EP3119991B1 - Zentrifugale radialturbine - Google Patents

Zentrifugale radialturbine Download PDF

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Publication number
EP3119991B1
EP3119991B1 EP15718087.8A EP15718087A EP3119991B1 EP 3119991 B1 EP3119991 B1 EP 3119991B1 EP 15718087 A EP15718087 A EP 15718087A EP 3119991 B1 EP3119991 B1 EP 3119991B1
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EP
European Patent Office
Prior art keywords
disc
induction
blades
support disc
turbine according
Prior art date
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Not-in-force
Application number
EP15718087.8A
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English (en)
French (fr)
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EP3119991A1 (de
Inventor
Claudio SPADACINI
Dario RIZZI
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Exergy SpA
Original Assignee
Exergy SpA
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Publication of EP3119991A1 publication Critical patent/EP3119991A1/de
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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
    • F01D1/02—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
    • F01D1/12—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 with repeated action on same blade ring
    • F01D1/14—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 with repeated action on same blade ring 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
    • F01D1/24—Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working fluid stream without intermediate stator blades or the like
    • F01D1/28—Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working fluid stream without intermediate stator blades or the like 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
    • F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
    • F01K25/00—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for
    • F01K25/08—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for using special vapours
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
    • F01K7/00—Steam engine plants characterised by the use of specific types of engine; Plants or engines characterised by their use of special steam systems, cycles or processes; Control means specially adapted for such systems, cycles or processes; Use of withdrawn or exhaust steam for feed-water heating
    • F01K7/16—Steam engine plants characterised by the use of specific types of engine; Plants or engines characterised by their use of special steam systems, cycles or processes; Control means specially adapted for such systems, cycles or processes; Use of withdrawn or exhaust steam for feed-water heating the engines being only of turbine type

Definitions

  • the subject of the present invention is a centrifugal radial turbine for producing electrical and/or mechanical energy.
  • the present invention is situated in the field of those processes that provide for the obtainment of one or more phases of expansion of a work fluid through one or more turbines adapted to convert the energy of the fluid by means of the expansion thereof in the turbine(s).
  • the present invention refers to the centrifugal radial expansion turbines of counter-rotating type.
  • the present invention refers to the expansion turbines used in the apparatuses for producing energy by means of steam Rankine cycle or organic Rankine cycle (ORC).
  • ORC organic Rankine cycle
  • Centrifugal radial turbines are known that are used for the expansion of steam or organic fluids.
  • the public document WO 2013/108099 illustrates a turbine for the expansion of an organic fluid in a Rankine cycle provided with arrays of rotor and stator blades that are alternated in a radial direction.
  • the supply of the steam in the turbine is obtained in frontal direction.
  • a first expansion of the work fluid is provided in a substantially radial direction.
  • a second expansion of the work fluid is provided in a substantially axial direction.
  • the stator blades are supported by an external casing of the turbine.
  • Counter-rotating centrifugal radial turbines have also been known for a long time, which are used for the expansion of the water steam.
  • the public document GB 311,586 illustrates a steam turbine that comprises two opposite rotating discs bearing blade rings. In proximity to the radially more internal blade ring, passages are present that traverse the discs starting from steam chambers obtained in the turbine containment box. Steam induction pipes are connected to said chambers.
  • the Applicant has observed that the known centrifugal radial turbines, like those described above, can be improved with regard to various aspects, in particular in a manner so as to increase the efficiency thereof and simultaneously improve the structural strength thereof.
  • the induction passages obtained in the discs first cause a structural weakening of the discs themselves. Indeed, such passages must be sized in a manner such to allow the transit of the maximum fluid flow rate that the turbine can treat, so as to maximize the efficiency thereof.
  • the passage crossing speed In order to limit the load losses through said passages, the passage crossing speed cannot however exceed specific values (approximately 10m/s), so that it is necessary and known to obtain said passages with areas such to obtain the desired flow rate even with low crossing speeds.
  • centrifugal radial turbines with (non counter-rotating) stator and rotor blades like those described in the document WO 2013/108099 , in particular in the configurations of figure 1 and figure 2 , have considerable problems relative to the insertion of the work fluid, since spaces are limited on the side of the machine where there is the support shaft; in addition, in such zone overly high temperatures cannot be allowed (cooling problems) in order to avoid damaging delicate components such as the mechanical seal and the bearings that normally equip said machines and said areas.
  • the Applicant set the objective of proposing a centrifugal radial turbine, preferably but not exclusively counter-rotating, with improved efficiency with respect to the centrifugal radial turbines, counter-rotating and otherwise, of the prior art.
  • the Applicant has set at least one of the following objects/improvements with regard to the prior art:
  • the Applicant has found that the indicated objective, at least one of the above-listed objects and still others can be achieved by also exploiting the induction phase in order to rotate the disc or discs by means of an axial stage obtained at the induction passages of said disc or said discs or, in other words, shaping said passages in a manner so as to have a blading.
  • the present invention regards a centrifugal radial turbine, comprising:
  • the present invention regards a centrifugal radial turbine, comprising:
  • the present invention regards a counter-rotating centrifugal radial turbine, comprising:
  • the induction channels are opened both on the first and on a second face opposite the first of the disc(s) and are preferably extended along an axial direction.
  • the rotor blades each have a leading edge (and a trailing edge) that is extended along a substantially radial direction.
  • the leading edge faces the second face of the respective disc.
  • the trailing edge faces the first face of the respective disc.
  • the induction channels are at least partially delimited by said induction rotor blades.
  • the adjacent induction channels are separated by one of said induction rotor blades.
  • the induction channels and the induction rotor blades are arranged in succession along at least one circular path coaxial with the rotation axis.
  • the axial rotor stage comprises a plurality of rotor blades arranged one after the other in an annular passage (which is extended along said circular path) obtained in the disc and coaxial with the rotation axis and said rotor blades divide said annular passage into a plurality of the abovementioned induction channels.
  • the induction rotor blades are integrally obtained in the respective support disc. This ensures greater solidity and structural strength of the disc(s).
  • the disc(s) and the relative rotor blades are obtained by means of three-dimensional sintering techniques (method for creating objects from metal and/or ceramic powders). This allows obtaining the disc(s) and the rotor blades with limited size, suitable for low-power applications (e.g. for powers comprised between about 5kW and about 50kW), for example in the automotive field.
  • the ratio between the radial height of each induction rotor blade and the diameter of the support disc(s) is comprised between about 0.007 and about 0.05.
  • radial height it is intended the extension along a radial direction of an induction rotor blade.
  • diameter of the disc it is intended the maximum diameter of the disc excluding possible auxiliary blades of an auxiliary axial stage arranged on a periphery of said disc.
  • the rotor blades and consequently the passage channels are small with respect to the size of the disc(s) and consequently the disc/discs is/are more solid with respect to those of the prior art.
  • an axial traversing speed of the work fluid through the induction channels is comprised between about 35 m/s and about 100 m/s, preferably between about 40 m/s and about 45 m/s. Due to the presence of the rotor blades, the speed of crossing the induction channels is such that the necessary flow rates are obtained with passage areas that are reduced with respect to the prior art.
  • the turbine comprises a plurality of induction stator blades of a respective axial stator stage side-by-side the induction rotor blades of the support disc or of each of the support discs and arranged on the side of the second face of the respective support disc opposite the first face.
  • the axial stator stage together with the respective axial rotor stage define an axial induction stage.
  • the turbine comprises a fixed portion provided with a plurality of fixed induction openings side-by-side the induction rotor blades of the support disc or of each of the support discs and placed on the side of a second face of the respective support disc opposite the first face.
  • the fixed induction openings are in fluid communication with an inlet duct and, possibly, with an induction chamber arranged on one side of the fixed portion opposite the respective disc.
  • the induction stator blades delimit the fixed induction openings.
  • the induction stator blades are housed in the fixed induction openings.
  • each of the fixed induction openings houses at least one induction stator blade.
  • the axial stator stage comprises a plurality of stator blades arranged one after the other in an annular passage obtained in the fixed portion and coaxial with the rotation axis of the disc or of the discs and said stator blades divide said annular passage into a plurality of the abovementioned fixed induction openings.
  • the fixed induction openings are through holes or slots obtained in the fixed portion and each of said holes or slots houses one or more of the induction stator blades.
  • the axial rotor stage is of action type.
  • the static pressure of the fluid upstream and downstream of the rotor blades is therefore the same.
  • the axial rotor stage is of reaction type.
  • the support disc or discs have compensation through openings obtained in radially internal positions with respect to the through induction channels, in order to balance the axial thrust on the discs.
  • the turbine comprises an annular chamber that is concentric and facing the second face of the support disc or of each support disc.
  • the fixed containment case that houses the support disc or discs comprises annular walls coaxial with the rotation axis and delimiting said annular chamber(s).
  • the annular chamber is partly delimited by the support disc, partly by said annular walls and partly by further delimitation walls integral with (or in any case fixed with respect to) the containment case and facing the respective support disc.
  • each support disc comprises annular appendages projecting from the respective second face, coaxial with the rotation axis and sealingly engaged with the annular walls in order to delimit said annular chamber(s).
  • the turbine comprises a plurality of sliding gaskets, each interposed between one end of an annular wall and the respective annular appendage.
  • said sliding gaskets are mounted on the ends of the annular walls and slide against said annular appendices.
  • said sliding gaskets could be mounted on the annular appendices and slide against the ends of the annular walls.
  • the turbine comprises at least one auxiliary axial stage placed in a position radially external with respect to the support disc with respect to each of the support discs.
  • Said at least one auxiliary axial stage is placed downstream of the radial rotor stages with respect to a direction of the flow of the work fluid.
  • said at least one auxiliary axial stage comprises a plurality of auxiliary rotor blades situated at or directly mounted on a peripheral edge of each of the support discs.
  • said at least one auxiliary axial stage comprises a plurality of auxiliary stator blades mounted fixed on a support element placed in a position radially external with respect to the support discs.
  • said support element is part of a radially external portion of the containment case.
  • each of the support discs has an auxiliary annular appendage projecting from the respective first face, coaxial with the rotation axis and placed in a position radially external with respect to the radial stages.
  • said annular appendage is sealingly engaged with a radially internal ring bearing radially internal ends of the auxiliary stator blades.
  • the turbine comprises a sliding gasket interposed between the radially internal ring and the respective annular appendage.
  • the turbine comprises a nose integral with the containment case and situated in the inlet duct.
  • the nose is placed on the side of a second face of the support disc opposite the first face.
  • the nose is part of the fixed portion provided with the fixed induction openings.
  • the fixed induction openings and, preferably, the induction stator blades are situated circumferentially around the nose.
  • the turbine is part of plants for the cogeneration of energy of Rankine cycle type which are closed-circuit (so that the work fluid remains in the circuit even during maintenance) and use organic fluids with high molecular weight.
  • the turbine can be used in open-cycle or closed-cycle steam plants.
  • the reference number 1 indicates overall an expansion turbine of counter-rotating centrifugal radial type in accordance with the present invention.
  • the illustrated centrifugal radial turbine counter-rotating 1 can be used in apparatuses for generating mechanical and/or electrical energy, for example of organic Rankine cycle (ORC) type or steam Rankine cycle type.
  • ORC organic Rankine cycle
  • the illustrated counter-rotating centrifugal radial turbine 1 is used in low-power applications (e.g. for generating powers comprised between about 5kW and about 50kW).
  • the turbine 1 comprises a fixed containment case 2 which at its interior houses a first support disc 3 and a second support disc 4.
  • the support discs 3, 4 can freely rotate, each independently from the other, in the support case 2 around a common rotation axis "X-X".
  • the first disc 3 is integral with a respective first rotation shaft 5 mounted in the containment case 2 by means of first bearings 6.
  • the second disc 4 is integral with a respective second rotation shaft 7 mounted in the containment case 2 by means of respective second bearings 8.
  • the first support disc 3 has a first face 9 that bears a plurality of radial rotor stages 10, 11, 12, 13 radially arranged in succession one after the other.
  • Each of said radial rotor stages 10, 11, 12, 13 comprises a plurality of blades 14 arranged in an array along a circular path concentric with the rotation axis "X-X".
  • the circular arrays of blades of the different stages 10, 11, 12, 13 form concentric rings.
  • the second support disc 4 has a respective first face 15 that bears a plurality of radial rotor stages 16, 17, 18, 19 radially arranged in succession one after the other.
  • Each of said radial rotor stages 16, 17, 18, 19 comprises a plurality of blades 20 arranged in an array along a circular path concentric with the rotation axis "X-X".
  • the circular arrays of blades of the different stages 16, 17, 18, 19 form concentric rings.
  • the first face 9 of the first support disc 3 is placed across from the first face 15 of the second support disc 4 and the blades 14 of the first disc 3 are radially alternated with the blades 20 of the second disc 4.
  • the radial rotor stages 10, 11, 12, 13 of the first support disc 3 are alternated along radial directions with respect to the radial rotor stages 16, 17, 18, 19 of the second support disc 4.
  • the blades 14 of the first support disc 3 terminate in proximity to the first face 15 of the second support disc 4 and the blades 20 of the second support disc 4 terminate in proximity to the first face 9 of the first support disc 3.
  • each of the abovementioned blades 14, 20 of the radial rotor stages 10, 11, 12, 13, 16, 17, 18, 19 are extended substantially parallel to said rotation axis "X-X", so that they are capable of working under the action of a flow of a work fluid of centrifugal radial type, i.e. mainly directed from the rotation axis "X-X" towards the outside.
  • the first support disc 3 has a second face 21, opposite the first 9, which bears two annular appendices (or reliefs) 22. As is visible in figure 3 , the annular appendices 22 form concentric rings coaxial with the rotation axis "X-X".
  • the second support disc 4 has a second face 23, opposite the first 15, which bears two annular appendices (or reliefs) 24. Analogous to the first support disc 3, the annular appendices 24 of the second support disc 4 form concentric rings coaxial with the rotation axis "X-X".
  • the first and the second rotation shaft 5, 6 are aligned along the common rotation axis "X-X" and are each extended from the second face 21, 23 of the respective support disc 3, 4 along opposite directions.
  • the first support disc 3 has, in a zone radially internal with respect to the radial rotor stages 10, 11, 12, 13 and radially external with respect to its rotation shaft 5, through induction channels 25 which traverse the thickness of the first support disc 3 along a substantially axial direction and are opened both on the first face 9 and on the second face 15.
  • said through induction channels 25 are arranged along a circular path coaxial with the rotation axis "X-X" and are delimited by radially opposite portions of the first support disc 3 and by a plurality of induction rotor blades 26 which form an axial rotor stage 27.
  • the axial rotor stage 27 is defined by a circular opening which is extended along the abovementioned circular path, within which the induction rotor blades 26 are placed which connect radially opposite portions of the first support disc 3.
  • the second support disc 4 has, in a radially internal zone with respect to the radial rotor stages 16, 17, 18, 19 and radially external zone with respect to its rotation shaft 7, through induction channels 28 which cross through the thickness of the second support disc 4 along a substantially axial direction and are opened both on the first face 15 and on the second face 23.
  • said through induction channels 28 are arranged along a circular path coaxial with the rotation axis "X-X" and are delimited by radially opposite portions of the second support disc 4 and by a plurality of induction rotor blades 29 which form an axial rotor stage 30.
  • the axial rotor stage 30 is defined by a circular opening that is extended along the abovementioned circular path, within which the induction rotor blades 29 are placed which connect radially opposite portions of the second support disc 4.
  • the two discs 3, 4, including the induction rotor blades 26, 29, are preferably made in a single piece, e.g. by means of three-dimensional sintering techniques.
  • the leading edge and the trailing edge of each of the abovementioned blades 26, 29 of the axial rotor stages 27, 30 are extended substantially radially (along radial directions with respect to said rotation axis "X-X"), so that they are capable of working under the action of a flow of the work fluid of axial type, i.e. mainly directed parallel to the rotation axis "X-X".
  • the leading edge of each of the induction blades 26, 29 faces the second face 21, 23 of the respective disc 3, 4 and the trailing edge faces the first face 9, 15 of the respective disc 3, 4.
  • the two first faces 9, 15 together delimit an expansion volume 31 of the work fluid which enters into said expansion volume 31 through the through induction channels 25, 28 of the two support discs 3, 4 and is radially expanded away from the rotation axis "X-X" through the radial rotor stages 10, 11, 12, 13, 16, 17, 18, 19 of said two discs 3, 4 and exits at a radially peripheral portion of the abovementioned discs 3, 4.
  • the orientation of the blades 14 of the radial rotor stages 10, 11, 12, 13 of the first disc 3 is opposite the orientation of the blades 20 of the radial rotor stages 16, 17, 18, 19 of the second disc 4, so that the expansion of the work fluid causes the rotation in opposite senses of said two discs 3, 4.
  • the ratio between the radial height of each induction rotor blade 26, 29 and the diameter of the support discs 3, 4 is comprised between about 0.007 and about 0.050. In the illustrated embodiment, such ratio is for example equal to about 0.025.
  • the expansion turbine 1 also comprises a first portion 32 that is fixed (with respect to the containment case 2) provided with a plurality of fixed induction openings 33 axially side-by-side the induction rotor blades 26 of the first support disc 3 and placed on the side of the second face 21 of said first disc 3.
  • the first fixed portion 32 can be an integral part of the case 2 or stably mounted in the case 2.
  • the first fixed portion 32 has an annular passage coaxial with the rotation axis "X-X" and a plurality of stator blades 34, situated in said annular passage, divide it into the abovementioned fixed induction openings 33.
  • the stator blades 34 are extended substantially radially (along radial directions with respect to said rotation axis "X-X").
  • the stator blades 34 form an axial stator stage 35 which together with the respective axial rotor stage 27 define an axial induction stage for the first support disc 3.
  • a second fixed portion 36 flanks the second face 23 of the second support disc 4.
  • the second fixed portion 36 is provided with a plurality of fixed induction openings 37 axially side-by-side the induction rotor blades 29 of the second support disc 4.
  • the second fixed portion 36 can be an integral part of the case 2 or stably mounted in the case 2.
  • the second fixed portion 36 has an annular passage coaxial with the rotation axis "X-X” and a plurality of stator blades 38, situated in said annular passage, divide it into the abovementioned fixed induction openings 37.
  • the stator blades 38 are extended substantially radially (along radial directions with respect to said rotation axis "X-X").
  • the stator blades 38 form an axial stator stage 39 which together with the respective axial rotor stage 30 define an axial induction stage for the second support disc 4.
  • the first fixed portion 32 is radially extended away from the rotation axis "X-X" (like a fixed disc) and has a respective face 40 placed across the annular appendices 22 of the first support disc 3. From said face 40 of the first fixed portion 32, two annular walls 41 coaxial with the rotation axis "X-X" (see figure 4 ) are extended. Each annular wall 41 is axially extended nearly to the second face 21 of the first support disc 3 at a respective annular appendage 22.
  • the annular appendage 22 remains arranged in a radially more internal position with respect to the respective annular wall 41.
  • An end 42 of the annular wall 41 lies in proximity to the annular appendage 22 and bears a sliding gasket 43 which remains radially interposed between said end 42 and said annular appendage 22.
  • the sliding gasket 43 lies in contact with and slides on the annular appendage 22, ensuring the seal of the work fluid.
  • the radially successive annular walls 41 delimit, together with the face 40 of the first fixed portion 32 and the second face 21 of the first support disc 3, a first annular chamber 44.
  • the second fixed portion 36 is structurally similar to the first fixed portion 32.
  • a respective face 46 is placed across from the annular appendices 24 of the second support disc 4. From said face 46, two annular walls 47 are extended (as much as the annular appendices 24) coaxial with the rotation axis "X-X". Each annular wall 47 is axially extended up to nearly the second face 23 of the second support disc 4 at a respective annular appendage 24.
  • the annular appendage 24 remains arranged in a radially more internal position with respect to the respective annular wall 47.
  • one end 42 of the annular wall 47 lies in proximity to the annular appendage 24 and bears a sliding gasket 43 which remains radially interposed between said end 42 and said annular appendage 24.
  • the sliding gasket 43 lies in contact with and slides on the annular appendage 24, ensuring the seal of the work fluid.
  • the radially successive annular walls 47 delimit, together with the face 46 of the first fixed portion 36 and the second face 23 of the second support disc 4, a second annular chamber 48.
  • both the first and the second fixed portion 32, 36 have a hole 50 for the passage of the respective rotation shaft 5, 7 ( figure 4 ).
  • both the support discs 3, 4 have compensation through openings 52 obtained in radially internal positions with respect to the through induction channels 25, 28.
  • the illustrated turbine 1 also comprises two auxiliary axial stages 53, each situated at a zone radially external with respect to the respective support disc 3, 4.
  • auxiliary axial stages 53 each situated at a zone radially external with respect to the respective support disc 3, 4.
  • the auxiliary axial stage 53 comprises a plurality of auxiliary rotor blades 54 mounted on a peripheral edge of the respective support disc 3, 4 and a plurality of auxiliary stator blades 55 mounted on a support element 2a making up part of a radially external portion of the containment case 2 and placed in a radially external position with respect to the support disc 3, 4.
  • the auxiliary rotor blades 54 are radially extended from the peripheral edge of the respective disc 3, 4 towards the outside, as is visible in figure 3 .
  • the auxiliary stator blades 55 are radially extended from the support element 56 and converge towards the rotation axis "X-X".
  • auxiliary stator blades 55 Radially internal terminal ends of the auxiliary stator blades 55 are borne by a radially internal ring 56.
  • ring 56 is situated at the peripheral edge of the respective support disc 3, 4 and faces the first face 9, 15 of said disc 3, 4.
  • Each of the support discs 3, 4 has an auxiliary annular appendage 57 projecting from the respective first face 9, 15, coaxial with the rotation axis "X-X" and placed in a position radially external with respect to the radial rotor stages 10-13, 16-19.
  • the radially internal ring 56 lies in a position that is radially external with respect to the auxiliary annular appendage 57 and in proximity to said auxiliary annular appendage 57 and bears a sliding gasket that remains radially interposed between said internal ring 56 and said auxiliary annular appendage 57.
  • the sliding gasket lies in contact with and slides on the auxiliary annular appendage 57, ensuring the seal of the work fluid.
  • the containment case 2 delimits a first induction chamber 58 arranged on one side of the first fixed portion 32 opposite the respective first support disc 3.
  • the first induction chamber 58 is annular and faces and is in fluid communication with the fixed induction openings 33 of the first fixed portion 32.
  • the first induction chamber 58 is also in fluid communication with a source 59 of work fluid (e.g. a circuit placed upstream of the turbine 1) intended to be expanded in the turbine 1.
  • the containment case 2 delimits a second induction chamber 60 arranged on one side of the second fixed portion 36 opposite the respective second support disc 4.
  • the second induction chamber 60 is annular and faces and is in fluid communication with the fixed induction openings 37 of the second fixed portion 36.
  • the second induction chamber 60 is in fluid communication with the source 59 of work fluid intended to be expanded in the turbine 1.
  • the work fluid coming from the source 59 enters into the induction chambers 58, 60 through suitable ducts 61 and from these flows axially through the fixed induction openings 33, 37, the stator blades 34, 38 of the fixed portions 32, 36 and through the induction rotor blades 26, 29 of the support discs 3, 4.
  • the speed of the work fluid through the induction channels 25, 28 is for example comprised between about 40 m/s and about 45 m/s.
  • the work fluid then flows through the radial rotor stages 10-13, 16-19 of the first and of the second disc 3, 4 and subsequently through the auxiliary axial stages 53.
  • the work fluid exiting from the auxiliary axial stage 53 is then conveyed into a volume 62 (preferably a volute) delimited by the containment case 2 towards a circuit placed downstream of the turbine 1.
  • FIG 2 has only one support disc 3. Elements analogous to those illustrated and described for the counter-rotating turbine of figure 1 will not be described again in detail herein; for the sake of simplicity, the same reference numbers are used for these elements.
  • the support disc 3 has a first face 9 which bears a plurality of radial rotor stages 10, 11, 12 radially arranged in succession one after the other.
  • stator stages 64, 65 Across from the first face 9, a wall 63 of the containment case 2 is placed that bears a plurality of radial stator stages 64, 65 arranged radially in succession one after the other.
  • Each of the stator stages 64, 65 comprises an array of blades 66 arranged in succession along a respective circular path.
  • the stator stages 64, 65 are radially alternated with the rotor stages 10, 11, 12.
  • the expansion volume 31 is delimited in this embodiment between the support disc 3 and the wall 63 of the containment case 2.
  • the structure of the single support disc 3 is substantially the same as the first support disc 3 described and illustrated for the counter-rotating turbine of figure 1 .
  • the turbine of figure 2 Analogous to the counter-rotating turbine of figure 1 , the turbine of figure 2 has two annular walls 41 having ends 42 lying in proximity to annular appendices 22 extended from the second face 21 of the support disc 3 in order to delimit an annular chamber 44.
  • the turbine of figure 2 comprises an auxiliary axial stage 53 comprising a plurality of auxiliary rotor blades 54 mounted on a peripheral edge of the support disc 3 and a plurality of auxiliary stator blades 55 mounted fixed on a support element 56 making up part of a radially external portion of the containment case 2.
  • the turbine of figure 2 comprises the induction channels 25 obtained in the support disc 3 and provided with induction rotor blades 26 defining the axial rotor stage 27.
  • the turbine of figure 2 comprises the fixed induction openings 33 axially side-by-side the induction rotor blades 26 of the support disc 3 and placed on the side of the second face 21 of said disc 3.
  • the fixed induction openings 33 have the induction stator blades 34 defining the axial stator stage 35.
  • the turbine of figure 2 comprises a nose 67 (e.g. a kind of pointed element) coaxial with the rotation axis "X-X" and situated on the side of the second face 21 of the support disc 3.
  • the nose 67 peripherally bears the induction stator blades 34 and is directed towards an axial inlet 68.
  • the nose 67 deflects the flow entering from the axial inlet 68 towards the fixed induction openings 33 that surround it.

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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)

Claims (15)

  1. Zentrifugal-Radialturbine, umfassend:
    ein festes Aufnahmegehäuse (2);
    wenigstens eine Tragescheibe (3, 4) mit einer ersten Fläche (9, 15), welche wenigstens eine radiale Rotorstufe (10, 11, 12, 13, 16, 17, 18, 19) lagert, welche durch ein Feld von Schaufeln (14, 20) gebildet ist, welche in einer Abfolge entlang eines jeweiligen Zirkulationspfads angeordnet sind;
    wenigstens eine Rotationswelle (5, 7), welche integral mit der jeweiligen Scheibe (3, 4) ist;
    wobei die wenigstens eine radiale Rotorstufe (10, 11, 12, 13, 16, 17, 18, 19) in einem Expansionsvolumen für ein Arbeitsfluid platziert ist;
    wobei die wenigstens eine Scheibe (3, 4) Durchgangs-Induktionskanäle (25, 28) aufweist, welche in einer radial externen Position bezüglich der jeweiligen Welle (5, 7) und in einer radial internen Position bezüglich der wenigstens einen radialen Rotorstufe (10, 11, 12, 13, 16, 17, 18, 19) platziert sind;
    wobei die wenigstens eine Scheibe (3, 4) frei ist, zusammen mit der jeweiligen Welle (5, 7) um eine Rotationsachse (X-X) unter der Wirkung des Arbeitsfluids zu rotieren, welches durch die Durchgangs-Induktionskanäle (25, 28) eintritt;
    dadurch gekennzeichnet, dass an den jeweiligen Durchgangs-Induktionskanälen (25, 28) die wenigstens eine Scheibe (3, 4) eine Mehrzahl von Induktions-Rotorschaufeln (26, 29) von wenigstens einer jeweiligen axialen Rotorstufe (27, 30) umfasst.
  2. Turbine nach dem vorhergehenden Anspruch, wobei die Induktionskanäle (25, 28) wenigstens teilweise von den Induktions-Rotorschaufeln (26, 29) begrenzt sind.
  3. Turbine nach einem der vorhergehenden Ansprüche, wobei die Induktions-Rotorschaufeln (26, 29) integral in der wenigstens einen Tragescheibe (3, 4) erhalten sind.
  4. Turbine nach einem der vorhergehenden Ansprüche, wobei das Verhältnis zwischen der radialen Höhe von jeder Induktions-Rotorschaufel (26, 29) und dem Durchmesser der wenigstens einen Tragescheibe (3, 4) zwischen etwa 0,007 und etwa 0,05 enthalten ist.
  5. Turbine nach einem der vorhergehenden Ansprüche, wobei eine axiale transversale Geschwindigkeit des Arbeitsfluids durch die Induktionskanäle (25, 28) zwischen etwa 35 m/s und etwa 100 m/s, vorzugsweise zwischen etwa 40 m/s und 45 m/s, enthalten ist.
  6. Turbine nach einem der vorhergehenden Ansprüche, umfassend eine Mehrzahl von Induktions-Statorschaufeln (34, 38) der jeweiligen axialen Stufe (27, 35, 30, 39) Seite an Seite mit den Induktions-Rotorblättern (26, 29) der wenigstens einen Tragescheibe (3, 4) und an der Seite der zweiten Fläche (21, 23) der jeweiligen Tragescheibe (3, 4) gegenüber der ersten Fläche (9, 15) platziert.
  7. Turbine nach einem der vorhergehenden Ansprüche, umfassend wenigstens eine radiale Statorstufe (63, 66), welche bezüglich des Aufnahmegehäuses (2) befestigt und durch ein Feld von Schaufeln (66) gebildet ist, welche in Abfolge entlang eines jeweiligen kreisförmigen Pfads und in radial externer und/oder in radial interner Position bezüglich der wenigstens einen radialen Rotorstufe (10, 11, 12) angeordnet sind, wobei das Expansionsvolumen (31) zwischen der Tragescheibe (3) und dem Aufnahmegehäuse (2) begrenzt ist.
  8. Turbine nach dem vorhergehenden Anspruch, umfassend eine mit dem Aufnahmegehäuse (2) integrale Nase (67), welche an der Seite einer zweiten Fläche (21) der Tragescheibe (3) gegenüber der ersten Fläche (9) angeordnet und in einer Einlassleitung (68) platziert ist.
  9. Turbine nach dem vorhergehenden Anspruch, wenn Anspruch 7 von Anspruch 6 abhängt, wobei die Induktions-Statorschaufeln (34) umfänglich um die Nase (67) herum platziert sind.
  10. Turbine nach einem der Ansprüche 1 bis 6, wobei die Turbine vom gegenrotierenden Typ ist und eine erste Tragescheibe (3) und eine zweite Tragescheibe (4) umfasst, wobei die erste Scheibe (3) zu der zweiten Scheibe (4) weist, um das Expansionsvolumen (31) zu begrenzen, und wobei sich die Schaufeln (14) der ersten Scheibe (3) radial mit den Schaufeln (20) der zweiten Scheibe (4) abwechseln.
  11. Turbine nach einem der vorhergehenden Ansprüche, wobei die axiale Rotorstufe (27, 30) von einem Aktionstyp ist.
  12. Turbine nach einem der vorhergehenden Ansprüche, wobei die axiale Rotorstufe (27, 30) von einem Reaktionstyp ist.
  13. Turbine nach einem der vorhergehenden Ansprüche, wobei die Tragescheibe oder -scheiben (3, 4) Kompensations-Durchgangsöffnungen (52) aufweisen, welche in radial internen Positionen bezüglich der Durchgangs-Induktionskanäle (25, 28) erhalten sind, um den axialen Schub auf die Scheiben (3, 4) auszugleichen.
  14. Turbine nach einem der vorhergehenden Ansprüche, umfassend eine ringförmige Kammer (44, 48), welche konzentrisch und zu der zweiten Fläche der Tragescheibe oder jeder Tragescheibe (3, 4) weisend ist; wobei das befestigte Aufnahmegehäuse (2), welches die Tragescheibe oder -scheiben (3, 4) aufnimmt, ringförmige Wände (41, 47) umfasst, welche koaxial mit der Rotationsachse (X-X) sind und die ringförmige(n) Kammer(n) (44, 48) begrenzt.
  15. Vorrichtung zum Erzeugen von mechanischer und/oder elektrischer Energie, umfassend eine Turbine nach wenigstens einem der Ansprüche 1 bis 14.
EP15718087.8A 2014-03-21 2015-03-17 Zentrifugale radialturbine Not-in-force EP3119991B1 (de)

Applications Claiming Priority (2)

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ITMI20140487 2014-03-21
PCT/IB2015/051940 WO2015140707A1 (en) 2014-03-21 2015-03-17 Centrifugal radial turbine

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EP3119991B1 true EP3119991B1 (de) 2018-05-02

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EP (1) EP3119991B1 (de)
JP (1) JP2017519155A (de)
CN (1) CN106460517A (de)
CA (1) CA2943407A1 (de)
MX (1) MX2016012186A (de)
RU (1) RU2016140623A (de)
WO (1) WO2015140707A1 (de)

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ITUA20162126A1 (it) * 2016-03-30 2017-09-30 Exergy Spa Metodo per la costruzione di dischi palettati per turbomacchine radiali e disco palettato ottenuto tramite tale metodo
ITUA20162125A1 (it) 2016-03-30 2017-09-30 Exergy Spa Turbomacchina radiale con compensazione della spinta assiale

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DE208040C (de) *
GB311586A (en) 1928-06-30 1929-05-16 Asea Ab Improvements in steam turbines
GB396352A (en) * 1932-05-09 1933-08-03 Asea Ab Improvements in radial flow steam or gas turbines having axially displaced bladings
CH253571A (de) * 1945-12-20 1948-03-15 Svenska Turbinfab Ab Gasturbinenaggregat.
CN1193686A (zh) * 1997-03-13 1998-09-23 张春智 透平膨胀喷射汽轮机
DE112005002547A5 (de) * 2004-11-02 2007-09-13 Alstom Technology Ltd. Optimierte Turbinenstufe einer Turbinenanlage sowie Auslegungsverfahren
CN101899994B (zh) * 2010-05-28 2013-04-10 大保辉彦 半径流汽轮机
ITBS20120008A1 (it) 2012-01-20 2013-07-21 Turboden Srl Metodo e turbina per espandere un fluido di lavoro organico in un ciclo rankine

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EP3119991A1 (de) 2017-01-25
US20170107818A1 (en) 2017-04-20
CN106460517A (zh) 2017-02-22
MX2016012186A (es) 2017-05-01
RU2016140623A (ru) 2018-04-23
WO2015140707A1 (en) 2015-09-24
JP2017519155A (ja) 2017-07-13
CA2943407A1 (en) 2015-09-24

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