A cascade process for the production of power from variable temperature heat sources, comprises: circulating a main working fluid selected from perfluorinated compounds (like Perfluoro-2-methylpentane/Perfluoro-i-hexane) in a main circuit (2) according to a main supercritical organic Rankine cycle, operatively coupling in a boiler (4) a variable temperature heat source (9) with the main working fluid of the main circuit (2) to heat and vaporize the main working fluid; circulating an auxiliary working fluid in an auxiliary circuit (3) according to an auxiliary Rankine cycle; thermally coupling in cascade the expanded main working fluid of the main Rankine cycle with the auxiliary working fluid of the auxiliary Rankine cycle, in order to cool the main working fluid and heating the vaporizing the auxiliary working fluid by heat transfer from the main Rankine cycle to the auxiliary Rankine cycle before the expansion of the auxiliary working fluid in an auxiliary expander (12).
F01K 23/04 - Ensembles fonctionnels caractérisés par plus d'une machine motrice fournissant de l'énergie à l'extérieur de l'ensemble, ces machines motrices étant entraînées par des fluides différents les cycles de ces machines motrices étant couplés thermiquement la chaleur de condensation provenant de l'un des cycles chauffant le fluide dans un autre cycle
F01K 7/32 - Ensembles fonctionnels de machines à vapeur caractérisés par l'emploi de types particuliers de machines motricesEnsembles fonctionnels ou machines motrices caractérisés par un circuit de vapeur, un cycle de fonctionnement ou des phases particuliersDispositifs de commande spécialement adaptés à ces systèmes, cycles ou phasesUtilisation de la vapeur soutirée ou de la vapeur d'évacuation pour le réchauffage de l'eau d'alimentation les machines motrices utilisant la vapeur à la pression critique ou hypercritique
F01K 25/08 - Ensembles fonctionnels ou machines motrices caractérisés par l'emploi de fluides énergétiques particuliers non prévus ailleursEnsembles fonctionnant selon un cycle fermé, non prévus ailleurs utilisant des vapeurs particulières
2.
METHOD FOR THE CONSTRUCTION OF STATOR AND ROTOR ELEMENTS OF TURBOMACHINES
The present invention relates to a method for the construction of rotor and stator elements of turbomachines, comprising: readying an ingot (1) of material to be machined; performing cuts in the ingot (1) so as to delimit blocks (10) of material interposed between portions of material intended to form blades (2) of the rotor or stator element; removing said blocks (10) freeing passages (11) between the portions of material; finishing the portions of material until the final shape is given to said blades (2) and to the passages (11). Execution of the cuts comprises: making first slots (6) on a first side (3) of the ingot (1), wherein the first slots (6) penetrate only partially through a thickness (t) of the ingot (1) to delimit into said ingot (1) a first half-block (7) of material joined to the ingot (1); making second slots (8) on a second side (4) of the ingot (1) opposite to the first side (3) to delimit a second half-block (9) into the ingot (1). The first slots (6) and the second slots (8) intersect each other so that the first and the second half-block (7, 9) define a single block (10) removable from the first side (3) and/or from the second side (4).
B23P 15/00 - Fabrication d'objets déterminés par des opérations non couvertes par une seule autre sous-classe ou un groupe de la présente sous-classe
B23H 9/10 - Usinage d'aubes de turbine ou de buses
B24C 1/04 - Méthodes d'utilisation de jet abrasif en vue d'effectuer un travail déterminéUtilisation d'équipements auxiliaires liés à ces méthodes pour travailler uniquement certaines parties déterminées, p. ex. pour graver la pierre ou le verre
B24C 3/32 - Machines ou dispositifs de traitement au jet abrasifInstallations de traitement au jet abrasif prévus pour le travail de pièces particulières, p. ex. de surface intérieure de blocs cylindres
B23K 26/38 - Enlèvement de matière par perçage ou découpage
B23C 3/18 - Usinage de surfaces à double courbure pour le façonnage d'hélices, d'aubes de turbines ou de roues à ailettes
The present invention is relative to a Brayton cycle plant and process for energy production, wherein an auxiliary turbine (8) which drives a compressor (9) is mechanically decoupled from a main turbine (2) and exploits a fraction (ΔΗ1) of a total enthalpy change (ΔΗ) exploited by the main turbine (2) in order to move the compressor.
F01K 7/16 - Ensembles fonctionnels de machines à vapeur caractérisés par l'emploi de types particuliers de machines motricesEnsembles fonctionnels ou machines motrices caractérisés par un circuit de vapeur, un cycle de fonctionnement ou des phases particuliersDispositifs de commande spécialement adaptés à ces systèmes, cycles ou phasesUtilisation de la vapeur soutirée ou de la vapeur d'évacuation pour le réchauffage de l'eau d'alimentation les machines motrices étant uniquement du type turbine
4.
RANKINE CYCLE PLANT AND PROCESS FOR THE REGASIFICATION OF LIQUEFIED GAS
The present invention regards a Rankine cycle plant for the regasification of liquefied gas, comprising: a Rankine closed loop system (2); a source (3) of liquefied gas (LG) at a cryogenic temperature, wherein the source (3) of liquefied gas (LG) is operatively coupled to a condenser (8) of the Rankine closed loop system (2) to receive heat from a working fluid (WF) flowing out from an expansion turbine (6; 6', 6") of the Rankine closed loop system (2) so as to take the liquefied gas (LG)to the gaseous state; a source (4) of a heating fluid (HF) at a temperature higher than the cryogenic temperature, wherein the source (4) of heating fluid (HF) is operatively coupled to an evaporator (5) of the Rankine closed loop system (2) to transfer heat to the working fluid (WF) coming from the condenser (8). The expansion turbine (6; 6', 6") is radial centrifugal and it has at least one auxiliary outlet (12, 13, 14; 12', 13', 14") interposed between successive stages. The condenser (8) is multilevel and it comprises at least two condensing chambers (25, 26, 27, 28), wherein a lower chamber (18) of the two condensing chambers (25, 26, 27, 28) is connected to an outflow opening (11; 11") of the expansion turbine (6; 6', 6") and an upper chamber (26, 27, 28) of the two condensing chambers (25, 26, 27, 28) is connected to the auxiliary outlet (12, 13, 14; 12', 13', 14") of the expansion turbine (6; 6', 6").
F01K 11/02 - Ensembles fonctionnels de machines à vapeur caractérisés par des machines motrices faisant corps avec les chaudières ou les condenseurs les machines motrices étant des turbines
F01K 25/10 - Ensembles fonctionnels ou machines motrices caractérisés par l'emploi de fluides énergétiques particuliers non prévus ailleursEnsembles fonctionnant selon un cycle fermé, non prévus ailleurs utilisant des vapeurs particulières ces vapeurs étant froides, p. ex. ammoniac, gaz carbonique, éther
5.
METHOD FOR THE CONSTRUCTION OF BLADED RINGS FOR RADIAL TURBOMACHINERY
The present invention relates to a method for constructing bladed rings for radial turbomachines. The method comprises: preparing a cylindrical block (M; M1, M2); making in the cylindrical block (M; M1, M2) a wavy circumferential cut (28, 28', 28") delimiting a first plurality of teeth (29) and a second plurality of teeth (30) meshing in one another; wherein the wavy circumferential cut (28, 28', 28") splits the cylindrical block (M; M1, M2) into a first annular body (31; 31 ', 31 ") provided with the first plurality of teeth (29) and into a second annular body (32; 32', 32") provided with the second plurality of teeth (30); separating the first annular body (31; 31 ', 31 ") from the second annular body (32; 32', 32"); removing material from each of the teeth (29, 30) of the first and second plurality to confer to each tooth (29, 30) the outline of at least one blade (22', 22") with an aerodynamic profile; joining coaxially the first annular body (31;31 ', 31 ") to the second annular body (32; 32', 32") by inserting the first blades (22') between the second blades (22").
The present invention relates to a thermodynamic cycle process for the production of mechanical and/or electrical power from variable temperature heat sources, comprising: circulating a gas (G) in a first closed circuit (2) according to a topping gas cycle, wherein the gas (G) is heated, expanded in a first expander (4), associated with a first electric generator (5) or a first mechanical user, cooled, compressed and again heated; operatively coupling in a boiler (100) a variable temperature heat source to the gas of the first closed circuit so as to perform a heating of the gas (G); circulating a working fluid (WF) in a second closed circuit (3) according to a bottoming Rankine cycle (RC), wherein the working fluid (WF) is heated and vaporized, expanded in a second expander (13), associated with a second generator (14) or a second mechanical user, condensed and again heated and vaporized; operatively coupling, in an exchanger (12), the expanded gas (G) of the topping cycle to the condensed and high-pressure working fluid (WF) of the bottoming Rankine cycle (RC), in order to cool the gas (G) and heat and vaporize the working fluid (WF) by transfer of heat from said topping cycle to the bottoming Rankine cycle (RC). The gas comprises, for example, carbon dioxide or sulfur hexafluoride or a mixture of sulfur hexafluoride and carbon dioxide. After the transfer of heat from the topping cycle to the Rankine cycle (RC) in the exchanger (12), the gas (G) of the topping cycle is further cooled in at least one cooling device (7', 7", 7"') to bring it close to its critical point.
F01K 23/10 - Ensembles fonctionnels caractérisés par plus d'une machine motrice fournissant de l'énergie à l'extérieur de l'ensemble, ces machines motrices étant entraînées par des fluides différents les cycles de ces machines motrices étant couplés thermiquement la chaleur de combustion provenant de l'un des cycles chauffant le fluide dans un autre cycle le fluide à la sortie de l'un des cycles chauffant le fluide dans un autre cycle
7.
METHOD FOR THE CONSTRUCTION OF ROTOR AND STATOR ELEMENTS OF TURBOMACHINERY
The present invention relates to a method for the construction of rotor and stator elements for turbomachinery comprising: preparing a solid (14) of material to be machined; performing cuts (15', 15", 15'", 15"", 22', 22", 22'", 22"") in the solid (14) so as to delimit blocks (20, 24, 28, 29, 32) of material interposed between portions of material intended to form vanes (9) of the rotor or stator element (1 ); removing said blocks (20, 24, 28, 29) to clear passages (27) between the portions of material; finishing the portions of material to provide the final shape to the vanes (9) and to the passages (27). For the formation of each of the passages (27), interrupted cuts (15', 15", 15'", 15"", 22', 22", 22'", 22"", 35) are performed in the solid (14) to delimit in the solid (14) at least one block (20, 32) and, after the removal of said at least one block (20, 32), a respective blind cavity (21, 33). The interrupted cuts (15', 15", 15'", 15""22', 22", 22'", 22"", 35) are substantially rectilinear cuts that terminate inside the solid (14) and, were they to continue beyond respective terminal points (20), they would intersect the final geometric shapes of the rotor or stator element. (1).
B23P 15/00 - Fabrication d'objets déterminés par des opérations non couvertes par une seule autre sous-classe ou un groupe de la présente sous-classe
B23H 9/10 - Usinage d'aubes de turbine ou de buses
B23C 3/18 - Usinage de surfaces à double courbure pour le façonnage d'hélices, d'aubes de turbines ou de roues à ailettes
B24C 1/04 - Méthodes d'utilisation de jet abrasif en vue d'effectuer un travail déterminéUtilisation d'équipements auxiliaires liés à ces méthodes pour travailler uniquement certaines parties déterminées, p. ex. pour graver la pierre ou le verre
B23K 26/38 - Enlèvement de matière par perçage ou découpage
The present invention relates to an assembly of turbines, comprising: a first counter rotating turbine (2) and a second counter rotating turbine (3); a first group of gears (13) and a second group of gears (14) arranged on opposite sides of the first and of the second counter rotating turbine (2, 3); a central shaft (33) configured to be connected to a generator (300); wherein the central shaft (33) is connected between the first and the second counter rotating turbine (2, 3) and is substantially parallel to the first and to the second turbine shafts (7, 8). The first group of gears (13) is operatively connected to the first turbine shaft (7) of the first counter rotating turbine (2), to the first turbine shaft (7) of the second counter rotating turbine (3) and to the central shaft (33) and is configured to transmit the rotary motion of the first turbine shafts (7) to the central shaft (33) according to a predefined rotation direction; The second group of gears (14) is operatively connected to the second turbine shaft (8) of the first counter rotating turbine (2), to the second turbine shaft (8) of the second counter rotating turbine (3) and to the central shaft (33) and is configured to transmit the rotary motion of the second turbine shafts (8) to the central shaft (33) according to the same predefined rotation direction.
F01D 1/24 - "Machines" ou machines motrices à déplacement non positif, p. ex. turbines à vapeur caractérisées par des rotors contra-rotatifs soumis au même courant de fluide énergétique sans aubes ou structures analogues intermédiaires sur les stators
9.
SET OF TURBINES AND A TURBINE TRAIN COMPRISING AT LEAST ONE SUCH SET
The present invention refers to a set of turbines, comprising: a first turbine (2) comprising a first shaft (7) supported in an overhung manner in a first case (8), and a first rotor (5) provided with first rotor blades (P1) and joined to a distal end (6) of the first shaft (7); a second turbine (3) comprising a second shaft (15) supported in an overhung manner in a second case (16), and a second rotor (13) provided with second rotor blades (P2) and joined to a distal end (14) of the second shaft (15). A first front face (21) of the first rotor (5) faces a second front face (22) of the second rotor (5). The set of turbines (1) further comprises a connection element (4) connected to the first front face (21) and to the second front face (22) to transmit rotation from the first shaft (7) to the second shaft (15) or vice versa. The connection element (4) comprises at least one elastic joint (24) configured to minimize the rotordynamic influence of the first turbine (2) and the second turbine (3) on each other.
F01D 5/06 - Rotors à plus d'un étage axial, p. ex. du type à tambour ou à disques multiplesLeurs parties constitutives, p. ex. arbres, connections des arbres
10.
METHOD FOR THE ASSEMBLY OF A RADIAL TURBINE AND RADIAL TURBINE
The present invention refers to a method for the assembly of a counter-rotating radial turbine, comprising: preparing a central case (9); pre-assembling a first turbine unit (33') and a second turbine unit (33"), each comprising: a half-case (19', 19") delimiting a housing (Α', A"); a rotating unit (26', 26") comprising a shaft (4') housed and rotatably supported in the housing (Α', A") and that is free to rotate about an axis of rotation (X1, X2) with respect to said housing (Α', A"); a rotor disc (3', 3") joined to and overhanging a distal end (Ε', E") of the shaft (4', 4") and having a front bladed face (7', 7") facing the opposite side with respect to the half-case (19', 19"). The method comprises coupling the first pre-assembled turbine unit (33') and the second pre-assembled turbine unit (33") to the central case (9) so as to arrange the front bladed face (7') of the first rotor disc (3') in front of the front bladed face (7") of the second rotor disc (3"), wherein, following the coupling process, the first half-case (19') and the second half-case (19") laterally close the central case (9).
F01D 25/26 - Carcasses d'enveloppe doublesMesures contre les tensions thermiques dans les carcasses d'enveloppe
F01D 1/28 - "Machines" ou machines motrices à déplacement non positif, p. ex. turbines à vapeur caractérisées par des rotors contra-rotatifs soumis au même courant de fluide énergétique sans aubes ou structures analogues intermédiaires sur les stators traversées par le fluide de travail principalement dans le sens radial
F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
11.
METHOD FOR THE CONSTRUCTION OF BLADED DISCS FOR RADIAL TURBOMACHINES AND A BLADED DISC OBTAINED BY MEANS OF THIS METHOD
The present invention concerns a method for the construction of bladed discs for radial turbomachines, comprising: preparing a disc (6, 14) provided with a front face (7); preparing a plurality of reinforcement rings (23) with different diameters. Preparing the disc (6, 14) comprises: realizing annular sets of blades (20) in one piece with the disc (6, 14), said sets (20) being concentric and coaxial with a central axis (X-X) and arranged on the front face (7), wherein each blade (20) has a leading edge (21 ) and a trailing edge (22) substantially parallel to the central axis (X-X); and/or preparing a plurality of reinforcement rings (23) comprises: realizing in one piece with each one of the reinforcement rings (23) an annular set of auxiliary blades (20') arranged around a central axis (X-X), wherein each auxiliary blade (20') has a leading edge (21 ') and a trailing edge (22') substantially parallel to the central axis (X-X). Each one of the reinforcement rings (23) is applied to the disc (6, 14) at one of the annular sets of blades (20) and/or auxiliary blades (20'), so as to define on the front face (7) annular sets of blades (20) and/or auxiliary blades (20'), each one provided with a respective reinforcement ring (23).
F01D 1/06 - "Machines" ou machines motrices à déplacement non positif, p. ex. turbines à vapeur avec des moyens stationnaires de guidage de fluide de travail et un rotor à ailettes ou de structure analogue traversées par le fluide de travail principalement dans le sens radial
F01D 5/04 - Organes de support des aubes, p. ex. rotors pour "machines" ou machines à flux radial
F01D 5/30 - Fixation des aubes au rotorPieds de pales
12.
RADIAL TURBOMACHINE WITH AXIAL THRUST COMPENSATION
The present invention relates to a radial turbomachine with axial thrust compensation, comprising: a fixed casing (3); a plurality of main concentric bladed rings (9',9",9"',9"") arranged in the fixed casing (3) around a central axis (X-X); a plurality of concentric auxiliary bladed rings (15', 15", 15"') arranged in the fixed casing (3) around the central axis (X-X) and radially alternated with the main bladed rings (9',9",9"',9""). A rotor (2, 2') comprising a rotor disc (6, 6') and a rotation shaft (4, 4', 4") integral with the rotor disc (6, 6') is rotatable in the fixed casing (3) around the central axis (X-X) and carries, on a front face (7, 7'), the main bladed rings (9',9",9"',9""). The main (9',9",9"',9"") and auxiliary (15', 15", 15"') bladed rings delimit, with the rotor disc (6, 6'), a plurality of concentric front main chambers (30, 33, 35, 36) at different pressures. A plurality of concentric rear annular main chambers (41 ',41 ",41 '",41 ""), each in fluid communication with a respective front main chamber (30, 33, 35, 36) and at the same pressure as the respective front main chamber (30, 33, 35, 36), is delimited between a rear face (8, 8') of the rotor disc (6, 6') and the fixed casing (3). A rear annular area (A_1 p, A_2p, A_3p, A_4p, A'_4p) of the rotor disc (6, 6') delimiting one of the rear annular main chambers (41 ',41 ",41 '",41 "") is equal to or substantially equal to a front area (A_1f, A_2f, A_3f, A_4f) of the rotor disc (6, 6') delimiting a respective front main chamber (30, 33, 35, 36), so that the force exerted by the pressure of the working fluid in each rear annular main chamber (41 ',41 ",41 '",41 "") substantially balances the force exerted by the pressure of the working fluid in the respective front main chamber (30, 33, 35, 36).
F01D 1/06 - "Machines" ou machines motrices à déplacement non positif, p. ex. turbines à vapeur avec des moyens stationnaires de guidage de fluide de travail et un rotor à ailettes ou de structure analogue traversées par le fluide de travail principalement dans le sens radial
F01D 3/00 - "Machines" ou machines motrices avec équilibrage des poussées axiales effectué par le fluide énergétique
F01D 5/04 - Organes de support des aubes, p. ex. rotors pour "machines" ou machines à flux radial
13.
METHOD OF MANUFATURING BLADED RINGS FOR RADIAL TURBOMACHINES USING STOP ELEMENTS WITH LOCALISED WELDS; CORRESPONDING BLADED RING
The present invention relates to a method of manufacturing a bladed ring (9) for radial turbomachines, comprising the steps of : assembling a first support ring (15) with a second support ring (22), with a plurality of blades (27), with a first connecting ring (40) and with a second connecting ring (41), so as to make a bladed ring (9) comprising the first and the second support ring (15, 22) coaxial and axially spaced one from the other and the plurality of blades (27) disposed equidistant from a central axis (X-X) and interposed between the aforesaid first and second support ring (15, 22). The method further comprises stably joining a first end (30) of each blade (27) to the first connecting ring (40), stably joining a second end (31) of each blade (27) to the second connecting ring (41), fixing the first connecting ring (40) to the first support ring (15) and fixing the second connecting ring (41) to the second support ring (22). The first support ring (15), the second support ring (22), the plurality of blades (27), the first connecting ring (40) and the second connecting ring (41) are all finished elements before assembling, meaning that they present their final geometry and they do not need further machining and/or plastic deformations during and/or after assembly.
B23K 31/02 - Procédés relevant de la présente sous-classe, spécialement adaptés à des objets ou des buts particuliers, mais non couverts par un seul des groupes principaux relatifs au brasage ou au soudage
F01D 5/04 - Organes de support des aubes, p. ex. rotors pour "machines" ou machines à flux radial
F01D 5/30 - Fixation des aubes au rotorPieds de pales
F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
B23K 101/00 - Objets fabriqués par brasage, soudage ou découpage
14.
METHOD FOR MANUFACTURING BLADED RINGS FOR RADIAL TURBOMACHINES AND BLADED RING OBTAINED BY THIS METHOD
The present invention relates to a method for the construction of bladed rings for radial turbomachines, comprising: preparing an annular block (31 ); roughing the annular block (31 ) by removing material to define a first axial section (32), a second axial section (33), a third axial section (34) and a fourth axial section (35), wherein the first axial section (32) defines a reinforcement ring (20), wherein the third axial section (34) defines a base ring (15); roughing the second axial section (33) by removing material to delimit a plurality of separate elements (36), wherein the separate elements (36) axially connect the base ring (15) to the reinforcement ring (20); finishing each of the separate elements (36) by removing material to provide said separate element (36) with the shape of an airfoil blade (22), wherein a leading edge (23) of said blade (22) and a trailing edge (24) of said blade (22) develop substantially parallel to a central axis (X-X) of the bladed ring (9, 14); roughing the fourth axial section (35) by removing material for delimiting an annular anchoring appendage (17) of the base ring (15) to a radial turbomachine (1 ).
The present invention relates to an ORC binary cycle geothermal plant, comprising at least one ORC closed-cycle system (2, 2', 2") and a geothermal system (3). The geothermal system (3) comprises at least: one intake line (10) of a geothermal fluid (GF) connected to at least one geothermal production well (11), wherein the geothermal fluid (GF) comprises non-condensable gases (NCGs); one interface line (12) connected to the intake line (10) and operatively coupled to the ORC closed-cycle system (2, 2', 2") in an interface zone (13), wherein the geothermal fluid (GF) exchanges heat with the organic working fluid (OWF) of the ORC closed-cycle system; one reinjection line (14) connected to the interface line (12) and to at least one geothermal reinjection well (15). The geothermal system (3) further comprises: at least one separator device (16, 16', 16") configured to separate at least the non-condensable gases (NCGs) from the geothermal fluid (GF); one expander (19) operatively connected to an outlet (17, 17', 17") of the non-condensable gases (NCGs) by the separator device (16, 16', 16"); and one auxiliary generator (20) operatively connected to the expander (19). The expander (19) is located downstream of the interface zone (13) for interfacing with the ORC closed-cycle system (2, 2', 2") so as to receive and expand at least the non- condensable gases (NCGs) after they have exchanged heat with the organic working fluid (OWF).
The present invention relates to a radial centrifugal turbomachine provided with an adjusting device (25) operatively active at the axial inlet (12) of the fixed casing (6) of the turbomachine (1 ). The adjusting device (25) comprises an annular member (26) delimiting at least one radially inner passage (28) situated at the axial inlet (12), wherein a front surface (30) of the annular member (26) and an abutment surface (35) of the casing (6) delimit between them a radial annular passage (15). An actuator (46) is connected to the annular member (26) and is configured to move axially and/or to rotate according to a predefined angle the annular member (26) so as to vary the radial annular passage (15) and/or passage sections (52) delimited between stator blades (13') of a first radial stage (3', 13') of the turbomachine (1 ) itself. A transmission shaft (39) coaxial with the rotation axis (X- X) and integral with the annular member (26) is operatively connected to the actuator (46). The adjusting device (25) allows adjusting the mass flow rate at the inlet of the turbomachine (1 ) in order to better adapt the performances of the turbomachine (1 ) itself to the loading of the process/cycle and also to implement a safety system dedicated to stopping the turbomachine (1 ) in case of an urgent stop request.
F01D 1/06 - "Machines" ou machines motrices à déplacement non positif, p. ex. turbines à vapeur avec des moyens stationnaires de guidage de fluide de travail et un rotor à ailettes ou de structure analogue traversées par le fluide de travail principalement dans le sens radial
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
F02C 3/08 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur le compresseur comprenant au moins un étage radial
The present invention relates to a radial turbomachine, comprising: a fixed casing (6); at least one rotor disc (2,2') installed in the casing (6) and rotatable in the casing (6) around a respective rotation axis (X-X); a plurality of annular rotor elements (3,22,23,24; 22,23) coaxial with the rotation axis (X-X), axially projecting from a front face (4,4') of the rotor disc (2,2') and/or from a rear face (9,9') of the rotor disc (2,2'); a plurality of annular fixed elements (13,25,27; 34) coaxial with the rotation axis (X-X), axially projecting from the casing (6) and each positioned in a radially external position with respect to a respective annular rotor element (3,22,23,24; 22,23); a plurality of sealing devices (28,29; 29,31; 32,33) radially interposed between at least some of said annular rotor elements (3,22,23,24; 22,23) and the respective annular fixed elements (13,25,27; 34). The annular rotor elements (3,22,23,24; 22,23) are radially movable between a first radially contracted configuration, when the turbomachine (1) is in a non-operative condition, wherein, at the sealing devices (28,29; 29,31; 32,33), the annular rotor elements (3,22,23,24; 22,23) are radially spaced from the respective annular fixed elements (13,25,27; 34), and a second radially expanded configuration under the action of the centrifugal force and/or of the heat, when the turbomachine (1) is operating, wherein, at the sealing devices (28,29; 29,31; 32,33), the annular rotor elements (3,22,23,24; 22,23) are close to the respective annular fixed elements (13,25,27; 34). In the second configuration the sealing devices (28,29; 29,31; 32,33) substantially prevent the passage of a working fluid between the annular rotor elements (3,22,23,24; 22,23) and the annular fixed elements (13,25,27; 34).
The present invention is related to a centrifugal radial turbine comprising 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. The disc (3, 4) has through induction channels (25, 28) situated in a position radially external with respect to a respective shaft (5, 7) and radially internal with respect to the radial rotor stage (10, 11, 12, 13, 16, 17, 18, 19). At the respective through induction channels (25, 28), the disc (3, 4) comprises a plurality of induction rotor blades (26, 29) of at least one respective axial rotor stage (27, 30).
F01D 1/06 - "Machines" ou machines motrices à déplacement non positif, p. ex. turbines à vapeur avec des moyens stationnaires de guidage de fluide de travail et un rotor à ailettes ou de structure analogue traversées par le fluide de travail principalement dans le sens radial
F01D 1/14 - "Machines" ou machines motrices à déplacement non positif, p. ex. turbines à vapeur avec des moyens stationnaires de guidage de fluide de travail et un rotor à ailettes ou de structure analogue avec action répétée sur la même roue d'aubes traversées par le fluide de travail principalement dans le sens radial
F01K 25/08 - Ensembles fonctionnels ou machines motrices caractérisés par l'emploi de fluides énergétiques particuliers non prévus ailleursEnsembles fonctionnant selon un cycle fermé, non prévus ailleurs utilisant des vapeurs particulières
The present invention regards a radial turbomachine, comprising: a fixed case (6); at least one rotor disc (2, 2', 2") installed in the case (6) and having rotor blades (3, 3', 3") mounted on a front face (4, 4', 4") thereof; a plurality of elements (25, 35) projecting from the case (6) and terminating in proximity to the rotor disc (2, 2', 2"), wherein the projecting elements (25, 35) comprise seal elements (34) acting against the rotor disc (2, 2', 2") that are operatively active on a rear face (9, 9', 9") of the rotor disc (2, 2', 2") or stator blades (13) radially interposed between the rotor blades (3) of the rotor disc (2); at least one support plate (17, 37) bearing the projecting elements (25, 35) and installed in the case (6). The support plate (17, 37) is radially extended across from the rotor disc (2, 2', 2") and comprises a plurality of first circular portions (29) concentric with a rotation axis (X-X) of the rotor disc (2) and a plurality of second circular portions (30) radially interposed between the first circular portions (29). At least several of the first circular portions (29) bear the projecting elements (25, 35) and the second circular portions (30) are more deformable, along radial directions, than the first circular portions (29) in a manner so as to allow relative movements between the first circular portions (29) when the support plate (17, 37) is subjected to the action of thermal gradients.
The present invention is relative to an expansion turbine comprising: a stator (3), a rotor (2) facing the stator (3), a short pipe (5), a shaft (7) rotatably mounted in the short pipe (5), wherein the shaft (7) is removably connected to the rotor (2) and said shaft (7) is extractable from the short pipe (5) from the side opposite said rotor (2). The turbine (1 ) also comprises devices (14) for removably connecting the rotor (2) to the shaft (7) having a handling portion (15) placed at a front face of the rotor (2) opposite the short pipe (5). At least one front static seal (30) is interposed between the rotor (2) and the stator (3) and placed at a radially inner position with respect to an expansion volume (V) delimited between the stator (3) and the rotor (2). The front static seal (30) is mobile between a first position, wherein it clears a passage (40) between the stator (3) and the rotor (2) in fluid communication with the expansion volume (V), and a second position, wherein it seals said passage (40) and sealingly isolates the expansion volume (V) from a space (21 ) for access to said handling portion (15). The front static seal (30) preferably has variable geometry and is for example defined by an inflatable gasket.
F01D 1/06 - "Machines" ou machines motrices à déplacement non positif, p. ex. turbines à vapeur avec des moyens stationnaires de guidage de fluide de travail et un rotor à ailettes ou de structure analogue traversées par le fluide de travail principalement dans le sens radial
F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages
21.
METHOD FOR BUILDING STAGES OF CENTRIFUGAL RADIAL TURBINES
The present invention relates to a method for building centrifugal radial stages of turbines, in which the first and the second end of each blade (4) are connected to respective two support rings (2, 3) joining, by means of laser welding, at least a first semi-portion (10) belonging to the respective end of the blade (4) to a respective second semi-portion (10) belonging to the respective support ring (2, 3) so as to form a resilient yielding connecting portion (10, 15) along a radial direction, and providing at least a stop portion (11) belonging to the end of the blade (4) facing, along the radial direction, at least a stop element (14) of the respective support ring (2, 3). The resilient yielding connecting portion (10, 15) enables the strop portion (11) to enter into contact with the stop element (14) when the stage (1) is subjected to the functioning loads of the turbine.
An ORC system for generation of energy by Organic Rankine Cycle comprises a turbo-expander (40) of a radial centrifugal type formed by a single rotor disc (108) and provided with an auxiliary opening (40c). The auxiliary opening (40c) is interposed between an inlet (40a) and an outlet (40b) of the turbine (40) and is in fluid connection with an auxiliary circuit (1000, 2000), such as to extract from the turbo-expander (40) or inject into the turbo-expander (40) the organic working fluid at an intermediate pressure between an injection pressure and a discharge pressure.
F01K 7/18 - Ensembles fonctionnels de machines à vapeur caractérisés par l'emploi de types particuliers de machines motricesEnsembles fonctionnels ou machines motrices caractérisés par un circuit de vapeur, un cycle de fonctionnement ou des phases particuliersDispositifs de commande spécialement adaptés à ces systèmes, cycles ou phasesUtilisation de la vapeur soutirée ou de la vapeur d'évacuation pour le réchauffage de l'eau d'alimentation les machines motrices étant uniquement du type turbine les turbines étant du type à pressions d'entrée multiples
F01K 17/02 - Utilisation de la vapeur ou des condensats provenant soit du soutirage, soit de la sortie des ensembles fonctionnels de machines motrices à vapeur pour le chauffage, p. ex. industriel, domestique
F01K 25/08 - Ensembles fonctionnels ou machines motrices caractérisés par l'emploi de fluides énergétiques particuliers non prévus ailleursEnsembles fonctionnant selon un cycle fermé, non prévus ailleurs utilisant des vapeurs particulières
F01D 1/06 - "Machines" ou machines motrices à déplacement non positif, p. ex. turbines à vapeur avec des moyens stationnaires de guidage de fluide de travail et un rotor à ailettes ou de structure analogue traversées par le fluide de travail principalement dans le sens radial
23.
APPARATUS AND PROCESS FOR GENERATION OF ENERGY BY ORGANIC RANKINE CYCLE
An apparatus for generation of energy through organic Rankine cycle comprises a heat exchanger (3) to exchange heat between a high temperature source and an organic working fluid, so as to heat and evaporate said working fluid, an expansion turbine (4) of the radial- outflow type, fed with the vaporised working fluid outflowing from the heat exchanger (3), to make a conversion of the thermal energy present in the working fluid into mechanical energy according to a Rankine cycle, a condenser (6) where the working fluid outflowing from the turbine (4) is condensed and sent to a pump (2) and then fed to the heat exchanger (3).
F01K 7/02 - Ensembles fonctionnels de machines à vapeur caractérisés par l'emploi de types particuliers de machines motricesEnsembles fonctionnels ou machines motrices caractérisés par un circuit de vapeur, un cycle de fonctionnement ou des phases particuliersDispositifs de commande spécialement adaptés à ces systèmes, cycles ou phasesUtilisation de la vapeur soutirée ou de la vapeur d'évacuation pour le réchauffage de l'eau d'alimentation les machines motrices étant du type à détentes multiples
F01K 25/10 - Ensembles fonctionnels ou machines motrices caractérisés par l'emploi de fluides énergétiques particuliers non prévus ailleursEnsembles fonctionnant selon un cycle fermé, non prévus ailleurs utilisant des vapeurs particulières ces vapeurs étant froides, p. ex. ammoniac, gaz carbonique, éther
F01D 1/06 - "Machines" ou machines motrices à déplacement non positif, p. ex. turbines à vapeur avec des moyens stationnaires de guidage de fluide de travail et un rotor à ailettes ou de structure analogue traversées par le fluide de travail principalement dans le sens radial
24.
APPARATUS AND PROCESS FOR GENERATION OF ENERGY BY ORGANIC RANKINE CYCLE
An apparatus (10) and a process for generation of energy through organic Rankine cycle (ORC) in which the heat exchanger (70) is of the hairpin type, so as to make the apparatus more flexible and optimise the cycle efficiency. The hairpin heat exchanger is able to stably carry out the preheating, once -through evaporation and superheating steps both at the nominal load and at the partial and transitory loads, either for sub-critical ORC cycles or for super- critical ORC cycles.
F01K 25/10 - Ensembles fonctionnels ou machines motrices caractérisés par l'emploi de fluides énergétiques particuliers non prévus ailleursEnsembles fonctionnant selon un cycle fermé, non prévus ailleurs utilisant des vapeurs particulières ces vapeurs étant froides, p. ex. ammoniac, gaz carbonique, éther
F22B 21/24 - Chaudières à tubes d'eau du type vertical ou semi-vertical, c.-à-d. où les faisceaux de tubes d'eau sont disposés verticalement ou pratiquement à la verticale composées de tubes d'eau de forme autre que rectiligne ou sensiblement rectiligne en serpentins ou sinueux
F22B 29/06 - Chaudières à vapeur du type à circulation forcée du type à circulation ouverte, c.-à-d. composées de tubes admettant de l'eau à une extrémité et dégageant de la vapeur surchauffée à l'autre extrémité
F22B 27/06 - Chaudières à vapeur instantanées ou du type flash avec des tubes d'eau en serpentins ou sinueux
An expansion turbine, comprising: a case having an inlet and an outlet for a working fluid; at least one stator ( 3 ) installed inside the case; at least one rotor (2) installed inside the case and rotating around a respective revolution axis (X-X); a short-pipe (4) constrained to the case; a mechanical unit (5) installed inside the short-pipe (4). The mechanical unit (5) comprises a bushing (7) and a shaft (6) rotatably installed inside the bushing (7). The shaft (6) is connected to the rotor (2) in removable manner and the whole mechanical unit (5) inclusive of the shaft (6) is extractable from the short-pipe (4) in a unitary form from the side opposite to said rotor (2). The rotor (2) is movable along the axial direction (X-X) between a first configuration, in which the mechanical unit (5) is installed inside the short-pipe (4) and the rotor (2) is spaced from the short-pipe (4), so that the working fluid can revolve it, and a second configuration, in which the mechanical unit (5) is extracted fom the short-pipe (4) and the rotor (2) leans agains the short-pipe (4) a static seal (18,19).
F01D 25/16 - Aménagement des paliersSupport ou montage des paliers dans les stators
F02C 6/12 - Turbocompresseurs de suralimentation, c.-à-d. ensembles fonctionnels destinés à augmenter la sortie de puissance mécanique des moteurs à piston à combustion interne en augmentant la pression de suralimentation
brevets