WO2018094444A1 - Rotor à flux inverse (rf) - Google Patents

Rotor à flux inverse (rf) Download PDF

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Publication number
WO2018094444A1
WO2018094444A1 PCT/AU2017/000248 AU2017000248W WO2018094444A1 WO 2018094444 A1 WO2018094444 A1 WO 2018094444A1 AU 2017000248 W AU2017000248 W AU 2017000248W WO 2018094444 A1 WO2018094444 A1 WO 2018094444A1
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WO
WIPO (PCT)
Prior art keywords
rotor
reverse flow
flow rotor
gas turbine
flow
Prior art date
Application number
PCT/AU2017/000248
Other languages
English (en)
Inventor
Warren Day
James Kim
Alexander Wright
Original Assignee
EcoJet Engineering Pty 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
Priority claimed from AU2016904814A external-priority patent/AU2016904814A0/en
Application filed by EcoJet Engineering Pty Ltd filed Critical EcoJet Engineering Pty Ltd
Publication of WO2018094444A1 publication Critical patent/WO2018094444A1/fr

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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
    • F01D1/32—Non-positive-displacement machines or engines, e.g. steam turbines with pressure velocity transformation exclusively in rotor, e.g. the rotor rotating under the influence of jets issuing from the rotor, e.g. Heron turbines
    • 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
    • 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
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F02C3/16—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant
    • F02C3/165—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant the combustion chamber contributes to the driving force by creating reactive thrust

Definitions

  • This invention relates to a fluid flow machine having at least one rotor containing internal flow channels for a flow medium to travel through, which does work on or extracts work from a fluid.
  • fluid flow machines include, but are not limited to, gas turbines, turbochargers, compressors, pumps and hydro turbines.
  • Rotors used in fluid flow machines are known to be of two configurations.
  • the first in which flow r both enters and exits the rotor in the axial direction resulting in no significant change in overall flow direction, otherwise known as axial type rotors.
  • This first configuration axial type rotors, were and still are predominantly used in aircraft propulsion applications to produce thrust. This configuration is ideal for thrust applications due to no significant change in fluid flow direction, resulting in minimal loss of fluid flow momentum.
  • centrifugal or radial flow rotors are most commonly utilised in small compact machines as they can impose or extract more energy from a working fluid per single stage.
  • the internal channels of centrifugal or radial flow rotors change the direction of absolute flow by 90 degrees, transferring energy through this diversion, as well as incorporating centrifugal forces as the internal channels contain flow paths in the radial direction.
  • Centrifugal rotors were initially used in aircraft applications, however currently they are found in many applications that incorporate fluid to either be accelerated or to drive another component.
  • Some current applications of centrifugal type rotors include micro gas turbines, turbochargers, compressors and pumps. These types of rotors can be used for both centrifugal flow, i.e. flowing from the inner radius to the outer radius, and centripetal flow, i.e.
  • Centrifugal flow is generally utilised for a compressor application as the centrifugal flinging force generated by the rotation of the rotor is partially what draws the fluid through the rotor.
  • Centripetal flow is generally utilised for a turbine application as the intake, being located at the outer radii, produces a larger moment or torque on the rotor.
  • rotors used in fluid flow machines have also been suggested to have both the intake and exit openings of said channels being located on the same axial surface of a rotor.
  • Each intake and exit opening are radially spaced at different predetermined distances from the axis of rotation.
  • Each flow channel aligning with a flow diverter having a first radially outer and a second radially inner deflector elbows both sequentially redirecting fluid flow through an angle of 90 degrees each.
  • the first elbow being the intake opening and opening in the direction of the relative velocity of the intake flow of the fluid, and the second elbow leading to the respective exit opening and opening in the direction of the relative velocity of the exiting fluid flow.
  • the first and second elbows are joined by a linear conduit to thereby form a U-shaped conduit.
  • MGT's A particular type of fluid flow machine known as micro gas turbines or MGT's, are a major application of such fluid flow rotors and are essentially small scale power generation devices.
  • MGT's generally utilise at least two fluid flow rotors; one rotor is used as a compressor rotor to accelerate and compress the fluid, which then enters a combustion chamber to further energise the flow.
  • Another rotor is used as a turbine rotor to extract energy from the highly energised fluid flow leaving the combustion chamber, which is used to drive the compressor and any other auxiliary components. All of these rotors are generally attached to a common shaft. The extracted energy is in the form of rotational kinetic energy, which can be then converted into electrical energy via a generator.
  • Generators used in MGT applications are known to be of the permanent magnet type, consisting of a stator and rotor, where the rotor component is attached to the rotating shaft of the MGT. These generators can be utilised as both a generator and starter motor, that being when electricity is applied to the generator, it acts as a starter motor to cause rotation of the rotor to initially drive the rotating components within the MGT up to a suitable speed to self-sustain combustion. When the MGT is already self-sustaining combustion and generating high rpm, electricity applied to the generator can be stopped and it can now be driven by the MGT to generate electricity, acting as a generator.
  • the total efficiency of an MGT unit can be broken down into the sum of the efficiencies of each individual component comprised of generally the combustor, rotors and generator. Centrifugal type rotors are the most common choice in MGT's as they are currently known to impose or extract the most energy per single stage. The maximum base total thermal efficiency of MGT's, without utilising any waste heat, are currently restrained to around the low-to-mid 30% mark.
  • the majority of current MGT technologies are derived directly from jet engines used for aircraft propulsion applications, which are ideal for producing thrust, however the nature of MGT's are to generate electrical energy via a generator that requires high torque not thrust. This ineffective adaption of a thrust-designed device is partially why base total thermal efficiencies of MGT's are so low.
  • the invention is a reverse flow rotor for use in a rotary fluid flow machine having:
  • a shaft on the rotor body to mount the rotor body and shaft in a fluid flow machine so that the rotor body and shaft can rotate within the fluid flow machine
  • the invention improves upon a rotary fluid flow machine of the type set forth in the introduction so as to increase energy transfer and efficiency between a rotor and working fluid.
  • the invention provides that both the intake and exit openings are on the same axial side of a rotor, with each intake opening and its associated exit opening being located at different radii distances from the axis of rotation, and each intake and associated exit opening being joined via a fluent
  • the flow channels connecting each intake and respective exit opening are fonned in such a manner that their intake openings are located on the same side as the exit openings. This provides a total change in absolute flow direction of approximately 1 80 degrees from one point to another on the rotor, such that the direction of flow exiting the rotor is approximately in the opposite direction of the flow entering the rotor.
  • the invention also provides that the intake or exit openings may, at the outer radii, be located on an angled face with deviation angle from the axial side between 0 - 60 degrees, such that 0 degrees being parallel to the axial face and 60 degrees having the greatest deviation angle from the axial face. This provides an approximate total change m absolute flow direction between 180 - 120 degrees. Having the intake or exit opening, at the outer radii, being located at an angled face can provide the working fluid flow at that location with an additional component of flow velocity to impose or extract a greater rotational force.
  • the fluid flow path may also be comprised of a combination of axial components and a radial component.
  • fluid flowing through the initial axial section of the inlet passage and the final axial section of the exit passage is travelling predominantly in the axial direction.
  • the fluid flowing through these axial sections imparts rotational force on the rotor, essentially functioning as a partial axial-type rotor.
  • the rotor's axial face surface from the axial view it is seen that each inlet and associated exit opening is separated by a radial distance.
  • Fluid flowing through the predominantly radial section of the internal passages contains a notable radial component of fluid flow velocity imparting a centrifugal or centripetal force on the rotor, depending on the desired direction of fluid flow throughout the rotor, essentially functioning as a partial centrifugal or radial flow type rotor.
  • This combination of axial and radial forces allows for increased energy transfer to occur within the rotor.
  • the invention also provides that the internal flow channels each follow a fluent three-dimensional path, following that of, but not restricted to, an elliptical path that spirals partially around the rotor centre of rotation, from one intake opening to their associated exit opening.
  • a fluent three-dimensional path following that of, but not restricted to, an elliptical path that spirals partially around the rotor centre of rotation, from one intake opening to their associated exit opening.
  • the invention provides that two or more of the above described rotors be securely fitted to a common shaft.
  • at least one rotor serves for compression of the flow medium and at least one other rotor serves for expansion of the flow medium, this configuration allows for the difference in power required for compression and the power generated via expansion to be transmitted via the shaft as usable power.
  • This embodiment may or may not also consist of a combustion chamber, to be located aft of compression and before expansion of the flow medium, to raise the energy of the fluid medium prior to energy extraction.
  • This configuration is suitable for any drive mechanism requiring synchronous operation of turbine and compressor rotors, such that they are rotating at the same rotational speed on a common shaft, such as gas turbine generators, automotive turbochargers, and gas turbine propeller/shaft engines.
  • This configuration results in high torque output, rather than thrust, therefore favouring applications utilising a drive mechanism, such as a generator for example.
  • the invention provides that at least one of said rotors be securely fitted to a shaft that is attached directly to an electric motor or generator. Provided the rotor or rotors serves for either compression of the flow medium, or expansion of the flow medium, this configuration results in an independent compressor pump or turbine generator, respectively.
  • This configuration when utilised as an electric motor driven compressor, is desirable for any application that requires a fluid medium to be pumped or compressed without the use of a combustor.
  • This configuration when utilised as a turbine generator, is desirable for any application that intends to generate electricity via a shaft driven generator when pre-energised flow is already available.
  • FIG. 1 shows a radial sectional view of a gas turbine generator configuration comprising a first embodiment of the invention, where the drawing is sectioned to show the second stage compressor intake passage.
  • FIG. 2 shows another radial sectional sliced view of the gas turbine generator configuration in
  • FIG. 1 where the drawing is sectioned to show the combustion chamber intake passage.
  • FIG. 3 shows another radial sectional sliced view of the gas turbine generator configuration in FIG. 1 where the drawing is sectioned to show the turbine exhaust passage.
  • FIG. 4 shows another radial sectional sliced view of the gas turbine generator configuration in FIG. 1 where the drawing is sectioned to show secondary multi stage axial-type turbine rotors.
  • FIG. 5 shows a partial axial or front view of a rotor designed for centrifugal flow of a fluid fl ow machine utilised in the first embodiment of the invention with the configuration of both intake and exit openings located on the same axial side of the rotor.
  • FIG. 6 shows a partial radial sectional view of the rotor along line V-V in FIG. 4.
  • FIG. 7 shows a partial internal sectional view of the rotor along line VI- VI in FIG. 6.
  • FIG. 8 shows an isometric view of the rotor designed for centrifugal flow in FIG. 4.
  • FIG. 9 shows a partial axial or front view of a rotor designed for centripetal flow of a fluid flow machine utilised in the first embodiment of the invention with the configuration of both intake and exit openings located on the same axial side of the rotor.
  • FIG. 10 shows a partial radial sectional view of the rotor along line IX - IX in FIG. 9.
  • FIG. 1 1 shows an isometric view of the rotor designed for centripetal flow in FIG. 9.
  • FIG. 12 shows a sectional view of a turbocharger configuration comprising a compressor rotor as seen in FIG. 4 and a turbine rotor as seen in FIG. 8 attached to a common shaft, comprising a second embodiment of the invention.
  • FIG. 13 shows a sectional view of a motor driven pump or compressor comprising a compressor rotor as seen in FIG. 4 attached to a motor via a shaft, comprising a third embodiment of the invention.
  • FIG. 14 shows a sectional view of an independent turbine generator comprising a turbine rotor as seen in FIG. 8 attached to a generator via a shaft, comprising a forth embodiment of the invention.
  • FIG. 15 shows a sectional view of a rotor designed for centripetal or centrifugal flow of a fluid machine to be utilised in the first embodiment of the invention with the alternative configuration of only intake or exit opening located on the axial side and its respective exit or intake opening located at an angled face.
  • FIGS. 1 , 2 and 3 show a fluid flow machine according to the invention comprising a first embodiment of a micro gas turbine 1.
  • This preferred embodiment comprises the integration and configuration of key components including a reverse-flow compressor rotor 2 and a reverse- flow turbine rotor 3, as well as several other intermediating components necessary for a micro gas turbine.
  • This preferred embodiment comprises of common shaft 4 that has attached to it a first stage centrifugal-type compressor rotor 6, a second stage reverse-flow compressor rotor 2, a reverse-flow turbine rotor 3 and an electric generator/starter motor 5.
  • This shaft 4 is restrained to pure rotation by a front bearing 14 and back bearing 15.
  • These bearings are preferable, but not limited to, air bearings for minimal friction.
  • the outer stators of these bearings are securely attached to front and rear bearing housings 16 and 17 respectively.
  • the first stage centrifugal-type compressor rotor blades 21 can also be seen and are located all throughout the internal channels 18 of the rotor 6.
  • a flow bypass manifold 8 Situated between the second stage reverse-flow compressor rotor 2 and reverse-flow turbine rotor 3 is a flow bypass manifold 8, a combustion chamber 7, exhaust flow channels 10 and a turbine inlet and exit stator plate 9 with guide vanes 22 being located all throughout the channels.
  • the combustion chamber contains igniters 23 located at the inlet of the combustion chamber. All components are housed within an outer tubular casing 20. In between the outer casing 20 and the turbine rotor 3, turbine stator plate 9 and combustion chamber 7 are cold air flow channels 19.
  • FIG. 1 is a second stage reverse-flow compressor intake channel 1 1 , located within a flow bypass manifold 8.
  • FIG. 2 is a combustion chamber intake channel 12, located within a flow bjfpass manifold 8.
  • Visible in FIG. 3 is an exhaust flow exit nozzle 13, located within a flow bypass manifold 8.
  • Ambient air is drawn into the micro gas turbine 1 through a first stage compressor rotor 6 in the direction represented by local arrows A.
  • the rotor blades 21 are located within and towards the entrance of the internal channels 1 and act to compress and do work on the fluid intake when rotating at speed.
  • Partially compressed air flows axially through the micro gas turbine along cold air flow channels 1 , located at the outer perimeters of the gas turbine, all the way to a flow bypass manifold 8. This air is then drawn into a second stage reverse-flow compressor rotor, for further compression, after passing through its intake channels 1 1 within the flow bypass manifold 25.
  • Compressed air then enters a combustion chamber 7 after passing through its intake channels 12 within the flow bypass manifold 8. Fuel is fed into the combustion chamber 7 through multiple small holes located at each ignitor 23. Compressed air enters the combustion chamber 7, spiralling as it does due to the tangential component of flow velocity leaving the reverse-flow rotor 2, to effectively mix with the fuel, just before each ignitor 23 ignites the air fuel mixture as it passes. The combusted flow then expands throughout the combustion chamber 7 and is directed axially towards a reverse-flow turbine 3.
  • the highly energised combustion flow first enters a turbine stator plate 9 where the velocity is increased and the orientation of combustion flow is redirected to optimal angles to impose maximum rotational force on the turbine rotor 3, without jeopardising the structural integrity or allowing flow slippage. This is achieved by the use of converging guide vanes 22 that are located all throughout the passages of the stator plate 9. Now the highly energised combustion flow enters the turbine rotor 3, where it expands throughout the rotor and energy is extracted. Operation of a reverse- flow turbine rotor 3 will be further described in a later section.
  • the energy extracted by the turbine is transferred to a shaft 4 in the form of rotational kinetic energy, which then drives all the other attached components including the first stage centrifugal-type compressor rotor 6, a second stage reverse-flow compressor rotor 2 and an electric generator 5.
  • Exhaust flow leaving the turbine rotor 3 passes through the turbine stator plate 9 again and travels axially down the micro gas turbine through exhaust flow channels 10 to the flow bypass manifold 8.
  • the exhaust flow exits the micro gas turbine unit through exhaust flow exit nozzles 13 within the flow bypass manifold 8 in the direction represented by local arrows B.
  • this preferred embodiment of a micro gas turbine 1 has the capacity for further energy extraction via multiple methods as the exhaust flow leaving the turbine rotor 3 may still contain a considerable amount of unharvested energy.
  • One of such possible methods would be to incorporate secondary multi stage axial-type turbine rotors 35 all throughout the exhaust flow channels 10, as graphically represented in FIG. 4, to extract further energy in the form of rotational kinetic energy, from the exhaust flow leaving the turbine rotor 3 before it exits the micro gas turbine unit.
  • Other possible methods could involve extracting further energy from the exhaust flow after it exits the micro gas turbine unit by utilising the heat energy still contained within the exhaust flow.
  • Some possible examples of the later method could include using the heat of the exhaust flow to drive an external steam turbine, be utilised for heating of a building's hot water supply or to drive any external device requiring heat as a driver or catalyst.
  • FIGS. 5, 6, 7 and 8 show a component 24 of the first embodiment of a micro gas turbine 1 , being a reverse- flow type rotor 2 to be used as a compressor or pump.
  • the rotor 2 is attached to a shaft 4.
  • FIG. 6 shows a partial radial cross section of the rotor 2, cut along line V-V from FIG. 5.
  • FIG. 7 shows a partial cross section of the internal flow channels 27, cut along line VI-VI from FIG. 6.
  • Rotor 2 has, but is not restricted to, ten flow channels 27 for fluid flow although only one of the channels is shown in FIGS. 5 and 6.
  • the number of flow channels 27 is related to the required size of flow channel cross sectional areas, the rotor diameter and rotor height.
  • Flow channels 27 have intake openings 25 and exit openings 26.
  • Each flow channel 27 is separated from adjacent flow channels 27 by internal walls 28 that extend along the length of the channels 27. As seen in Fig 5, walls 28 are between adjacent flow channels 27 where an opening 25 has adjacent openings 25' and 25" and the opening 26 has adjacent openings 26' and 26". Walls 28 are formed between adjacent openings 25 and 26 comprising the internal surfaces 41 and internal surfaces 40 and 42 of adjacent flow channels 27.
  • the walls 28 are shaped to in effect act as a blade, either of a turbine or compressor.
  • the walls 28 are radially angled and curved so as to provide a reacting force, either to or from the fluid.
  • the internal flow channel walls 29 follow a fluent curvature into the rotor, defining the passage of the flow channels in the axial orientation.
  • the intake openings and exit openings are located along annuli concentric with the axis of shaft 4 at mean radii r and R respectively, with r being smaller than R.
  • intake openings 25 are located on the same front axial side 30 of the rotor 2 as exit openings 26, the back axial side 31 in the shown component having neither intake nor exit openings.
  • the radial dimension of the intake openings 25 is larger than that of the exit openings 26, while their circumferential dimension is smaller. This results in a substantially trapezoidal shape of the intake openings and a narrower slotted shape of the exit openings.
  • Each intake opening 25 communicates with its associated exit opening 26 through the respective flow channels 27 within rotor 2.
  • the internal walls 29 of these flow channels 27 follow fluent elliptical curves, as seen in FIG. 6, for the particular shown component 24.
  • arrow A shows the intake flow direction
  • arrow B shows the ex t flow direction, indicating that the rotor is designed for centrifugal fluid flow.
  • Fluid is drawn into intake openings 25 by rotor walls 28, which extend along the length of the rotor's internal channels 27, doing work on the fluid by rotating at high speeds and essentially pushing the fluid along with the blade surface area.
  • the fluid flow is accelerated through converging flow channels 27 and then leaves the rotor through exit openings 26.
  • FIGS. 9, 10 and 1 1 show a component 24 of a first embodiment of a micro gas turbine 1 , being a reverse- flow type rotor 3 designed to be utilised as a turbine.
  • the rotor 3 is attached to a shaft 4.
  • FIG. 10 shows a partial radial cross section of the rotor 3, cut along line IX-IX from FIG. 9. Since rotor 3 differs slightly from rotor 2 only in slight certain details, only such differences shall be discussed, reference being had for the remainder to the description of rotor 2. Identical parts are designated by the same reference numerals.
  • Rotor 3 is designed for centripetal flow through the flow channels.
  • the intake and exit openings of the flow channels are also formed on a common axial side 30 of the rotor.
  • the internal walls 29 of the flow channels 27 follow fluent elliptical curves with internal walls 28 being located all throughout the internal flow channels 27, as seen particularly in FIG. 10, for the shown component.
  • these internal walls 28 also act as the common walls between adjacent flow channels 27.
  • the intake openings 26 and exit openings 25 have effectively switched locations, such that the intake openings 26 are located at a larger radial distance R from the axis of rotation than the exit openings 25.
  • arrow A shows the intake flow direction at the outer radii
  • arrow B shows the exit flow direction at the inner radii, indicating that the rotor is designed for centripetal flow.
  • Energised fluid flow is directed into the intake openings 26 and flows through diverging flow channels 27 where the flow decelerates whilst also applying force against the rotor walls 28, which extend along the length of the rotor's internal channels 27, doing work on the rotor 3 causing rotation to high speeds.
  • the decelerated flow then leaves the rotor through exit openings 25.
  • the fluid flowing through rotor 3 is deflected radially by approximately 180 degrees, similar to that of rotor 2. That is, arrow B points in a direction opposite to that of arrow A. This configuration has particular benefits for applications used for the purpose of energy extraction, such as a turbine.
  • This configuration results in a very large change in flow momentum to occur within the rotor, as a 1 0 degree change in flow direction results in the flow velocity vector to exit in the opposite direction of the intake velocity vector.
  • the force due to change in momentum or impulse of the flow is directly imposed onto the rotor, as there is a tangential component of the flow velocity present, the energy transfer that occurs within the rotor is extracted in the form of rotational kinetic energy and generates high torque.
  • the particular rotor shown in FTGS. 9, 10 and 1 1 also has an increased number of flow channels 27, compared to that of the first rotor, however this particular number of flow channels 27 is not a requirement, since as previously mentioned for rotor 2, the number of flow channels 27 is related to the required size of flow channel cross sectional areas, the rotor diameter and rotor height.
  • FIG. 12 shows a fluid flow machine according to the invention comprising a second embodiment of a synchronous drive configuration 32 designed to be possibly utilised as a turbocharger or any other turbine driven pump device.
  • the second embodiment comprises of previously described components of the first embodiment, only details of the modified arrangement of components shall be discussed, reference being had for the remainder to the description of the first embodiment. Identical parts are designated by the same reference numerals.
  • the embodiment shown in FIG. 12 comprises a reverse-flow compressor rotor 2 and a reverse-flow turbine rotor 3, both of which are attached to a common shaft 4.
  • Energised fluid flow which may be in the form of exhaust flow from another system, enters a turbine rotor 3 through its intake openings 26, in the direction represented by local arrow A and exits through its exit openings 25, in the direction represented by local arrow B.
  • Energy extracted through rotor 3 is transmitted through a shaft 4 in the form of rotational kinetic energy and in turn drives a compressor rotor 2.
  • Rotor 2 draws in fluid flow through its intake openings 25, in the direction represented by local arrow A and exits through its exit openings 26, in the direction represented by local arrow B.
  • the energised fluid flow exiting rotor 2 can then be redirected to wherever required to meet its intended use.
  • FIG. 13 shows a fluid flow machine according to the invention comprising a third embodiment of a motor driven compressor or pump configuration 33 designed to be possibly utilised as an electric turbocharger or any other motor driven compressor or pump device.
  • the third embodiment comprises of previously described components of the first embodiment, only details of the modified arrangement of components shall be discussed, reference being had for the remainder to the description of the first embodiment. Identical parts are designated by the same reference numerals.
  • This embodiment shown in FIG. 13 comprises of a reverse-flow compressor rotor 2 attached to a shaft 4, which is attached to or is an integral component of an electric motor 5.
  • This motor possibly of a permanent magnet type, takes in electrical power to drive a shaft 4, which rotates a compressor rotor 2.
  • Fluid flow is then drawn into a rotor 2 through its intake openings 25, in the direction represented by local arrow A and exits through its exit openings 26, in the direction represented by local arrow B.
  • the energised fluid flow exiting rotor 2 can then be redirected to wherever required to meet its intended use.
  • FIG. 14 shows a fluid flow machine according to the invention comprising a forth embodiment of a turbine driven generator configuration 34 designed to be possibly utilised for extracting energy from combustion flow, steam, exhaust flow, water flow, air flow or any other energised fluid mediums.
  • the forth embodiment simply comprises of previously described components of the first embodiment, only details of the arrangement of components shall be discussed, reference being had for the remainder to the description of the first embodiment. Identical parts are designated by the same reference numerals.
  • FIG. 14 comprises of a reverse-flow turbine rotor 3 attached to a shaft 4, which is attached to or is an integral component of an electric generator 5.
  • Energised flow enters a rotor 3 through its intake openings 26, in the direction represented by local arrow A and exits through its exit openings 25, in the direction represented by local arrow B.
  • Energy from the fluid is extracted by a turbine rotor 3 in the form of rotational kinetic energy, which is transferred to a shaft 4 that then drives a generator 5.
  • This generator possibly of a permanent magnet type, then generates electricity that can be redistributed to wherever required to meet its intended use.
  • Figure 15 shows an alternative embodiment of the rotor 3.
  • both intake and exit openings 25 and 26 are on the same axial side of the rotor 3, the intake opening 25 is located on an angled face 35 with deviation angle from the axial side between 0 - 60 degrees, such that 0 degrees being parallel to the axial face 30 and 60 degrees having the greatest deviation angle from the axial face 30.
  • the stators 8 and 9 would have faces that are also angled so as to mate with the angled surfaces of the rotor 3.

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

Abstract

La présente invention concerne une machine à écoulement de fluide, et un rotor associé. Selon un aspect, le rotor contient des canaux d'écoulement internes pour un milieu d'écoulement à traverser, qui travaille sur ou qui extrait un travail à partir d'un fluide. Des exemples de machines à écoulement de fluide comprennent, entre autres, des turbines à gaz, des turbocompresseurs, des compresseurs, des pompes et des hydroturbines. Selon un autre aspect, l'invention concerne un rotor à écoulement inverse comprenant un corps de rotor, un arbre sur le corps de rotor pour monter le corps de rotor et l'arbre dans une machine à écoulement de fluide de telle sorte que le corps de rotor et l'arbre peuvent tourner à l'intérieur de la machine d'écoulement de fluide, une pluralité d'ouvertures d'admission et de sortie espacées radialement autour d'un côté du corps de rotor, et situées sur un trajet d'écoulement de fluide reliant chaque ouverture d'admission à une ouverture de sortie, le trajet d'écoulement de fluide étant incurvé de façon continue entre l'ouverture d'admission et l'ouverture de sortie.
PCT/AU2017/000248 2016-11-23 2017-11-23 Rotor à flux inverse (rf) WO2018094444A1 (fr)

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AU2016904814 2016-11-23
AU2016904814A AU2016904814A0 (en) 2016-11-23 Reverse-flow (rf) rotor

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB758364A (en) * 1953-09-29 1956-10-03 Bachl Herbert Improvements in or relating to fluid flow machines for elastic working media
US4029431A (en) * 1974-08-23 1977-06-14 Herbert Bachl Fluid-flow machine
US4278397A (en) * 1978-05-16 1981-07-14 Getwent Gesellschaft Fur Technische Und Wissenschaftliche Energieumsatzehtwicklungen M.B.H. Fluid flow machine
US20110164958A1 (en) * 2010-01-05 2011-07-07 Saitoh Takeo S Centrifugal reverse flow disk turbine and method to obtain rotational power thereby
EP3032068A1 (fr) * 2014-12-12 2016-06-15 United Technologies Corporation Moteur de turbine à gaz à flux primaire inversé

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB758364A (en) * 1953-09-29 1956-10-03 Bachl Herbert Improvements in or relating to fluid flow machines for elastic working media
US4029431A (en) * 1974-08-23 1977-06-14 Herbert Bachl Fluid-flow machine
US4278397A (en) * 1978-05-16 1981-07-14 Getwent Gesellschaft Fur Technische Und Wissenschaftliche Energieumsatzehtwicklungen M.B.H. Fluid flow machine
US20110164958A1 (en) * 2010-01-05 2011-07-07 Saitoh Takeo S Centrifugal reverse flow disk turbine and method to obtain rotational power thereby
EP3032068A1 (fr) * 2014-12-12 2016-06-15 United Technologies Corporation Moteur de turbine à gaz à flux primaire inversé

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