EP3119991B1 - Centrifugal radial turbine - Google Patents
Centrifugal radial turbine Download PDFInfo
- 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
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- 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
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- 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
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- 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
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- 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
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- 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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Description
- 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). Preferably but not exclusively, the present invention refers to the centrifugal radial expansion turbines of counter-rotating type. Preferably but not exclusively, 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). In the ORC apparatuses, work fluids of organic type are used in place of the conventional water/steam system.
- Centrifugal radial turbines are known that are used for the expansion of steam or organic fluids.
- For example, 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. In a first section of the turbine, defined at high pressure, a first expansion of the work fluid is provided in a substantially radial direction. In a second section, defined at low pressure, 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.
- For example, the public document
GB 311,586 - Also known are counter-rotating centrifugal radial turbines in which the induction of the steam between the discs occurs through ducts obtained in the rotation shafts integral with said discs. The public document
DE-208040C discloses also a disc with admission through channels placed in a radially outer position with respect to the respective shaft and radially inner with respect to the rotor radial stages. - In such context, 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 Applicant first of all observed that the induction passages obtained in the discs, for example those described in the abovementioned document
GB 311,586 - The Applicant also observed that the fact that such passages rotate with the respective disc still causes - even if limiting the crossing speeds as mentioned above - considerable load losses that negatively affect the efficiency of the entire turbine.
- The Applicant also observed that the 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 offigure 1 andfigure 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. - In such context, 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.
- More generally, the Applicant has set at least one of the following objects/improvements with regard to the prior art:
- ▪ improving the efficiency of the phase of induction of the work fluid between the rotor and stator blades (in the case of single-disc centrifugal radial turbines) or between the rotor discs (for counter-rotating centrifugal radial turbines);
- ▪ increasing the structural strength of the disc or discs;
- ▪ simplifying the induction of the work fluid even with high flow rates, as in the case of expansion of organic fluids in ORC cycles;
- ▪ allowing the use of the turbine, in particular counter-rotating, with any work fluid (e.g. organic fluids or water).
- 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.
- In particular, the indicated objectives, at least one of the above-listed objects and still others are substantially achieved by a centrifugal radial turbine according to one or more of the set of claims.
- Aspects of the invention are illustrated hereinbelow.
- According to one aspect, the present invention regards a centrifugal radial turbine, comprising:
- a fixed containment case;
- at least one support disc having a first face bearing at least one radial rotor stage formed by an array of blades arranged in succession along a respective circular path;
- at least one rotation shaft integral with the respective disc;
- in which said at least one radial rotor stage is situated in an expansion volume for a work fluid;
- in which said at least one disc has through induction channels situated in radially external position with respect to the respective shaft and radially internal position with respect to said at least one radial rotor stage;
- in which said at least one disc is free to rotate together with the respective shaft around a rotation axis under the action of the work fluid entering through the through induction channels;
- characterized in that, at the respective through induction channels, said at least one disc comprises a plurality of induction rotor blades of at least one respective axial rotor stage.
- According to one aspect, the present invention regards a centrifugal radial turbine, comprising:
- a fixed containment case;
- a support disc having a first face bearing at least one radial rotor stage formed by an array of blades arranged in succession along a respective circular path;
- a rotation shaft integral with the respective disc;
- at least one radial stator stage fixed with respect to the containment case and formed by an array of blades arranged in succession along a respective circular path and in a radially external and/or radially internal position with respect to said at least one radial rotor stage,
- in which an expansion volume is delimited between the support disc and the containment case;
- in which said at least one disc has through induction channels situated in radially external position with respect to the respective shaft and radially internal position with respect to said at least one radial rotor stage;
- in which said at least one disc is free to rotate together with the respective shaft around a rotation axis under the action of the work fluid entering through the through induction channels;
- characterized in that, at the respective through induction channels, said at least one disc comprises a plurality of induction rotor blades of at least one respective axial rotor stage.
- According to one aspect, the present invention regards a counter-rotating centrifugal radial turbine, comprising:
- a first support disc having a first face bearing at least one radial rotor stage formed by an array of blades arranged in succession along a respective circular path and with a first orientation;
- a first rotation shaft integral with the first disc;
- a second support disc comprising a first face bearing at least one radial rotor stage formed by an array of blades arranged in succession along a respective circular path and with a second orientation, opposite the first;
- a second rotation shaft integral with the second disc;
- in which the first disc faces the second disc in order to delimit an expansion volume and the blades of the first disc are radially alternated with the blades of the second disc;
- in which each of the discs has through induction channels situated in radially external position with respect to the respective shaft and radially internal position with respect to the arrays of blades of the radial rotor stages;
- in which the first and the second disc are free to rotate together with the respective shafts around a common rotation axis and rotate in opposite directions under the action of a work fluid entering through the induction channels;
- characterized in that, at the respective through induction channels, each of the discs comprises a plurality of induction rotor blades of at least one respective axial rotor stage.
- 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 inlet of the work fluid into the expansion volume (comprised between the disc and the case or between the first and the second disc if counter-rotating) occurs through the induction channels situated at a radially internal portion of said disc(s). The fluid is moved, expanding outward, away from the rotation axis, and exits at a radially peripheral portion of the abovementioned disc(s).
- In one aspect, the induction channels are at least partially delimited by said induction rotor blades.
- In one aspect, the adjacent induction channels are separated by one of said induction rotor blades.
- In one aspect, the induction channels and the induction rotor blades are arranged in succession along at least one circular path coaxial with the rotation axis.
- In a preferred embodiment, 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 Applicant has verified that the solution according to the invention allows introducing the steam by means of an axial expansion stage that allows carrying out such process in an efficient manner and with much more limited passage channels on the disc(s) with respect to those of the prior art.
- In one aspect, the induction rotor blades are integrally obtained in the respective support disc. This ensures greater solidity and structural strength of the disc(s).
- In one aspect, 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.
- In one aspect, 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.
- With radial height it is intended the extension along a radial direction of an induction rotor blade. With 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.
- In one aspect, 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.
- In one aspect, 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.
- In one aspect, 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.
- In one aspect, the induction stator blades delimit the fixed induction openings.
- In one aspect, the induction stator blades are housed in the fixed induction openings.
- In one aspect, each of the fixed induction openings houses at least one induction stator blade.
- In one embodiment, 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.
- In one embodiment, 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.
- In one aspect, 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.
- In one aspect, the axial rotor stage is of reaction type.
- In one aspect, 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.
- In one aspect, the turbine comprises an annular chamber that is concentric and facing the second face of the support disc or of each support disc.
- In one aspect, 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.
- In one aspect, 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).
- In one aspect, the turbine comprises a plurality of sliding gaskets, each interposed between one end of an annular wall and the respective annular appendage.
- In one aspect, said sliding gaskets are mounted on the ends of the annular walls and slide against said annular appendices.
- In a different aspect, said sliding gaskets could be mounted on the annular appendices and slide against the ends of the annular walls.
- In one aspect, 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.
- In one aspect, 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.
- In one aspect, 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.
- In one aspect, said support element is part of a radially external portion of the containment case.
- In one aspect, 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.
- In one aspect, said annular appendage is sealingly engaged with a radially internal ring bearing radially internal ends of the auxiliary stator blades.
- In one aspect, the turbine comprises a sliding gasket interposed between the radially internal ring and the respective annular appendage.
- In one aspect, the turbine comprises a nose integral with the containment case and situated in the inlet duct.
- In one aspect, the nose is placed on the side of a second face of the support disc opposite the first face.
- In one aspect, the nose is part of the fixed portion provided with the fixed induction openings.
- In one aspect, the fixed induction openings and, preferably, the induction stator blades are situated circumferentially around the nose.
- In one aspect, 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.
- In a different aspect, the turbine can be used in open-cycle or closed-cycle steam plants.
- Further characteristics and advantages will be clearer from the detail description of preferred but not exclusive embodiments of a centrifugal radial turbine in accordance with the present invention.
- Such description will be set forth hereinbelow with reference to the set of drawings, provided only as a non-limiting example, in which:
- ▪
figure 1 is a half-section view along an axial plane of a centrifugal radial turbine according to a first embodiment of the present invention; - ▪
figure 2 is a half-section view along an axial plane of a centrifugal radial turbine according to a different embodiment of the present invention; - ▪
figure 3 is a front view of a support disc belonging to the turbines pursuant tofigures 1 or2 ; - ▪
figure 4 is a front view of a portion of the turbine offigure 1 ; and - ▪
figure 5 illustrates a detail of the turbine pursuant tofigures 1 or2 . - With reference to
figure 1 , 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. Preferably but not exclusively, 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 afirst support disc 3 and asecond support disc 4. Thesupport discs support case 2 around a common rotation axis "X-X". For such purpose, thefirst disc 3 is integral with a respectivefirst rotation shaft 5 mounted in thecontainment case 2 by means offirst bearings 6. Thesecond disc 4 is integral with a respectivesecond rotation shaft 7 mounted in thecontainment case 2 by means of respectivesecond bearings 8. - The
first support disc 3 has afirst 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 ofblades 14 arranged in an array along a circular path concentric with the rotation axis "X-X". In other words, the circular arrays of blades of thedifferent stages - The
second support disc 4 has a respectivefirst 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 ofblades 20 arranged in an array along a circular path concentric with the rotation axis "X-X". In other words, the circular arrays of blades of thedifferent stages - The
first face 9 of thefirst support disc 3 is placed across from thefirst face 15 of thesecond support disc 4 and theblades 14 of thefirst disc 3 are radially alternated with theblades 20 of thesecond disc 4. In other words, the radial rotor stages 10, 11, 12, 13 of thefirst support disc 3 are alternated along radial directions with respect to the radial rotor stages 16, 17, 18, 19 of thesecond support disc 4. Theblades 14 of thefirst support disc 3 terminate in proximity to thefirst face 15 of thesecond support disc 4 and theblades 20 of thesecond support disc 4 terminate in proximity to thefirst face 9 of thefirst support disc 3. - The leading edge and the trailing edge of each of the
abovementioned blades - The
first support disc 3 has asecond face 21, opposite the first 9, which bears two annular appendices (or reliefs) 22. As is visible infigure 3 , theannular appendices 22 form concentric rings coaxial with the rotation axis "X-X". - Also the
second support disc 4 has asecond face 23, opposite the first 15, which bears two annular appendices (or reliefs) 24. Analogous to thefirst support disc 3, theannular appendices 24 of thesecond support disc 4 form concentric rings coaxial with the rotation axis "X-X". - The first and the
second rotation shaft second face respective support disc - 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 itsrotation shaft 5, throughinduction channels 25 which traverse the thickness of thefirst support disc 3 along a substantially axial direction and are opened both on thefirst face 9 and on thesecond face 15. - As is visible in
figure 3 , said throughinduction channels 25 are arranged along a circular path coaxial with the rotation axis "X-X" and are delimited by radially opposite portions of thefirst support disc 3 and by a plurality ofinduction rotor blades 26 which form anaxial rotor stage 27. In other words, theaxial rotor stage 27 is defined by a circular opening which is extended along the abovementioned circular path, within which theinduction rotor blades 26 are placed which connect radially opposite portions of thefirst 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 itsrotation shaft 7, throughinduction channels 28 which cross through the thickness of thesecond support disc 4 along a substantially axial direction and are opened both on thefirst face 15 and on thesecond face 23. - In a manner structurally identical to the
first support disc 3, said throughinduction channels 28 are arranged along a circular path coaxial with the rotation axis "X-X" and are delimited by radially opposite portions of thesecond support disc 4 and by a plurality ofinduction rotor blades 29 which form anaxial rotor stage 30. In other words, theaxial rotor stage 30 is defined by a circular opening that is extended along the abovementioned circular path, within which theinduction rotor blades 29 are placed which connect radially opposite portions of thesecond support disc 4. - The two
discs induction rotor blades abovementioned blades induction blades second face respective disc first face respective disc - The two
first faces expansion volume 31 of the work fluid which enters into saidexpansion volume 31 through the throughinduction channels support discs discs abovementioned discs - The orientation of the
blades 14 of the radial rotor stages 10, 11, 12, 13 of thefirst disc 3 is opposite the orientation of theblades 20 of the radial rotor stages 16, 17, 18, 19 of thesecond disc 4, so that the expansion of the work fluid causes the rotation in opposite senses of said twodiscs - Preferably, the ratio between the radial height of each
induction rotor blade support discs - 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 fixedinduction openings 33 axially side-by-side theinduction rotor blades 26 of thefirst support disc 3 and placed on the side of thesecond face 21 of saidfirst disc 3. The first fixedportion 32 can be an integral part of thecase 2 or stably mounted in thecase 2. As is visible infigure 4 , the first fixedportion 32 has an annular passage coaxial with the rotation axis "X-X" and a plurality ofstator blades 34, situated in said annular passage, divide it into the abovementioned fixedinduction openings 33. Thestator blades 34 are extended substantially radially (along radial directions with respect to said rotation axis "X-X"). Thestator blades 34 form anaxial stator stage 35 which together with the respectiveaxial rotor stage 27 define an axial induction stage for thefirst support disc 3. - A second fixed
portion 36 flanks thesecond face 23 of thesecond support disc 4. The second fixedportion 36 is provided with a plurality of fixedinduction openings 37 axially side-by-side theinduction rotor blades 29 of thesecond support disc 4. The second fixedportion 36 can be an integral part of thecase 2 or stably mounted in thecase 2. Analogous to the first fixedportion 32, the second fixedportion 36 has an annular passage coaxial with the rotation axis "X-X" and a plurality ofstator blades 38, situated in said annular passage, divide it into the abovementioned fixedinduction openings 37. Thestator blades 38 are extended substantially radially (along radial directions with respect to said rotation axis "X-X"). Thestator blades 38 form anaxial stator stage 39 which together with the respectiveaxial rotor stage 30 define an axial induction stage for thesecond support disc 4. - The first fixed
portion 32 is radially extended away from the rotation axis "X-X" (like a fixed disc) and has arespective face 40 placed across theannular appendices 22 of thefirst support disc 3. From saidface 40 of the first fixedportion 32, twoannular walls 41 coaxial with the rotation axis "X-X" (seefigure 4 ) are extended. Eachannular wall 41 is axially extended nearly to thesecond face 21 of thefirst support disc 3 at a respectiveannular appendage 22. - As is better visible in the detail of
figure 5 , theannular appendage 22 remains arranged in a radially more internal position with respect to the respectiveannular wall 41. Anend 42 of theannular wall 41 lies in proximity to theannular appendage 22 and bears a slidinggasket 43 which remains radially interposed between saidend 42 and saidannular appendage 22. The slidinggasket 43 lies in contact with and slides on theannular appendage 22, ensuring the seal of the work fluid. - The radially successive
annular walls 41 delimit, together with theface 40 of the first fixedportion 32 and thesecond face 21 of thefirst support disc 3, a firstannular chamber 44. - The second fixed
portion 36 is structurally similar to the first fixedportion 32. Arespective face 46 is placed across from theannular appendices 24 of thesecond support disc 4. From saidface 46, twoannular walls 47 are extended (as much as the annular appendices 24) coaxial with the rotation axis "X-X". Eachannular wall 47 is axially extended up to nearly thesecond face 23 of thesecond support disc 4 at a respectiveannular appendage 24. - The
annular appendage 24 remains arranged in a radially more internal position with respect to the respectiveannular wall 47. In mirrored manner with respect to that represented infigure 5 , oneend 42 of theannular wall 47 lies in proximity to theannular appendage 24 and bears a slidinggasket 43 which remains radially interposed between saidend 42 and saidannular appendage 24. The slidinggasket 43 lies in contact with and slides on theannular appendage 24, ensuring the seal of the work fluid. - The radially successive
annular walls 47 delimit, together with theface 46 of the first fixedportion 36 and thesecond face 23 of thesecond support disc 4, a secondannular chamber 48. - In the illustrated embodiment, both the first and the second fixed
portion hole 50 for the passage of therespective rotation shaft 5, 7 (figure 4 ). - In addition, both the
support discs openings 52 obtained in radially internal positions with respect to the throughinduction channels - The illustrated turbine 1 also comprises two auxiliary
axial stages 53, each situated at a zone radially external with respect to therespective support disc stages 53, since these are structurally identical. - The auxiliary
axial stage 53 comprises a plurality ofauxiliary rotor blades 54 mounted on a peripheral edge of therespective support disc auxiliary stator blades 55 mounted on a support element 2a making up part of a radially external portion of thecontainment case 2 and placed in a radially external position with respect to thesupport disc - The
auxiliary rotor blades 54 are radially extended from the peripheral edge of therespective disc figure 3 . Theauxiliary stator blades 55 are radially extended from thesupport element 56 and converge towards the rotation axis "X-X". - Radially internal terminal ends of the
auxiliary stator blades 55 are borne by a radiallyinternal ring 56.Such ring 56 is situated at the peripheral edge of therespective support disc first face disc - Each of the
support discs annular appendage 57 projecting from the respectivefirst face internal ring 56 lies in a position that is radially external with respect to the auxiliaryannular appendage 57 and in proximity to said auxiliaryannular appendage 57 and bears a sliding gasket that remains radially interposed between saidinternal ring 56 and said auxiliaryannular appendage 57. The sliding gasket lies in contact with and slides on the auxiliaryannular appendage 57, ensuring the seal of the work fluid. - The
containment case 2 delimits afirst induction chamber 58 arranged on one side of the first fixedportion 32 opposite the respectivefirst support disc 3. Thefirst induction chamber 58 is annular and faces and is in fluid communication with the fixedinduction openings 33 of the first fixedportion 32. Thefirst induction chamber 58 is also in fluid communication with asource 59 of work fluid (e.g. a circuit placed upstream of the turbine 1) intended to be expanded in the turbine 1. Thecontainment case 2 delimits asecond induction chamber 60 arranged on one side of the second fixedportion 36 opposite the respectivesecond support disc 4. Thesecond induction chamber 60 is annular and faces and is in fluid communication with the fixedinduction openings 37 of the second fixedportion 36. Thesecond induction chamber 60 is in fluid communication with thesource 59 of work fluid intended to be expanded in the turbine 1. - During use, the work fluid coming from the
source 59 enters into theinduction chambers suitable ducts 61 and from these flows axially through the fixedinduction openings stator blades portions induction rotor blades support discs induction channels - The work fluid then flows through the radial rotor stages 10-13, 16-19 of the first and of the
second disc axial stages 53. The work fluid exiting from the auxiliaryaxial stage 53 is then conveyed into a volume 62 (preferably a volute) delimited by thecontainment case 2 towards a circuit placed downstream of the turbine 1. - The embodiment illustrated in
figure 2 has only onesupport disc 3. Elements analogous to those illustrated and described for the counter-rotating turbine offigure 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 afirst face 9 which bears a plurality of radial rotor stages 10, 11, 12 radially arranged in succession one after the other. - Across from the
first face 9, awall 63 of thecontainment 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 ofblades 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 thesupport disc 3 and thewall 63 of thecontainment case 2. - The structure of the
single support disc 3 is substantially the same as thefirst support disc 3 described and illustrated for the counter-rotating turbine offigure 1 . Analogous to the counter-rotating turbine offigure 1 , the turbine offigure 2 has twoannular walls 41 having ends 42 lying in proximity toannular appendices 22 extended from thesecond face 21 of thesupport disc 3 in order to delimit anannular chamber 44. - Analogous to the counter-rotating turbine of
figure 1 , also the turbine offigure 2 comprises an auxiliaryaxial stage 53 comprising a plurality ofauxiliary rotor blades 54 mounted on a peripheral edge of thesupport disc 3 and a plurality ofauxiliary stator blades 55 mounted fixed on asupport element 56 making up part of a radially external portion of thecontainment case 2. - Analogous to the counter-rotating turbine of
figure 1 , also the turbine offigure 2 comprises theinduction channels 25 obtained in thesupport disc 3 and provided withinduction rotor blades 26 defining theaxial rotor stage 27. - Analogous to the counter-rotating turbine of
figure 1 , also the turbine offigure 2 comprises the fixedinduction openings 33 axially side-by-side theinduction rotor blades 26 of thesupport disc 3 and placed on the side of thesecond face 21 of saiddisc 3. The fixedinduction openings 33 have theinduction stator blades 34 defining theaxial stator stage 35. - Unlike the counter-rotating turbine of
figure 1 , the turbine offigure 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 thesecond face 21 of thesupport disc 3. Thenose 67 peripherally bears theinduction stator blades 34 and is directed towards anaxial inlet 68. Thenose 67 deflects the flow entering from theaxial inlet 68 towards the fixedinduction openings 33 that surround it.
Claims (15)
- Centrifugal radial turbine, comprising:a fixed containment case (2);at least one support disc (3, 4) having a first face (9, 15) bearing at least one radial rotor stage (10, 11, 12, 13, 16, 17, 18, 19) formed by an array of blades (14, 20) arranged in succession along a respective circular path;at least one rotation shaft (5, 7) integral with the respective disc (3, 4);wherein said at least one radial rotor stage (10, 11, 12, 13, 16, 17, 18, 19) is situated in an expansion volume (31) for a work fluid;wherein said at least one disc (3, 4) has through induction channels (25, 28) situated in radially external position with respect to the respective shaft (5, 7) and radially internal position with respect to said at least one radial rotor stage (10, 11, 12, 13, 16, 17, 18, 19);wherein said at least one disc (3, 4) is free to rotate together with the respective shaft (5, 7) around a rotation axis (X-X) under the action of the work fluid entering through the through induction channels (25, 28);characterized in that, at the respective through induction channels (25, 28), said at least one disc (3, 4) comprises a plurality of induction rotor blades (26, 29) of at least one respective axial rotor stage (27, 30).
- Turbine according to the preceding claim, wherein the induction channels (25, 28) are at least partially delimited by said induction rotor blades (26, 29).
- Turbine according to one of the preceding claims, wherein the induction rotor blades (26, 29) are integrally obtained in said at least one support disc (3, 4).
- Turbine according to one of the preceding claims, wherein the ratio between the radial height of each induction rotor blade (26, 29) and the diameter of said at least one support disc (3, 4) is comprised between about 0.007 and about 0.05.
- Turbine according to one of the preceding claims, wherein an axial traversing speed of the work fluid through the induction channels (25, 28) is comprised between about 35 m/s and about 100 m/s, preferably between about 40 m/s and about 45 m/s.
- Turbine according to one of the preceding claims, comprising a plurality of induction stator blades (34, 38) of the respective axial stage (27, 35, 30, 39) side-by-side the induction rotor blades (26, 29) of said at least one support disc (3, 4) and placed to the side of a second face (21, 23) of the respective support disc (3, 4) opposite the first face (9, 15).
- Turbine according to one of the preceding claims, comprising at least one radial stator stage (63, 66) fixed with respect to the containment case (2) and formed by an array of blades (66) arranged in succession along a respective circular path and in radially external and/or radially internal position with respect to said at least one radial rotor stage (10, 11, 12), wherein the expansion volume (31) is delimited between the support disc (3) and the containment case (2).
- Turbine according to the preceding claim, comprising a nose (67) integral with the containment case (2), placed on the side of a second face (21) of the support disc (3) opposite the first face (9) and situated in an inlet duct (68).
- Turbine according to the preceding claim when claim 7 depends on claim 6, wherein the induction stator blades (34) are situated circumferentially around the nose (67).
- Turbine according to one of the claims from 1 to 6, wherein said turbine is of counter-rotating type and comprises a first support disc (3) and a second support disc (4), wherein the first disc (3) faces the second disc (4) in order to delimit the expansion volume (31) and the blades (14) of the first disc (3) are radially alternated with the blades (20) of the second disc (4).
- Turbine according to one of the preceding claims, wherein axial rotor stage (27, 30) is of action type.
- Turbine according to one of the preceding claims, wherein the axial rotor stage (27, 30) is of reaction type.
- Turbine according to one of the preceding claims, wherein the support disc or discs (3, 4) have compensation through openings (52) obtained in radially internal positions with respect to the through induction channels (25, 28), in order to balance the axial thrust on the discs (3, 4).
- Turbine according to one of the preceding claims, comprising an annular chamber (44, 48) that is concentric and facing the second face of the support disc or of each support disc (3, 4); wherein the fixed containment case (2) which houses the support disc or discs (3, 4) comprises annular walls (41, 47) coaxial with the rotation axis (X-X) and delimiting said annular chamber(s) (44, 48).
- Apparatus for generating mechanical and/or electrical energy comprising a turbine according to at least one of the claims from 1 to 14.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
ITMI20140487 | 2014-03-21 | ||
PCT/IB2015/051940 WO2015140707A1 (en) | 2014-03-21 | 2015-03-17 | Centrifugal radial turbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3119991A1 EP3119991A1 (en) | 2017-01-25 |
EP3119991B1 true EP3119991B1 (en) | 2018-05-02 |
Family
ID=50981685
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP15718087.8A Not-in-force EP3119991B1 (en) | 2014-03-21 | 2015-03-17 | Centrifugal radial turbine |
Country Status (8)
Country | Link |
---|---|
US (1) | US20170107818A1 (en) |
EP (1) | EP3119991B1 (en) |
JP (1) | JP2017519155A (en) |
CN (1) | CN106460517A (en) |
CA (1) | CA2943407A1 (en) |
MX (1) | MX2016012186A (en) |
RU (1) | RU2016140623A (en) |
WO (1) | WO2015140707A1 (en) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
ITUA20162125A1 (en) | 2016-03-30 | 2017-09-30 | Exergy Spa | Radial turbomachinery with axial thrust compensation |
ITUA20162126A1 (en) * | 2016-03-30 | 2017-09-30 | Exergy Spa | Method for the construction of bladed discs for radial turbomachinery and bladed disc obtained by this method |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE208040C (en) * | ||||
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 (en) * | 1945-12-20 | 1948-03-15 | Svenska Turbinfab Ab | Gas turbine unit. |
CN1193686A (en) * | 1997-03-13 | 1998-09-23 | 张春智 | Turbine expansion jet steam turbine |
DE112005002547A5 (en) * | 2004-11-02 | 2007-09-13 | Alstom Technology Ltd. | Optimized turbine stage of a turbine plant as well as design methods |
CN101899994B (en) * | 2010-05-28 | 2013-04-10 | 大保辉彦 | Semi-drain steam turbine |
ITBS20120008A1 (en) | 2012-01-20 | 2013-07-21 | Turboden Srl | METHOD AND TURBINE TO EXPAND AN ORGANIC WORKING FLUID IN A RANKINE CYCLE |
-
2015
- 2015-03-17 RU RU2016140623A patent/RU2016140623A/en not_active Application Discontinuation
- 2015-03-17 MX MX2016012186A patent/MX2016012186A/en unknown
- 2015-03-17 EP EP15718087.8A patent/EP3119991B1/en not_active Not-in-force
- 2015-03-17 CA CA2943407A patent/CA2943407A1/en not_active Abandoned
- 2015-03-17 US US15/127,921 patent/US20170107818A1/en not_active Abandoned
- 2015-03-17 WO PCT/IB2015/051940 patent/WO2015140707A1/en active Application Filing
- 2015-03-17 JP JP2017500458A patent/JP2017519155A/en active Pending
- 2015-03-17 CN CN201580020886.9A patent/CN106460517A/en active Pending
Non-Patent Citations (1)
Title |
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None * |
Also Published As
Publication number | Publication date |
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WO2015140707A1 (en) | 2015-09-24 |
CA2943407A1 (en) | 2015-09-24 |
EP3119991A1 (en) | 2017-01-25 |
CN106460517A (en) | 2017-02-22 |
US20170107818A1 (en) | 2017-04-20 |
RU2016140623A (en) | 2018-04-23 |
MX2016012186A (en) | 2017-05-01 |
JP2017519155A (en) | 2017-07-13 |
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