WO2015019294A1 - Procédé de génération d'énergie mécanique, turbine à flux unique et turbine à double flux, et appareil turboréacteur associé - Google Patents

Procédé de génération d'énergie mécanique, turbine à flux unique et turbine à double flux, et appareil turboréacteur associé Download PDF

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Publication number
WO2015019294A1
WO2015019294A1 PCT/IB2014/063718 IB2014063718W WO2015019294A1 WO 2015019294 A1 WO2015019294 A1 WO 2015019294A1 IB 2014063718 W IB2014063718 W IB 2014063718W WO 2015019294 A1 WO2015019294 A1 WO 2015019294A1
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Prior art keywords
flow
jet
double
centrifugal
collector
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PCT/IB2014/063718
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English (en)
Inventor
Sergei Konstantinovich Isaev
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GITA DMITRI GEORGIEVICH
SHRAMKO ANDREY VALER'EVICH
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GITA DMITRI GEORGIEVICH
SHRAMKO ANDREY VALER'EVICH
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Publication of WO2015019294A1 publication Critical patent/WO2015019294A1/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
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/06—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially radially
    • 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
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/08—Adaptations for driving, or combinations with, 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

Definitions

  • the invention relates to mechanical engineering, in particular to air- driven, gas-driven and steam-driven turbines for driving electrical power generators, propulsion systems, refrigeration compressors, and heat pumps.
  • Utility model patent RU99540 discloses a turbine comprising a rotor with nozzles arranged in an equally spaced manner around the circumference, a stator with blades, and a supercharger located at the inlet into the turbine body; said elements being provided in order to increase the turbine efficiency.
  • the primary disadvantage of such turbine is low efficiency due to significant pressure loss in both the working medium flow entering the turbine (due to complicated and suboptimal flow duct configuration at a section including an inlet, output and passages of a centrifugal supercharger, passages and blades of stationary distributor, and passages and blades of rotating distributor) which fails to provide sufficient working medium compression in the rotor pocket, and in the working medium flow exiting the turbine (due to simplified and suboptimal nozzle configuration, since the nozzles are tapered, sonic and reducing, thus failing to expel the working medium from the turbine at supersonic rate).
  • the working medium flow entering the turbine flows around the rotating outer surface of the supercharger, thus changing direction at an angle close to 180°, which leads to a significant pressure loss in the flow.
  • the working medium flow exits the supercharger along the rotational axis of the supercharger, rather than radially, which also leads to a substantial decrease in working medium flow compression therein.
  • the blades of the stationary distributor and the blades of the rotating distributor further contribute to pressure loss in the working medium flow. Therefore, considering relatively narrow diameter of the supercharger, the compression rate of the working medium flow in the turbine is low.
  • the closest prior art for the present invention is a method for producing mechanical energy in a turbine, and a turbine therefor (RU 2200848, F01 D1/32, 11.03.2002) .
  • the prior art method for producing mechanical energy in a turbine comprising a Segner wheel includes supplying a working medium into passages of a turbine rotor and then accelerating the working medium exiting from the passages in one direction perpendicular to the rotor radius so as to rotate the rotor.
  • the working medium is expelled from these passages into the space around the rotor, wherein the space is defined by a jacket.
  • the working medium frictionally interacts with the jacket, and exits through openings in the jacket so as the working medium is accelerated in one direction to rotate the jacket.
  • the space around the rotor as defined by the jacket is enclosed circumferentially along the outlet openings of the rotor passages.
  • a turbine comprises
  • a Segner wheel formed by a tube with a closed end attached to a shaft in a coaxial manner, wherein the turbine is adapted to rotate on the tube,
  • axes of deflected open ends of tube assemblies are arranged perpendicularly to a plane passing through axes of tube assemblies and the axis of the tube, and openings aligned with the tube assemblies are provided in the tube wall;
  • a housing enclosing the Segner wheel and the jacket, said housing provided with openings for installing the Segner wheel tube, Segner tube shafts and the jacket with a fitting for providing working medium exit therein, wherein
  • the jacket is formed as a cylindrical barrel, the cylindrical barrel band being arranged adjacently to the deflected ends of the Segner wheel tube assemblies forming a gap,
  • At least one pair of tube assemblies with open ends deflected in different directions with respect to axis thereof is radially attached to the cylindrical barrel band, said directions being opposite to the sides of the Segner wheel tube assemblies,
  • axes of deflected open ends of barrel tube assemblies are arranged perpendicularly to a plane passing through axes of barrel tube assemblies and the axis of the tube, and openings aligned with the tube assemblies are provided in the band wall.
  • the pressure in the inner chamber of the barrel must be sufficiently high.
  • the high pressure in the inner chamber of the barrel does not allow the working medium to effectively exit from the tube assemblies into the chamber of the barrel.
  • the barrel significantly decreases efficiency of producing mechanical energy in the turbine, makes the turbine unreasonably heavy and large, and can be omitted.
  • the research made by the Inventors has shown that when the barrel 5 is rotated, the working medium is unaffected by centrifugal forces whosecentrifugal pressure drives the working medium out from the open ends of the barrel and creates further rotation torque combining with the friction torque, due to the fact that a small portion of working medium in the inner chamber of the barrel forms a thin "boundary layer" adjacent to the inner wall of the barrel rotates together with the barrel in the same direction, while the other portion of the working medium rotates in the opposite direction by eddy flows formed by the Segner wheel.
  • the speed of said portion of the working medium depends on the distance to the rotational center of the barrel.
  • a third portion of the working medium, in which the working medium is practically still, is formed within the barrel between two portions of working medium rotating in opposite directions.
  • the object of the present invention is to eliminate, or at least alleviate, the above and other drawbacks of the prior art and to provide a highly efficient method of producing mechanical energy in a jet turbine, a single-flow jet turbine, a double-flow jet turbine, and a turbo-jet apparatus based thereon with a high operational efficiency factor.
  • the object of the present invention is achieved by modifying the operational thermodynamic cycle of the jet turbine so as to achieve an increase in power and efficiency and a decrease in the mass-dimensional characteristics of a single-flow or double-flow jet turbine and a turbo-jet apparatus comprising thereof at a given power requirement.
  • a method for producing mechanical energy in a jet turbine is provided, the method comprising
  • a single-flow jet turbine comprising
  • a single-flow centrifugal impulse wheel having blades and rotatably mounted on a shaft, the wheel being adapted to compress a working medium entering the wheel, and covered with a cowl along upper side edges of the blades to form centrifugal passages having outlet openings, and
  • a hollow toroid-shaped collector having a circular opening extending along the inner circumference of the collector
  • collector is rigidly fixed and sealingly attached to the single-flow centrifugal impulse wheel so as to provide the outlet openings of the centrifugal passages with a fluid connection to the inner chamber of the toroid-shape collector
  • the collector has exhaust openings with jet nozzles mounted therein, the exhaust openings being arranged substantially along the outer circumference of the toroid-shaped collector.
  • the technical effect of the invention is the increased efficiency of producing energy, such as mechanical energy, in turbine, such as a single- flow jet turbine, or a double-flow jet turbine, and a turbo-jet apparatus based thereon. Further, the invention provides higher power and efficiency of producing mechanical energy whilst reducing the weight and dimensions of a jet turbine at a given power value. In addition, the invention provides a thermodynamic cycle in which working medium flow is compressed directly in the flow part of the gas-dynamic tract of a turbine. The flow part comprises passages formed by the cowl of the wheel and the blades, a collector chamber and nozzles.
  • a centrifugal impulse wheel of the jet turbine can be implemented as an impulse wheel of a single-flow centrifugal compressor.
  • blades of a single-flow centrifugal impulse wheel are radial. In one embodiment of the invention, blades of a single-flow centrifugal impulse wheel have a shaped deflection angle at the outlet directed against the direction of rotation.
  • the toroid-shaped collector is formed integral with inlet portions of the jet nozzles.
  • an opening extending along the inner circumference of the toroid-shaped collector is continuous or, in some other particular embodiments, multiple openings can be formed by installing dividers.
  • the width of an opening extending along the inner circumference of the collector is preferably not less than the blade height in outlet cross-section of centrifugal passages of a single-flow centrifugal impulse wheel.
  • jet nozzles are supersonic, to achieve maximum working medium exit speed from the jet turbine.
  • jet nozzles are mounted into the toroid-shaped collector of the jet turbine tangentially, in a plane perpendicular to the rotation axis of the single-flow centrifugal impulse wheel.
  • the jet nozzles are mounted into the toroid-shaped collector tangentially, wherein some of the jet nozzles are mounted in a plane perpendicular to the rotation axis of the single-flow centrifugal impulse wheel, while some other jet nozzles are mounted at an angle to the plane perpendicular to the rotation axis of the single-flow centrifugal impulse wheel.
  • some of the jet nozzles have an elongated inlet section, wherein a side cut is made in the elongated inlet section to supply the working medium through said cut.
  • the jet nozzles are provided with a fixedly secured bottom on the side of inlet section end, wherein the dimensions of said bottom correspond to cross-sectional dimensions of the toroid-shaped collector.
  • the toroid-shaped collector of the jet turbine is provided with dividers extending in a cross-section plane of the collector, wherein said dividers are fixedly secured generally in the vicinity of the inlet section end of each of the jet nozzles.
  • the number of the jet nozzles does not exceed the number of the centrifugal passages in the single-flow centrifugal impulse wheel . Without being bound to a particular theory, the inventors believe that this increases efficiency of each jet nozzle.
  • a double-flow jet turbine comprising
  • a double-flow centrifugal impulse wheel having blades and rotatably mounted on a shaft, the wheel being adapted to compress a working medium entering the wheel, wherein said double-flow impulse wheel comprises two single-flow centrifugal impulse wheels securely and sealingly connected to each other in a coaxial manner or formed as a single integral element,
  • said wheels are arranged such that shape of the blades in one of said wheels mirrors the shape of the blades in the other of said wheels, and
  • impulse wheels are covered with cowls along upper side edges of the blades to form centrifugal passages having outlet openings, and, at least one hollow toroid-shaped collector having an opening extending along the inner circumference of the collector,
  • the collector is securely and sealingly attached to the double-flow centrifugal impulse wheel in such manner that the outlet openings of the centrifugal passages are in a fluid connection and open into the inner chamber of the toroid-shaped collector,
  • the collector further has exhaust openings with jet nozzles mounted therein, the exhaust openings being arranged substantially along the outer circumference of the toroid-shaped collector.
  • single-flow impulse wheels forming the double-flow impulse wheel or formed as a single integral element are generally implemented each as an impulse wheel of a single- flow centrifugal compressor.
  • blades of a double-flow centrifugal impulse wheel are radial.
  • blades of a double-flow centrifugal impulse wheel are formed to define a deflection angle at the outlet, wherein the angle is directed against the direction of rotation.
  • the toroid-shaped collector is formed integral with inlet portions of the jet nozzles. In some embodiments of the invention, an opening extending along the inner circumference of the toroid-shaped collector is continuous.
  • an opening extending along the inner circumference of the toroid-shaped collector is provided with dividers.
  • the width of an opening around the circumference defined by said inner diameter is generally at least equal to the total blade height in outlet cross-section of passages of the double-flow centrifugal impulse wheel. Without being bound to a particular theory, the inventors believe that this reduces pressure loss in the working medium when it enters the toroid-shaped collector.
  • the jet nozzles are supersonic.
  • jet nozzles are mounted into the toroid-shaped collector of the jet turbine tangentially, in a plane perpendicular to the rotation axis of the double-flow centrifugal impulse wheel.
  • jet nozzles are mounted into the toroid-shape collector of the jet turbine tangentially, wherein some of the jet nozzles are mounted in a plane perpendicular to the rotation axis of the double-flow centrifugal impulse wheel, while some other jet nozzles are mounted at an angle to the plane perpendicular to the rotation axis of the double-flow centrifugal impulse wheel.
  • jet nozzles are provided with an elongated inlet section, wherein a side cut is made in the elongated inlet section to supply the working medium through said cut.
  • jet nozzles are provided with a fixedly secured bottom on the side of inlet section end, wherein the dimensions of said bottom correspond to cross-sectional dimensions of the toroid-shaped collector.
  • the toroid-shaped collector is provided with dividers extending across the collector in cross-section plane, wherein said dividers are fixedly secured generally in the vicinity of the inlet section end of each jet nozzle.
  • the number of jet nozzles does not generally exceed half of the number of the centrifugal passages in the double-flow centrifugal impulse wheel when utilizing one toroid-shaped collector, and is preferably equal to the number of passages when utilising two toroid-shaped collectors. Without being bound to a particular theory, the inventors believe that this increases efficiency of each jet nozzle.
  • a turbo-jet apparatus comprising
  • inlet collectors for supplying a working medium
  • the collectors being fixedly mounted around the shaft and connected to inlet openings of impulse wheels by means of tube assemblies, wherein the tube assemblies are arranged around the shaft, the tube assemblies being fixedly connected to the collectors, and moveably connected to the inlet openings of the impulse wheels of the turbines in a sealed manner.
  • the single-flow turbines comprise impulse wheels arranged such that shape of the blades in one of said wheels mirrors the shape of the blades in some other of said wheels, wherein the jet nozzles are directed in oppositely mirrored directions.
  • Fig. 1 shows an axonometric view of a single-flow jet turbine according to one embodiment of the present invention.
  • Fig. 2 shows an axonometric cross-sectional view of a single-flow jet turbine according to one embodiment of the present invention.
  • Fig. 3 shows an axonometric view of a single-flow centrifugal impulse wheel according to one embodiment of the present invention.
  • Fig. 4 shows an axonometric view of an embodiment of a toroid- shaped collector according to one embodiment of the present invention .
  • Fig. 5 shows an axonometric view of an embodiment of a jet nozzle with an elongated inlet section according to one embodiment of the present invention.
  • Fig. 6 shows an axonometric view of an embodiment of a toroid- shaped collector formed integrally with the inlet sections of a jet nozzle according to one embodiment of the present invention.
  • Fig. 7 shows an axonometric view of an embodiment of a jet nozzle with a threaded apparatus according to one embodiment of the present invention.
  • Fig. 8 shows an axonometric cross-sectional view of a double-flow jet turbine according to one embodiment of the present invention.
  • Fig. 9 shows an axonometric view of a double-flow jet turbine according to one embodiment of the present invention.
  • Fig. 10 shows an axonometric view of a double-flow centrifugal impulse wheel according to one embodiment of the present invention.
  • Fig. 11 shows an axonometric view of a turbo-jet apparatus with two double-flow jet turbines according to one embodiment of the present invention.
  • Fig. 12 shows an axonometric cross-sectional view of a turbo-jet apparatus with two double-flow jet turbines according to one embodiment of the present invention.
  • Fig. 13 shows the results of analysis of operational characteristics of a single-flow jet turbine with different working medium compression values according to one embodiment of the present invention.
  • a single-flow jet turbine (Fig. 1 and Fig. 2) according to one embodiment of the present invention comprises a shaft 1 with single-flow centrifugal impulse wheel 2 comprising blades 3 fixedly mounted thereon (e.g. by means of splines).
  • the impulse wheel 2 is covered with a cowl 4 along the upper side edge of blades 3 to form closed centrifugal passages 5 comprising inlet openings 6, which function as an inlet for the impulse wheel 2 of the jet turbine, and outlet openings 7, which function as an outlet from the impulse wheel 2.
  • the impulse wheel 2 is provided with radial blades 3.
  • blades of the impulse wheel can have a shaped form, for example, they can be profiled, with a deflection angle at the outlet directed against the direction of rotation of the impulse wheel.
  • Cowl 4 is generally attached to the upper side edge of the blades 3 in a fixed and rigid manner, e.g. via welding.
  • the cowl can be mounted fixedly with respect to the impulse wheel 2 with a gap therebetween to provide rotation thereof, and is attached to a stationary base which can be specifically formed therefore.
  • the single-flow centrifugal impulse wheel 2 is adapted to compress the working medium entering the wheel by means of centrifugal forces acting upon the working medium and due to geometry of the flow duct formed by centrifugal passages 5.
  • Single-flow impulse wheel 2 can be implemented for example, as an impulse wheel of a single-flow centrifugal compressor, in particular, an impulse wheel similar to the prior art solution (N . Kampsti, "Compressor Aerodynamics", chapter 2.2, Moscow, Mir Publishing, 2000). Parameters of a single-flow impulse wheel and operational characteristics thereof including its geometrical parameters are determined based on requirements for the jet turbine in accordance with methods and calculations provided, for instance, in the aforementioned publication.
  • Blades 3 of the centrifugal impulse wheel 2 can be curved such that they interact with the encircling flow of a working medium and force on particles of the working medium when the impulse wheel 2 is rotated. Consequently, centrifugal forces are generated in the particles of the working medium, and the working medium is thrown back with a high speed to an exterior of the impulse wheel 2, in particular, to the outlet openings 7 of the centrifugal passages 5, where the working medium has an increased pressure.
  • blades 3 form geometry of the flow duct of centrifugal passages 5, and blades 3 compress the working medium in centrifugal passages 5 together with centrifugal forces. Compression of a medium flow in the single-flow jet turbine according to the present invention depends partly on rotation speed of the impulse wheel 2 which can be increased in the single-flow jet turbine due to its construction.
  • a single-flow impulse wheel 2 is in a fluid connection with a collector 8.
  • the collector 8 is implemented as a toroid provided with an opening 9 extending along the inner circumference of the collector.
  • the opening 9 can be continuous or provided with dividers.
  • the width of the opening 9 is at least equal to the blade 3 height in cross-section of opening 7 of centrifugal passages 5 of the impulse wheel 2, which provides unimpeded inlet of working medium into the toroid-shaped collector 8 without pressure loss in the working medium.
  • the toroid-shaped collector 8 is attached to the impulse wheel 2 in such manner that outlet openings 7 of the centrifugal passages 5 are in fluid communication with the inner chamber 10 of the toroid-shaped collector 8.
  • the toroid- shaped collector 8 can be formed with different cross-sections, e.g. square, rectangular, circular or other shape.
  • the toroid-shaped collector 8 is provided with a circular cross-section in order to minimize mass-dimensional properties thereof.
  • the width of the opening 9 is practically identical to the cross-sectional diameter of the toroid-shaped collector 8.
  • the toroid-shaped collector 8 is fixedly and hermetically sealed to the impulse wheel 2 from the side of opening 9.
  • the toroid-shaped collector 8 can be provided with specific attachment points, by which it is connected (generally by means of bolted connection providing a hermetic seal, e.g. using a washer or a sealant) to the impulse wheel 2 and the cowl 4, which can be provided with cylindrical flanges 11 and 12 respectively for said purpose.
  • a hermetic seal e.g. using a washer or a sealant
  • Such arrangement provides secure attachment of the toroid-shaped collector 8 to the impulse wheel 2, as well as the ability to assembly and disassembly the jet turbine.
  • - collector 3 connects together the impulse wheel 2 and the jet nozzles 14 by a rigid, hermetic, and compact connection providing their effective joint and providing outflow of working medium through the outlet openings 7 of the closed centrifugal passages 5 in the chamber 10;
  • - collector 3 stores working medium in the chamber 10 and provides increase of the working medium's pressure
  • Openings 13, in which the jet nozzles 14 are installed, are arranged around the outer circumference of the toroid-shaped collector 8 (Fig. 4).
  • jet nozzles 14 are generally supersonic, e.g. formed by convergent-divergent nozzles (A. A. Dorofeev, "Basic thermal rocket engine theory", chapters 3 and 5, Bauman MHTS, Moscow, 1999), with flow duct sections thereof in serial arrangement: the inlet section, the convergent section, and the divergent section respectively.
  • convergent-divergent nozzles A. A. Dorofeev, "Basic thermal rocket engine theory”, chapters 3 and 5, Bauman MHTS, Moscow, 1999
  • the jet nozzles 14 are mounted with inlet section thereof into the toroid- shaped collector 8 tangentially and uniformly directed along the circumference, generally perpendicular to the impulse wheel 2.
  • the axis of symmetry of at least some jet nozzles 14 can be arranged at an angle with respect to the plane perpendicular to the axis of rotation of impulse wheel 2 by forming openings 13 in the toroid-shaped collector 8 at different angles with respect to the plane perpendicular to the axis of rotation of impulse wheel 2, and by providing curvilinear jet nozzles 14.
  • Jet nozzles 14 can be mounted by means of a threaded connection and/or by welding.
  • the inlet section of the jet nozzle 14 is elongated (Fig. 5) to provide the possibility of installing said section into the toroid-shaped collector 8, e.g. by welding.
  • Jet nozzles can be realized by forming the toroid-shaped collector integrally with the inlet sections of jet nozzles (Fig. 6). Jet nozzles can thus be installed into the toroid-shaped collector by means of a threaded connection and/or by welding (Fig. 7) .
  • the toroid-shaped collector is formed integrally with the inlet section of jet nozzles. This allows to significantly increase the strength of attachment in such jet nozzle collector, which consequently results in that the rotational speed of the impulse wheel can be substantially increased, in particular up to 680-700 m/s or more, and therefore, that the compression of working medium flow in the jet turbine can be increased.
  • An increase in working medium compression in the flow channel of the jet turbine's gas-dynamic tract results in an increase in efficiency of producing mechanical energy and, correspondingly, in jet turbine output.
  • a side cut 15 is formed in the elongated inlet section of the jet nozzle 14. Side cut 15 is open towards outlet openings 7 and provides supply of working medium therethrough, from chamber 10 of the toroid-shaped collector 8 into jet nozzle 14.
  • jet nozzles 14 can be provided on the inlet side with a fixedly secured (e.g. by welding) bottom 16, wherein the dimensions of said bottom correspond to cross- sectional dimensions of the toroid-shaped collector 8, with said bottom bridging said collector.
  • each jet nozzle 14 can be tightly covered from the inlet side thereof with a divider fixedly secured (e.g. by welding) in the collector 8, wherein the dimensions of said divider correspond to cross-sectional dimensions of the toroid-shaped collector 8, with said divider bridging said collector.
  • jet nozzles can be mounted tangentially on the openings of the toroid-shaped collector.
  • jet nozzles are formed with a bottom fixedly secured on the side of inlet section end, wherein the dimensions of said bottom correspond to cross-sectional dimensions of the inlet section of the jet nozzle.
  • Jet nozzles 14 can be formed with different cross-sections, e.g. square, rectangular, circular or other shape. In the illustrated embodiments of jet turbines, jet nozzles 14 are formed with a circular cross-section in order to minimize mass-dimensional properties thereof.
  • jet nozzles 14 are integral with the collector to provide a high strength of the turbine structure. In another embodiment, jet nozzles 14 are dismountable to allow for easier manufacturing, repair and/or replacement during maintenance.
  • axes of symmetry of jet nozzles 14 are arranged substantially perpendicular to the outlet profile of radial blades 3 in cross-section of outlet openings 7 of the impulse wheel 2.
  • the direction of mounting jet nozzles 14 generally coincides with the deflection angle of blades 3 in cross-section of outlet openings 7 in order to reduce working medium pressure loss in the jet turbine.
  • the number of jet nozzles 14 In order to provide a steady working medium flow over the whole length of the flow duct of a single-flow jet turbine, the number of jet nozzles 14 generally does not exceed the number of centrifugal passages 5.
  • all elements of the single-flow jet turbine are made of a high-strength construction-grade titanium alloy BT6.
  • design parameters as selected above are also applicable to a double-flow jet turbine and a turbo-jet apparatus according to embodiments of the present disclosure in order to increase the working medium pressure and/or reduce the working medium pressure losses.
  • a double-flow jet turbine (Fig. 8 and Fig. 9) comprises a double-flow centrifugal impulse wheel 22 with blades 23 rotatably mounted on a shaft 21, adapted to compress the working medium entering the wheel .
  • the double-flow impulse wheel 22 is formed of two single-flow impulse wheels arranged in a coaxial manner and fixedly secured to each other, or formed integrally.
  • Single-flow impulse wheels similar to the wheel described herein for a single-flow jet turbine can be used, wherein one wheel is formed with a mirrored (opposite) direction of blade shape with respect to the other.
  • the secure coaxial connection between the single-flow impulse wheels can be formed, e.g. by means of a fixed bolted connection or by welding.
  • the double-flow impulse wheel 22 (Fig. 10) is formed integrally from one piece by milling the blades on each side of the piece using specialized multi-axis machining tools.
  • the blade shapes are milled in a mirrored (opposite) direction on each side.
  • the double-flow impulse wheel 22 is covered with cowls 24 along the upper side edge of blades 23.
  • centrifugal passages 25 are formed, comprising inlet openings 26, which function as inlets for the double-flow impulse wheel 22 , and outlet openings 27, which function as outlets from the double-flow impulse wheel 22.
  • Cowls 24 is generally attached to the upper side edges of the blades 23 in a fixed and rigid manner, e.g. via welding.
  • the cowls 24 can be mounted fixedly with respect to the double-flow impulse wheel 22 with a gap therebetween to provide rotation thereof, and are attached to a specifically formed stationary base.
  • the double-flow impulse wheel 22 is rigidly and sealedly connected to one (common for both single- flow wheels) toroid-shaped collector 28, wherein inlet openings 27 of centrifugal passages 25 are open into the collector chamber 29.
  • the toroid-shaped collector 28 can be attached to the double-flow impulse wheel 22 similarly to the attachment of the toroid-shaped collector in a single-flow jet turbine described herein.
  • Openings 31, in which the jet nozzles 32 are installed, are arranged around the outer circumference of the toroid-shaped collector 28.
  • Jet nozzles 32 are formed and mounted into the toroid-shaped collector 30 of the double-flow jet turbine similarly to the process described herein with respect to the single-flow jet turbine.
  • the collector can be provided with fixedly attached dividers 33 placed in front of the inlet section of each jet nozzle 32.
  • the double-flow jet turbine can also be provided with two identical toroid-shaped collectors mounted in a coaxial manner and securely connected to each other with side surfaces thereof, e.g., by means of bolts or by welding. Jet nozzles can thus be rigidly mounted along the outer circumference of each collector by means of a threaded connection and/or by welding.
  • two toroid-shaped collectors can be formed by installing an inner medial divider in a common toroid-shaped collector for both single-flow wheels, wherein said divider is placed perpendicularly to the axis of rotation of the collector and dividing the inner chamber thereof into two (generally equal) parts. Jet nozzles can thus be rigidly mounted along the outer circumference of each part of the collector by means of a threaded connection and/or by welding.
  • mass-dimensional properties of a double-flow jet turbine provided with one toroid-shaped collector display a near 20% improvement over similar combined properties of two single-flow jet turbines combined.
  • a turbo-jet apparatus (Fig. 11 and Fig. 12) comprises a shaft 41 with bearing supports 42, with at least two double-flow jet turbines 43 fixedly mounted thereon in a spaced manner and adapted to rotate in one direction.
  • Several single-flow and/or double-flow turbines as disclosed in claims 2 and 17 can be mounted on the shaft 41 at the same time.
  • single-flow turbines can be mounted in the same way, or they can be arranged facing each other or in opposite directions with respect to the inlets thereof.
  • Double-flow turbines can be mounted on the shaft 41 facing in one direction only.
  • single-flow jet turbines with impulse wheels formed with mirrored (opposite) directions of blade shape and mirrored (opposite) direction of mounting jet nozzles must be used.
  • Inlet collectors 44 for supplying working medium are generally fixedly mounted around the shaft 41. Connection between the inlet collectors 44 and inlet openings of impulse wheels of the turbines 43 is formed by means of tube assemblies 45 arranged around the shaft 41 with inlet collectors 44, wherein said tube assemblies are sealedly and moveably connected with inlet openings of impulse wheels of the turbines 43 by means of end seals and/or labyrinth seals. Tube assemblies 45 are rigidly connected with inlet collectors 44, e.g. by means of flanges, thread or by welding.
  • turbo-jet apparatuses with several single-flow or double- flow jet turbines results in a manifold increase in power of turbo-jet apparatuses with only a slight increase in mass-dimensional properties thereof.
  • the method for producing mechanical energy in a single-flow jet turbine is carried out as follows. In the initial position, the single-flow centrifugal impulse wheel 2 of a single-flow jet turbine is in a rest state, i.e. it is motionless.
  • a working medium e.g. steam from a steam generator or gas from a combustion chamber
  • a working medium is urged by its initial pressure to enter the inlet of the wheel 2, into inlet openings 6 of the centrifugal passages 5 at an initial speed; upon passing through said elements, the working medium flows from outlet openings 7 through opening 9 into inner chamber 10 of the toroid-shaped collector 8. From the chamber 10, the working medium moves through side cuts 15 into jet nozzles 14.
  • the initial pressure of the working medium acts upon bottoms 16, resulting in acceleration of the working medium in the jet nozzles 14 to supersonic speed; the working medium then exits the nozzles into surrounding space substantially perpendicular to the radius of the impulse wheel 2, thus forming a propelling force pulse that rotates the impulse wheel 2 on the shaft 1
  • the working medium at this stage is not compressed due to geometry of the flow duct of centrifugal passages 5 and due to centrifugal forces acting upon the working medium neither in the impulse wheel 2 nor in the toroid-shaped collector 8.
  • the rotation of impulse wheel 2 of the jet turbine at the initial stage occurs exclusively due to the propelling force pulse created when the working medium exits jet nozzles 14, wherein prior to said exit, the working medium generally possesses the initial thermodynamic characteristics. Therefore, the single-flow jet turbine utilizing only the difference of the initial working medium pressure acts in accordance with the Segner wheel principle. That a short operational interval of the single- flow jet turbine is the time interval required for the turbine to reach the design operation. As the rotational velocity of the impulse wheel 2 increases, approaching the design values, blades 3 forming the flow duct geometry of centrifugal passages 5, together with the centrifugal forces acting upon the working medium flow in centrifugal passages 5, compress the working medium flow with a corresponding increase in density.
  • the compressed working medium flow having the high temperature, pressure and velocity values passes from the centrifugal passages 5 into the inner chamber 10 of the toroid-shaped collector 8, where said flow is slowed due to counterpressure of the working medium present therein and is further compressed to increase pressure and temperature of the working medium with respect to the pressure and temperature of the working medium at outlet openings 7.
  • the gradients of density, temperature, pressure and velocity are leveled, wherein the working medium flow is slowed and the working medium flow pressure is increased to a maximum value known as the slowed working medium flow pressure.
  • the pressure of the working medium inside the collector 8 is further increased by centrifugal forces. Thus, prior being expelled through the jet nozzles 14, the working medium reaches maximum pressure.
  • the single-flow jet turbine can be actuated and efficiently operated when the initial working medium pressure at the input into the impulse wheel 2 is insufficient for actuating the turbine and achieving normal operation thereof.
  • forced initial rotation of the shaft 1 can be used (e.g. using a mechanical or electromechanical drive), which creates a necessary and sufficient compression of the working medium in the impulse wheel 2 of the jet turbine, said compression providing further operation of the jet turbine without forced rotation of the shaft 1.
  • the table shows results of mathematical simulation and preliminary bench testing of the disclosed single-flow jet turbine obtained in different operation modes (modes I to IV, and also modes V to VI) thereof in relation to initial working medium pressure at the inlet into the jet turbine and in relation to compression of the working medium therein.
  • the single-flow jet turbine is made of BT6 titan alloy.
  • the results of mathematical simulation and preliminary testing of the single-flow jet turbine show that power thereof and efficiency of producing mechanical energy are affected by two primary factors: initial pressure and temperature of the working medium entering the turbine inlet, as well as working medium compression in the flow part of the single-flow jet turbine.
  • the following parameters are controllable : vapor flow rate through the turbine; vapor pressure at inlet of the impulse wheel; vapor temperature at inlet of the impulse wheel; diameter of the impulse wheel; rotational velocities of the impulse wheel; and quantity of the jet nozzles.
  • Working medium flow compression values can be changed indirectly, for example, by changing rotational velocity of the impulse wheel.
  • the value of the vapor flow rate through the turbine lies within range 1000 kg/h - 50000 kg/h, preferably 5000 kg/h - 15000 kg/h.
  • Vapor pressure at inlet of the impulse wheel has the value 10 kPa - 5000 kPa, preferably within ranges 400 kPa - 800 kPa and 1500 kPa - 2000 kPa.
  • Vapor temperature at inlet of the impulse wheel has the value 100°C - 250°C, preferably within ranges 150°C - 170°C and/or 190°C - 210°C.
  • Diameter of the impulse wheel lies within 0,1 m - 2 m, preferably 0,5 m - 0,8 m.
  • Rotational velocities of the impulse wheel has the value 1000 rpm - 10000 rpm, preferably within ranges 3000 rpm - 4500 rpm and/or 5500 rpm - 7000 rpm .
  • the number of the jet nozzles is selected from 2 to 50, preferably from 10 to 20.
  • vapor flow rate through the turbine, diameter of the impulse wheel, and quantity of the jet nozzles had the same values for all modes I to VI.
  • Vapor pressure at inlet of the impulse wheel and vapor temperature at inlet of the impulse wheel were increased for modes V and VI.
  • Working medium flow compression values in the impulse wheel were changed in modes I to VI.
  • Initial pressure and temperature of the working medium relate to parameters that are usually defined by the type and operation of working medium source (generator), for example, a steam generator, and the increase of initial pressure and temperature of the working medium is not directly associated with the jet turbine. It shall be appreciated that the increase in initial pressure and temperature of the working medium is associated with substantial additional energy consumption, e.g. by the steam generator, which is not always feasible due to technical, operational, financial and other reasons.
  • working medium source for example, a steam generator
  • the compression of the working medium in the single-flow jet turbine is defined solely by design efficiency thereof and constitutes the primary factor behind the significant increase in efficiency of producing mechanical energy in said turbine.
  • the single-flow jet turbine provides practically identical power and efficiency of producing mechanical energy when operating in modes III and V, and in modes IV and VI. Therefore, the increase in working medium compression in the single-flow jet turbine operating in modes III and IV up to 5.08 and 5.95, respectively, allows to use lower working medium pressure and temperature values (630 kPa and 158°C instead of 1600 kPa and 200°C) at the inlet, while still providing required power.
  • the increase in working medium flow compression can be achieved, for example, by adjusting rotational velocity of the impulse wheel. Rotational velocities of the impulse wheel in modes III and IV were increased to increase working medium flow compressions in these modes, as shown in the table.
  • the single-flow jet turbine is capable of achieving required performance in terms of efficiency and power thereof with a low initial working medium pressure at the inlet.
  • the data presented herein supports the claimed advantage of the disclosed method for increasing efficiency of producing mechanical energy in the disclosed single-flow jet turbine, wherein said method is based on an innovative operational thermodynamic cycle that provides compression of working medium entering the turbine prior to the exit of said working medium .
  • the method for producing mechanical energy is similarly implemented in a double-flow jet turbine provided with a double-flow centrifugal impulse wheel.
  • the double-flow centrifugal impulse wheel is formed with a common hollow toroid-shaped collector
  • the common hollow collector is more evenly filled with working medium .
  • the method for producing mechanical energy is similarly implemented in turbo-jet apparatuses based on single-flow and/or double- flow jet turbines.
  • Such technical solution provides a compact-sized turbojet apparatus with a manifold increase in power.
  • the single-flow and double-flow jet turbines implementing a thermodynamic cycle with working medium flow compression prior to acceleration and subsequent exit thereof directly in the flow part of their gas-dynamic tracts, as well as the turbo-jet apparatuses based thereon provide a substantial increase in power and efficiency of producing mechanical energy compared to the prior art, with efficiency ratio of about 55-65% and more.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne l'ingénierie mécanique, en particulier des turbines à air, à gaz et à vapeur pour entraîner des générateurs d'énergie électrique, des systèmes de propulsion, des compresseurs frigorifiques, des pompes à chaleur et autres. Selon l'invention, un procédé pour générer de l'énergie mécanique dans une turbine à réaction comprend les étapes d'utilisation d'un fluide de travail dans une roue à impulsion centrifuge de celle-ci, la roue étant pourvue de passages centrifuges, de compression du fluide de travail dans les passages centrifuges de la roue, de sortie du fluide de travail dans un collecteur toroïdal ayant des buses à jet, pour diminuer la vitesse d'écoulement et augmenter la pression d'écoulement de manière à amener le fluide de travail à être accéléré dans les buses à jet et à sortir dans l'espace environnant à une vitesse supersonique, formant ainsi une impulsion de force de propulsion permettant une rotation de la roue à impulsion de la turbine à réaction. L'invention fournit une augmentation de l'efficacité de génération d'énergie mécanique par une augmentation de la puissance et de l'efficacité, et par la diminution du poids et des dimensions pour une exigence d'alimentation donnée. Selon l'invention, un procédé de génération d'énergie mécanique peut être utilisé dans une turbine à réaction à flux unique, une turbine à réaction à double flux et un appareil turboréacteur associé.
PCT/IB2014/063718 2013-08-05 2014-08-05 Procédé de génération d'énergie mécanique, turbine à flux unique et turbine à double flux, et appareil turboréacteur associé Ceased WO2015019294A1 (fr)

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RU181361U1 (ru) * 2017-12-18 2018-07-11 Василий Алексеевич Аброськин Центробежная турбина
EP3392456A4 (fr) * 2015-12-15 2019-08-14 Posco Energy Co. Ltd. Turbine à vapeur du type à réaction

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US11471808B2 (en) 2017-01-09 2022-10-18 Cummins Filtration Ip, Inc. Impulse turbine with non-wetting surface for improved hydraulic efficiency
DE112019000644T5 (de) 2018-02-02 2020-10-29 Cummins Filtration Ip, Inc. Trennbaugruppe mit einer einteiligen impulsturbine
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RU2742711C2 (ru) * 2018-04-28 2021-02-09 Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" Радиальная биротативная активно-реактивная турбина (варианты)
CN112343676A (zh) * 2019-08-07 2021-02-09 江苏海事职业技术学院 一种背压式汽轮机设备
CN111766129A (zh) * 2020-06-18 2020-10-13 浙江省海洋水产研究所 一种化学需氧量消解试验用加热与冷却装置
CN113982752B (zh) * 2021-10-30 2022-09-27 中北大学 一种氢燃料高速旋转磁流体发电装置
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US20150037134A1 (en) 2015-02-05
RU2013136499A (ru) 2015-02-10
GB201401984D0 (en) 2014-03-19

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