 defines an interior space 115 to accommodate a rotor assembly 120.
  • the rotor assembly is configured to rotate about the axis of rotation 101.
  • the rotor assembly has a plurality of disks 121 spaced apart along the axis of rotation.
  • the disks can be substantially planar and oriented perpendicular to the axis of rotation, although any suitable disk configuration can be utilized, such as a conical disk configuration. Regardless, the disks can be substantially parallel to one another throughout.
  • any suitable number of disks can be utilized (e.g., depending on power requirements).
  • the plurality of disks 121 define an interior opening (internal to the plurality of disks 121 and hidden from view) along the axis of rotation.
  • fluid can pass through gaps between the disks and the interior opening as the fluid moves through the housing from the inlet opening 112 to the outlet opening 113 and/or 114.
  • the interior opening is free of any structural material as there is not shaft extending through the interior opening to facilitate rotation.
  • the interior opening provides a central void centred on the axis of rotation and defines a fluid flow path through the interior opening that coincides with the axis of rotation. This can facilitate laminar flow through the gaps and the interior opening, since there are no structural parts that would be needed to fix a shaft in the opening (and which would hence rotate about the shaft) interfering with the flow.
  • the rotor assembly 120 also includes extension members 122a, 122b to couple the rotor assembly to the housing 110 and facilitate rotation of the rotor assembly about the axis of rotation 101.
  • the extension members122a, 122b are attached to the plurality of disks 121 opposite one another and substantially inline to facilitate rotation of the rotor assembly about the axis 101.
  • the extension members 122a, 122b can be attached to the plurality of disks 121 using an adhesive, fasteners, or any other suitable substance or device.
  • the extension member can include a flange 123a, 123b to interface with the plurality of disks 121 (more specifically the flange 123a, 123b can interface with a respective adjacent one of the plurality of disks 121) and facilitate coupling with the disks.
  • the extension members 122a, 122b can be mounted on bearings when coupled to the housing 110 to provide low friction rotational interface.
  • the extension members 122a, 122b include vent ports 125a, 125b extending through the extension members in fluid communication with the interior opening formed by the plurality of disks 121. Thus fluid can exit or enter the housing via the extension member vent ports 125a, 125b, which extend through the housing openings 113, 114, respectively.
  • one of the extension members 122a, 122b can be designed as a blank closing the interior opening at one end, so that fluid exits or enters through the other one of the extension members 122a, 122b.
  • the various components of the boundary layer turbomachine 100 can be constructed of any suitable material
  • the rotor assembly 120 i.e., the plurality of disks 121, the extension member 122a, and/or the extension member 122b
  • the housing 110 i.e., the housing portion 111a and/or the housing portion 111b
  • the rotor assembly 120 is designed to provide a low mass to volume ratio. In some cases, the rotor assembly 120 can be provided as a complete unit as a replacement of a damaged or worn rotor assembly.
  • the extension member 122a, 122b can facilitate coupling the rotor assembly 120 to a generator or a motor.
  • the extension member 122a, 122b can include a flange 124a, 124b to interface with a generator shaft or a motor shaft and facilitate coupling the rotor assembly 120 to the generator or motor, such as utilizing fasteners, etc.
  • a generator e.g., an electric generator or a pump
  • a motor can be coupled to the rotor assembly 120 to cause rotation of the rotor assembly, thereby causing movement of the fluid through the housing 110 and utilizing the boundary layer turbomachine 100 as a pump.
  • each housing portion 111a, 111b can be coupled to a generator or a motor.
  • the housing portions 111a, 111b can include mounting features 116a, 116b, respectively, to interface with a generator or a motor and facilitate coupling the housing 110 to the generator or motor, such as utilizing fasteners, welds, etc.
  • the mounting feature 116a, 116b can extend at least as far as the extension member 122a, 122b to facilitate directly attaching the housing 110 to a generator or motor without interference from the extension member 122a, 122b.
  • the boundary layer turbomachine 100 can be operated with the axis of rotation 101 in any suitable orientation, such as vertical or horizontal.
  • the boundary layer turbomachine can be powered by steam from a number of different sources, such as capturing waste heat from a boiler, injecting water directly into the exhaust stream of a liquid fuel generator by replacing the muffler, or by generating its own heat content from a combustor.
  • a fccdwatcr tank can be used to pump, sensors, computers, and other electronic components.
  • water can enter the boundary layer turbomachine 100 as steam and can exit as a liquid, although any fluid within a wide range of pressures and temperatures may be used, which can depend on the material and resin properties when boundary layer turbomachine components are constructed of a carbon or basalt fiber composite.
  • the boundary layer turbomachine 100 includes a partition 130.
  • the partition 130 circumferentially divides the interior space 115 into an outer chamber 116 and a rotor chamber 117 located radially inward of the outer chamber.
  • the outer chamber 116 can be an annular volume having an inner radial dimension 102 of 80 to 95% of a radius 103 of the interior space 115.
  • the rotor assembly 120 is disposed in the rotor chamber 117. Although the illustration shows the rotor assembly engaged with an inner edge of partition members 132, actual contact can create undesirable friction.
  • an outer edge of the rotor assembly can be spaced a rotor gap distance apart from the inner edge of partition members 132.
  • the rotor gap can generally be 85 to 95% of a rotor chamber radius measured to the inner edge.
  • the rotor gap can vary depending on size, but is often from 1 mm to 2 cm at a resting condition. Accordingly, the rotor gap can be designed to accommodate such disk stretching. Notably, operating speeds can vary considerably. However, in many cases the rotor assembly can operate at speeds of 10,000 rpm up to 100,000 rpm.
  • the partition 130 has partition openings 131 such that fluid is movable through the partition between the outer chamber 116 and the rotor chamber 117.
  • the opening 112 can be associated with the outer chamber 116 such that the outer chamber serves as an expansion chamber for the fluid when the opening 112 is an inlet opening.
  • the inlet can also be oriented to produce tangential flow within the expansion chamber.
  • the partition openings 131 are spaced (e.g., equally) circumferentially around the partition 130 so as to allow fluid to move from the outer chamber 116 into the rotor chamber 117 and, thus, into gaps between the disks of the rotor assembly 120, at multiple locations around the outer edge of the disks. This configuration offering multiple access ports from the outer chamber 116 to the rotor assembly 120 disks can increase the efficiency of the turbomachine, particularly when the partition openings 131 are equally spaced from one another.
  • the partition 130 and partition openings 131 an embodiments of how this can be implemented with a single inlet opening, for example opening 112.
  • Other such embodiments connect a single inlet (or outlet) opening to a different kind of manifold, for example a conduit conduit around the perimeter of the turbomachine with ports and/or branch conduits providing fluid flow paths to guide fluid into or from the plurality of locations.
  • the turbomachine has a plurality of inlet (or outlet) openings, each providing a flow path into (or from) the gaps at respective ones of the plurality of locations.
  • one or more openings are associated with two or more of the plurality of locations via respective manifolds.
  • the partition openings 131 can be defined by two or more partition members 132 or formed in a single partition member.
  • the partition members 132 can be arranged in a circular configuration with an internal diameter sized to accommodate the rotor assembly 120 disks (i.e., larger than the outer diameter of the disks).
  • the partition 130 i.e., partition members 132
  • the partition 130 can be an individual component which is secured in place, or integrally formed with the housing, such as housing portion 111a.
  • the partition members 132 illustrated are merely one-half of the partition 130, with a complimentary set of partition members secured to the opposite housing portion 111b.
  • the partition can be formed as a single set of partition members in order to avoid misalignment of complimentary partition members.
  • the partition openings 131 can comprise a venturi configuration.
  • venturi is used herein to generally define a configuration wherein the partition opening 131 formed by two complimenting surfaces 133, 134 of adjacent partition members 132 converges and/or diverges such that fluid passing through the partition opening reaches enhanced speed while concurrently developing a significantly reduced pressure producing an effect similar to the Venturi effect.
  • Any suitable venturi configuration can be utilized.
  • the cross-section of the partition opening 131 normal to the direction of flow through the partition opening 131 can increase in the direction of flow.
  • the partition openings 131 can have an angle 104 of 25 to 55 degrees.
  • the partition openings 131 can have a radial dimension 105 of 5 mm to 5 cm.
  • the partition openings 131 can have an outer circumferential dimension 106 of 5 mm to 5 cm and an inner circumferential dimension 107 of 1 cm to 10 cm.
  • the angle 104, radial dimension 105, outer circumferential dimension 106, and inner circumferential dimension 107 can vary depending on the fluid type, size, and application of the turbomachine. In some embodiments, the angle 104 is in the range of 40° to 60°, more specifically 45° to 55°, for example 51.5° or 51° or 52°, which has been found to result in efficient energy transfer.
  • the partition openings 131 can be reconfigured during use to facilitate bidirectional flow of fluid through the housing.
  • the configuration (i.e., the angle 104, radial dimension 105, outer circumferential dimension 106, and/or inner circumferential dimension 107) of the partition openings 131 can be controlled by manipulating one or more partition members 132 via a motor, which can be actuated by one or more switches to achieve suitable flow characteristics through the partition openings in two directions.
  • the fluid In a steady operational state where fluid enters the housing via the opening 112, the fluid circulates around the outer chamber 116 and maintains a relatively constant pressure regime within the outer chamber.
  • the fluid passes through the partition openings 131 into the rotor chamber 117 and enters the spaces or gaps between the individual disks 121 within the rotor assembly 120.
  • the fluid By adhesive and viscous action on the surfaces of the disks the fluid causes the disks to rotate.
  • the fluid between the disks is acted upon by both centrifugal force and the pressure difference maintained between the outer chamber 116 and the partition openings 131, which causes the fluid to be retained within the disks.
  • This increased residence of the fluid between the disks enables the fluid to continue to transfer energy and do work by imparting further rotation in the form of torque, which increases efficiency and allows the turbomachine to convert more thermal energy to mechanical work.
  • a debris trap 140 can be included to gather and expel heavier particles thrown to the outer edges of the rotor assembly 120 disks by centrifugal force.
  • a portion of the partition 130 can form the debris trap 140 as shown in FIGS. 3A and 3B in the shape of a channel or groove along an inner radial surface of one or more of the partition members 132.
  • the debris trap 140 can convey the particles from the interior space 115 via an opening 141, which can lead to a debris receptacle 142 external to the housing 110 via a conduit 143, as shown in FIGS. 1 and 2A .
  • the illustrated debris trap includes openings 141 at each end, although a single opening may be suitable.
  • the debris receptacle 142 can be easily serviced and cleaned utilizing steam pressure and gravity.
  • the debris trap 140 can therefore capture particles from the fluid and prevent the particles from leaving the turbomachine as emissions. In certain applications this can dramatically reduce the environmentally negative emissions associated with typical existing technologies.
  • the opening 112 can be configured as an adaptive inlet port to provide the optimal efficiency intake pressure and/or flow pattern for the fluid.
  • a modular, replaceable inlet fitting 118 can optionally be used to provide different orifice or inlet opening sizes as desired to affect the intake pressure and/or flow pattern of the fluid.
  • the inlet manifold 144 can include replaceable inserts across a width of the manifold.
  • FIG. 4 illustrates a disk 250 that can be utilized in a rotor assembly in accordance with an example of the present disclosure.
  • the disk 250 can include a plurality of fluid guides 251.
  • the fluid guides can have any suitable cross-section such as, but not limited to, airfoil, elliptical, circular, diamond, and the like. However, an airfoil cross-section as illustrated can be particularly effective.
  • the airfoil shape can be symmetric about a longitudinal central axis of the airfoil, in some arrangement.
  • the fluid guides 251 can be arranged in a ring configuration 252a, 252b, and/or 252c across the disk 250.
  • the ring configuration can comprise multiple rings 252a-c concentric about the axis of rotation 201. Although three such rings are illustrated, from about three to about eight rings can often be suitable depending on the size and design operating parameters.
  • a radial relationship of the rings 252a-c can correspond to the Fibonacci ratio (1.61618) or the Golden ratio (1.61803) to maximize the efficiency of the fluid as the fluid follows a spiral flow path along the disk 250.
  • other radial relationships can be used such as equidistant, or ratios of 1.2 to 2, for example.
  • an inclination angle can be adjusted based on desired operating parameters.
  • the inclination angle 254 i.e. an angle between a rotor radius 256 and central longitudinal airfoil axis 258, can be from about 20° to about 75°, and in some cases 30° to 55°.
  • the inclination angle is in the range of 40° to 60°, more specifically 45° to 55°, for example 51.5°, which has been found to result in efficient energy transfer.
  • the inclination angle 254 and the angle 104 arc substantially the same.
  • the number, geometric design, and location of the fluid guides 251 on the disk 250 can be optimized based on the size of the disk, the inlet pressure, and the design speed of rotation of the rotor assembly.
  • a venturi configuration of a partition opening can control the fluid flow between the concentric rings 252a-c. As the rotational velocity of the rotor assembly increases, fluid flow increases towards the center of the disks. At lower rotational velocity, fluid flow tends towards the outer edges of the disks.
  • FIG. 5 illustrates adjacent disks 350a, 350b of a rotor assembly in accordance with an example of the present disclosure oriented to show a gap between the disks.
  • the disks 350a, 350b of a rotor assembly are typically relatively thin (e.g., a thickness 353 of approximately 1.45 mm) and typically have a gap 354 or space between the disks of a distance 355 equal to or less than the disk thickness 353.
  • disk thickness can range from about 0.5 mm to about 5 mm, and in some cases from about 0.8 mm to about 2 mm.
  • the outer edges of the disks 350a, 350b can be tapered by an angle 356 to a thinner edge of small radius to provide a tapered zone that can lessen turbulence and facilitate a smooth transition of fluid flow into or out of the rotor assembly.
  • FIG. 6 illustrates a cross-section of a portion of a rotor assembly 420 in accordance with an example of the present disclosure.
  • the rotor assembly 420 includes a plurality of disks 421 (identified individually as disks 450a-n) that defines a central hollow interior opening 426 along an axis of rotation, which extends through the interior opening.
  • the disks 450a-n include a plurality of spacers 451a-n disposed between adjacent disks to space the disks apart along the axis of rotation to provide gaps 454a-m between the disks.
  • fluid can pass through the gaps 454a-m between the disks 450a-n and the interior opening 426 as the fluid moves through the rotor assembly 420.
  • the disks 450a-n can be permanently coupled to one another by the plurality of spacers 451a-n, such as using an adhesive.
  • the adhesive is a common resin binder used to form the entire assembly, in particular in embodiments where the assembly is formed from a fibre composite material (i.e. composite of fibrous material, for example provided as a felt or other matted material and a resin binder).
  • the discs 450a-n and respective adjacent spacers 451a-n are assembled together before the resin binder is fully cured, so that the resin binder in the discs 450a-n and respective adjacent spacers 451a-n fuses and then fully cures, resulting in some embodiments in a monolithic fiber composite structure.
  • the resin permeates the fibrous material of adjacent layers of the assembly and fuses the entire structure into a monolithic assembly with no discernible interfaces between the layers. Fusing of the resin in adjacent layers and/or the subsequent full curing is facilitated by appropriate timing and/or heat treatment during the manufacturing process.
  • the assembly is manufactured using carbon fibres carbon fiber composite (e.g., TorayTM T800S) and an appropriated resin binder and hardener.
  • the assembly is manufactured using basalt fibres in combination with a suitable resin binder and hardener.
  • An example of basalt fibres used in some embodiments is a weave with weight 6.80z/yds 2 (34g/m 2 ) and fiber thickness 9.8mils (0.25nm).
  • a bismaleimide two-component system such as Matrimid® 5292 A-2 resin and Matrimid ® 5292 B hardener available commercially from Huntsman Corporation, TX, see also US Patent No. 4,100,140 can be used with either carbon or basalt fibres. With no solid central shaft to hold the disks together, this configuration can be termed shaftless.
  • the spacers 451a-n can be integrally formed with the disks 450a-n.
  • no other parts are needed to complete the disk assembly.
  • the spacers 451a-n can have an airfoil configuration and can therefore also serve as fluid guides as discussed above with reference to FIG. 4 .
  • the spacers 451a-n can be configured in accordance with the above description of fluid guides 251.
  • the fluid guides 251 and spacers 451a-n are identical and the disks 450a-n are spaced apart by the fluid guides 251 described above, that is in some arrangements, the spacers 451 a-n are the fluid guides 251.
  • the disks 450a-n can be flat on one side and can have spacers projecting from an opposite side, which can be set out or arranged in a ring configuration as discussed above, for example with reference to the fluid guides 251 and/or Figure 4 .
  • the spacers 451a-n can ensure precise and proper spacing of the disks 450a-n from one another and contribute rigidity to the rotor assembly 420 structure under operating loads by providing multiple, geometrically and radially distributed coupling locations to interlock adjacent disks.
  • the rotor assembly 420 will include from 60 to 200 disks having gap distances of 0.5 mm to 5 mm, although any suitable number and spacing of disks can be utilized. Although the number of disks within a rotor assembly can vary, as a general guideline, from 50 to 500 disks, and in some cases from 75 to 200 disks can be included. In some embodiments, identical disks can be used to construct the entire rotor assembly 420 (including outer end disks), thus simplifying construction.
  • disks of different configurations can be incorporated into the rotor assembly, such as disks having different spacer/fluid guide configurations.
  • a “smooth” disk can be used to "cap” an end of the rotor assembly disks, thus providing smooth exposed disk faces on opposite ends of the rotor assembly.
  • the disks of the rotor assembly can be constructed of lightweight carbon fiber composite material, which can provide a high surface area with less mass compared to typical designs that rely heavily on a "flywheel” effect to preserve momentum, unlike a turbomachine of the present disclosure.
  • FIG. 7 illustrates a cross-section of a portion of a rotor assembly 520 in accordance with another example of the present disclosure.
  • the rotor assembly 520 includes a plurality of disks 521 that define a central hollow interior opening 526 along an axis of rotation, which extends through the interior opening. Accordingly, fluid moving through gaps between adjacent disks can freely enter or exit the interior opening 526 directly from the gaps.
  • the interior opening 526 is also defined at least in part by a helical baffle 527 to facilitate directional flow or movement of fluid through the rotor assembly 520 for venting fluid from the rotor assembly.
  • the helical baffle 527 can be formed by a feature or protrusion on each disk such that when the disks are assembled the baffle is formed with gaps in the baffle between adjacent disks. In other embodiments, the helical baffle 527 can be a separate component added to the disk assembly such that the baffle extends across the gaps between adjacent disks.
  • An extension member 522 is also shown attached to the plurality of disks 521.
  • the extension member 522 can be attached to the plurality of disks 521 using an adhesive, fasteners, or any other suitable substance or device.
  • the extension member 522 can include a flange 523 to interface with the plurality of disks 521 and facilitate coupling with the disks.
  • the extension member 522 also includes a vent port 525 oriented along the axis of rotation.
  • the vent port 525 can extend through the extension member 525 in fluid communication with the interior opening 526 formed by the plurality of disks, thus effectively forming an extension of the interior opening.
  • a diameter of the vent port 525 is illustrated as being different than a diameter of the interior opening 526, it should be recognized that the vent port and the interior opening can have substantially the same diameter to facilitate unrestricted fluid flow between the interior opening and the vent port.
  • the helical baffle optionally extends across an extension member 522.
  • the vent port 525 can be defined at least in part by a helical baffle 528 to facilitate movement of the fluid through the vent port 525.
  • the helical baffle 528 can be a protruding internal surface feature integrally formed with the substrate or included as a separate component.
  • the helical baffles 527, 528 can be continuous through the interior opening 526 and the vent port 525 such that the interfacing ends of the baffles align with one another to maintain the flow or movement of fluid through the rotor assembly 520 for venting fluid from the rotor assembly.
  • interior opening 526 and the vent port 525 are shown with the helical baffles 527, 528, it should be recognized that the interior opening and the vent port can have smooth or featureless boundaries, which can simplify construction of the rotor assembly 520.
  • FIGS. 8A and 8B illustrate a computer model showing the fluid volume in an interior space of a boundary layer turbomachine in accordance with an example of the present disclosure. These figures show fluid in the inlet opening, the outer chamber, the partition openings, the rotor chamber, the interior opening, and the vent port.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (18)

  1. Une turbomachine couche limite (100), comprenant :
    un boîtier (110) délimitant un espace intérieur (115) et doté d'une ouverture d'admission (112, 113, 114) et d'une ouverture de sortie (112, 113, 114) pour faciliter le mouvement d'un fluide à travers le boîtier ;
    un bloc rotor (120, 420, 520) disposé dans le boîtier (110) et configuré pour tourner autour d'un axe de rotation (101), le bloc rotor présentant :
    une pluralité de disques (121, 421, 450, 521) espacés les uns des autres le long de l'axe de rotation et délimitant une ouverture intérieure configurée comme un vide centré sur l'axe de rotation, le fluide passant à travers des interstices (3 54, 454) entre les disques (121, 421, 450, 521) et l'ouverture intérieure (426, 526) quand le fluide se déplace à travers le boîtier, la turbomachine étant configurée de manière à ce qu'un fluide se déplaçant à travers le boîtier soit guidé pour entrer dans ou sortir des interstices au niveau d'une pluralité d'emplacements autour des bords extérieurs des disques ; et
    une partition (130) divisant circonférentiellement l'espace intérieur (115) en une chambre extérieure (116) dotée d'un volume annulaire et une chambre de rotor (117) située radialement vers l'intérieur par rapport à la chambre extérieure, le bloc rotor (120, 420, 520) étant disposé dans la chambre de rotor (117), la partition présentant des ouvertures de partition (131) espacées circonférentiellement autour de la partition (130) de manière à ce que le fluide puisse se déplacer à travers la partition entre la chambre extérieure (116) et la chambre de rotor (117) au niveau de la pluralité d'emplacements, caractérisée en ce qu'une paire d'éléments d'extension (122) couplent le bloc rotor (120, 420, 520) au boîtier (110) et sont configurés pour faciliter la rotation du bloc rotor autour de l'axe de rotation (101), la paire d'éléments d'extension étant attachée à la pluralité de disques en face les uns des autres alignés avec l'axe de rotation, les éléments d'extension comprenant chacun en sus une ouverture pour fluide en communication fluide avec l'ouverture intérieure (426, 526) pour permettre au fluide d'entrer dans ou sortir de l'ouverture intérieure via les ouvertures pour fluide.
  2. La turbomachine couche limite de la revendication 1, dans laquelle l'ouverture d'admission (112, 113, 114) est associée à la chambre extérieure (116) de manière à ce que la chambre extérieure serve de chambre d'expansion pour le fluide.
  3. La turbomachine couche limite de la revendication 1 ou 2, dans laquelle les ouvertures de partition (131) présentent une zone de section transversale tangentielle qui s'agrandit dans une direction radialement vers l'intérieur.
  4. La turbomachine couche limite de la revendication 1 ou 2, dans laquelle les ouvertures de partition (131) comprennent une configuration de venturi.
  5. La turbomachine couche limite d'une quelconque des revendications 1 à 4, dans laquelle les ouvertures de partition (131) sont espacées régulièrement sur la circonférence autour de la partition (130).
  6. La turbomachine couche limite d'une quelconque des revendications précédentes, la turbomachine étant configurée de manière à ce que le fluide traversant le boîtier (110) soit guidé pour entrer dans les interstices (354, 454) au niveau d'une pluralité d'emplacements espacés sur la circonférence autour du bloc rotor (120, 420, 520) selon un angle dans la plage de 40° à 60°, éventuellement 45° à 55°, par exemple 51° ou 52° relativement à un rayon des disques.
  7. La turbomachine couche limite d'une quelconque des revendications précédentes, comprenant en sus un piège à débris (140).
  8. La turbomachine couche limite de la revendication 7, dans laquelle le piège à débris (140) est formé par une rainure le long d'une surface radiale intérieure d'une partie de la partition (130).
  9. La turbomachine couche limite d'une quelconque des revendications 1 to 8, dans laquelle l'ouverture intérieure délimite un trajet d'écoulement de fluide coïncidant avec l'axe de rotation (101).
  10. La turbomachine couche limite d'une quelconque des revendications précédentes, dans laquelle les disques (121, 421, 450, 521) sont espacés les uns des autres par une pluralité d'espaceurs (451) et dans laquelle, de préférence, les espaceurs ont une section transversale profilée.
  11. La turbomachine couche limite de la revendication 10, dans laquelle les disques (121, 421, 450, 521) et les espaceurs (45 1) forment une structure monolithique.
  12. La turbomachine couche limite de la revendication 10 ou 11, dans laquelle les espaceurs (451) sont disposés selon une configuration en anneau à travers chaque disque (121, 421, 450, 521).
  13. La turbomachine couche limite de la revendication 10, 11 ou 12, dans laquelle les espaceurs (451) ont chacun un axe longitudinal (258) qui est orienté selon un angle d'inclinaison (254) par rapport à un rayon du rotor (256) du bloc rotor (120, 420, 520), et l'axe longitudinal de chaque espaceur est disposé selon angle d'inclinaison dans la plage de 40° à 60°, éventuellement 45° à 55°, par exemple 51° ou 52° relativement au rayon de rotor.
  14. La turbomachine couche limite d'une quelconque des revendications précédentes, dans laquelle l'ouverture intérieure (426, 526) délimite un déflecteur hélicoïdal (527) pour faciliter le mouvement du fluide à travers le bloc rotor (120, 420, 520).
  15. La turbomachine couche limite de la revendication 1, dans laquelle le volume annulaire a une dimension radiale intérieure (102) de 80 à 95% d'un rayon (103) de l'espace intérieur (115).
  16. La turbomachine couche limite de la revendication 1, dans laquelle le volume annulaire a une épaisseur radiale constante.
  17. La turbomachine couche limite de la revendication 1, dans laquelle la pluralité de disques (121, 421, 450, 521) comprend de 50 à 500 disques.
  18. Un procédé de fonctionnement de la turbomachine couche limite d'une quelconque des revendications précédentes, le procédé comprenant l'étape consistant à alimenter un mélange de gaz et de liquide à travers la ou les ouvertures d'admission pour entraîner la turbomachine couche limite.
EP15171530.7A 2015-01-09 2015-06-10 Turbomachine à couche limite et procédé de fonctionnement associé Active EP3103961B1 (fr)

Priority Applications (11)

Application Number Priority Date Filing Date Title
EP15171530.7A EP3103961B1 (fr) 2015-06-10 2015-06-10 Turbomachine à couche limite et procédé de fonctionnement associé
US14/991,228 US11208890B2 (en) 2015-01-09 2016-01-08 Boundary layer turbomachine
MX2017016039A MX2017016039A (es) 2015-06-10 2016-06-10 Turbomaquina de capa limite, unidad de rotor y particion correspondientes.
AU2016276259A AU2016276259A1 (en) 2015-06-10 2016-06-10 Boundary layer turbomachine, corresponding rotor assembly and partition
CN201680043992.3A CN109983202A (zh) 2015-06-10 2016-06-10 边界层涡轮机、对应的转子组件和隔板
PCT/IB2016/001360 WO2016198962A2 (fr) 2015-06-10 2016-06-10 Turbomachine couche limite
JP2018516648A JP2018521268A (ja) 2015-06-10 2016-06-10 境界層ターボ機械、対応するロータ組立体及び隔壁
KR1020187000709A KR20180098215A (ko) 2015-06-10 2016-06-10 경계층 터보기계
US15/735,510 US20200256191A1 (en) 2015-06-10 2016-06-10 Boundary layer turbomachine
CA2989093A CA2989093A1 (fr) 2015-06-10 2016-06-10 Turbomachine couche limite
PH12018500094A PH12018500094A1 (en) 2015-06-10 2018-01-10 Boundary layer turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15171530.7A EP3103961B1 (fr) 2015-06-10 2015-06-10 Turbomachine à couche limite et procédé de fonctionnement associé

Publications (2)

Publication Number Publication Date
EP3103961A1 EP3103961A1 (fr) 2016-12-14
EP3103961B1 true EP3103961B1 (fr) 2019-11-06

Family

ID=57234800

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15171530.7A Active EP3103961B1 (fr) 2015-01-09 2015-06-10 Turbomachine à couche limite et procédé de fonctionnement associé

Country Status (1)

Country Link
EP (1) EP3103961B1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4118339A4 (fr) * 2020-04-15 2023-10-11 Kin-Chung Ray Chiu Pompe à vide sans joints dotée de surface d'impact de gaz sans pales à rotation supersonique

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3062156B1 (fr) * 2017-01-24 2021-01-29 Bernard Etcheparre Turbine centrifuge a disques a effet de bord et a aubes rapportees

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1061142A (en) 1909-10-21 1913-05-06 Nikola Tesla Fluid propulsion
CH615935A5 (fr) 1975-06-19 1980-02-29 Ciba Geigy Ag
US4534699A (en) * 1983-06-22 1985-08-13 Possell Clarence P Coal fired turbine
GB2226081A (en) * 1988-12-14 1990-06-20 Rolls Royce Plc Fluid friction pump or turbine
US7341424B2 (en) * 1999-12-23 2008-03-11 Dial Discoveries, Inc. Turbines and methods of generating power
US7192244B2 (en) * 2004-02-23 2007-03-20 Grande Iii Salvatore F Bladeless conical radial turbine and method
US7695242B2 (en) * 2006-12-05 2010-04-13 Fuller Howard J Wind turbine for generation of electric power

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4118339A4 (fr) * 2020-04-15 2023-10-11 Kin-Chung Ray Chiu Pompe à vide sans joints dotée de surface d'impact de gaz sans pales à rotation supersonique

Also Published As

Publication number Publication date
EP3103961A1 (fr) 2016-12-14

Similar Documents

Publication Publication Date Title
US11208890B2 (en) Boundary layer turbomachine
US7600961B2 (en) Fluid transfer controllers having a rotor assembly with multiple sets of rotor blades arranged in proximity and about the same hub component and further having barrier components configured to form passages for routing fluid through the multiple sets of rotor blades
JP6005139B2 (ja) ターボ・エンジン、特に内燃機関
JP5625117B2 (ja) 反作用式タービン
EP2264281B1 (fr) Dispositif anti-vortex pour compresseur de moteur à turbine à gaz
EP3103962A1 (fr) Rotor pour turbomachine à couche limite et une telle turbomachine
CA2707226A1 (fr) Compresseur supersonique comprenant un trajet d'ecoulement radial
EP3103961B1 (fr) Turbomachine à couche limite et procédé de fonctionnement associé
US7241106B2 (en) Combined cycle boundary layer turbine
CN108930557A (zh) 用于压缩机导叶前缘辅助导叶的方法及系统
EP3510250B1 (fr) Turbomachine à couche limite
CN102182517B (zh) 带叶盘式附面层透平
JP2018523049A (ja) 反動型蒸気タービン
JP6823649B2 (ja) せん断流ターボ機械装置
EP3307987A2 (fr) Turbomachine couche limite
AU2016291301B2 (en) Tubular adhesion turbine or pump
WO2014120123A2 (fr) Coiffe thermoplastique pour un moteur de turbine
CA2426906A1 (fr) Statoreacteur rotatif

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20170614

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20171128

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: GREEN FROG TURBINES (UK) LIMITED

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20190123

RIN1 Information on inventor provided before grant (corrected)

Inventor name: HELTON, BILL

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: AT

Ref legal event code: REF

Ref document number: 1198963

Country of ref document: AT

Kind code of ref document: T

Effective date: 20191115

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602015040963

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20191106

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200207

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200206

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200306

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200206

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200306

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602015040963

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1198963

Country of ref document: AT

Kind code of ref document: T

Effective date: 20191106

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20200807

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 602015040963

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20200610

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200610

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20200630

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200630

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200610

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200610

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200630

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200630

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210101

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200630

REG Reference to a national code

Ref country code: GB

Ref legal event code: S28

Free format text: APPLICATION FILED

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191106

REG Reference to a national code

Ref country code: GB

Ref legal event code: S28

Free format text: RESTORATION ALLOWED

Effective date: 20220805

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20230921

Year of fee payment: 9