EP3167158A1 - Turbine et procédé d'expansion d'un fluide de travail avec saut d'enthalpie isentropique élevé - Google Patents

Turbine et procédé d'expansion d'un fluide de travail avec saut d'enthalpie isentropique élevé

Info

Publication number
EP3167158A1
EP3167158A1 EP15736632.9A EP15736632A EP3167158A1 EP 3167158 A1 EP3167158 A1 EP 3167158A1 EP 15736632 A EP15736632 A EP 15736632A EP 3167158 A1 EP3167158 A1 EP 3167158A1
Authority
EP
European Patent Office
Prior art keywords
expansion
stages
shaft
turbine
group
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.)
Withdrawn
Application number
EP15736632.9A
Other languages
German (de)
English (en)
Inventor
Roberto Bini
Mario Gaia
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Turboden SpA
Original Assignee
Turboden SpA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Turboden SpA filed Critical Turboden SpA
Publication of EP3167158A1 publication Critical patent/EP3167158A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/04—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 axially
    • 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

Definitions

  • the present invention relates to a turbine in which the operating fluid expands, at the beginning, in a centripetal direction and then in a centrifugal (and eventually axial) direction, and to a method for expanding an operating fluid in such a turbine, in particular an organic fluid in a Rankine cycle.
  • the isentropic enthalpy drop provided by the expansion in the turbine i.e. the maximum work per mass unit the expanding operating fluid can produce, expressed for example in kJoule/kg, most of all depends from fluid characteristics and, generally, is a function of the difference between evaporation and condensation temperatures of the fluid.
  • the characteristics of the operating fluid itself strongly affect the enthalpy drop, which is higher for fluids having simple molecule and low value of molecular mass.
  • the computation of the isentropic enthalpy drop is a well known topic of the theory of Rankine cycles; the turbine designer implements the turbine design by using, as starting values, the composition of the operating fluid, the inlet values of temperature, flow rate, pressure and titer of the fluid, as well as the value of exhaust pressure. From these data the value of the isentropic enthalpy drop can be easily calculated with known methods, therefore such a value has to be interpreted as a characterizing parameter in turbine design.
  • expansion ratio both defined as the ratio between the inlet pressure and the exhaust pressure, and as the volume expansion ratio, i.e. the ratio between the volumetric flow rate at the exhaust zone and that one at the turbine inlet zone.
  • ORC Organic Rankine cycle
  • ORC plants are used for the combined production of electrical and thermal power starting from solid biomass; alternatively waste heats of industrial processes, heat recovery from prime movers or geothermal heat sources are used.
  • an ORC plant fed with biomass usually comprises:
  • a heat exchanger provided to give part of the heat of combustion fumes/ gases to a heat-transfer fluid, such as a diathermic oil, delivered by an intermediate circuit;
  • the heat-transfer fluid for example diathermic oil
  • the heat-transfer fluid circulates in a closed loop, passing through the afore mentioned heat exchanger in which the organic operating fluid evaporates.
  • the steam of the operating fluid expands in the turbine, producing mechanic power, then is transformed into electrical power by the generator connected to the shaft of the turbine itself.
  • the steam of the operating fluid condenses in an appropriate condenser, giving heat to a cooling fluid, usually water, used downstream of the plant as thermal carrier at about 80°C - 90°C, for example for the district heating.
  • the operating fluid is fed to the heat exchanger crossed by the heat-transfer fluid, completing the cycle in closed loop.
  • the present invention applies in Rankine cycles in general, both of ORC type or else of steam type, in Kalina cycles and in general in industrial processes where the expansion of an operating fluid is provided, in the cases the isentropic enthalpy drop of the turbine is high relative to the squared peripheral speed of the turbine, and therefore in connection with an external diameter of the arrays approximately by a meter, i.e. in the cases considered in the present application:
  • “cantilevered” solution is preferably adopted, meaning that the bearings supporting the shaft are at the same part with respect to the rotor in which the produced power is collected. In fact it is an easier solution from the implementation point of view, needing only one rotating seal per each shaft, it is cost-effective and can be maintained more easily than a solution with a rotor comprised between the bearings.
  • WO 2013/108099 describes a third solution than can be considered the closest prior art with regard to the present invention.
  • WO 2013/108099 describes a turbine with only one shaft in which the fluid expands in radial centrifugal stages and in axial stages, in succession.
  • At least one array of stator or rotor blades, name angular blades is arranged between the radial stages and the axial stages in order to divert the operating fluid.
  • the enthalpy drop of the operating fluid expanded through the angular blades is equal to at least 50% of the average enthalpy drop provided to complete the fluid expansion in the whole turbine.
  • the rotor or the rotor pool supporting radial and axial stages can be assembled on the shaft at an end, extending substantially in a cantilevered configuration, so that the turbine has extremely compact size in comparison with the other known solutions, and the bearings, the reduction gear and the electric generator are on the same side, easily accessible for maintenance. From a thermodynamic point of view this solution provides the highest level enthalpy drop occurring at the pool of the angular blades and the subsequent axial blades.
  • the present invention relates, in a first aspect thereof, to a turbine according to the claim 1 for the expansion of a compressible operating fluid, for example gas or steam.
  • a compressible operating fluid for example gas or steam.
  • the turbine comprises at least two groups of expansion stages, each defined by arrays of stator blades and/or arrays of rotor blades.
  • a first group of stages is named group of stages of first expansion
  • a second group of stages is named group of stages of second expansion.
  • the group of stages of second expansion is positioned downstream of the group of stages of first expansion with respect to the direction of motion of the operating fluid through the turbine.
  • the arrays of rotor blades of the group of stages of first expansion are constrained to a first shaft. Some of the arrays of rotor blades of the group of stages of second expansion are constrained to the first shaft and the others to a second shaft, so to be alternated and fluidically interconnected.
  • the first shaft and the second shaft are aligned on a common rotation axis X- X, i.e. they are coaxial, and rotate in a way opposite one to another.
  • the rotation speed of the first shaft is greater than the rotation speed of the second shaft. For example if the second shaft rotates at a speed of 3000 revolutions per minute, the first shaft rotates at a speed comprised between 4500 and 6000 revolutions per minute.
  • the group of stages of first expansion extends in a radial centripetal direction with respect to the rotation axis X-X and the group of stages of second expansion extends in a radial centrifugal direction with respect to the same axis.
  • the described configuration allows obtaining a high efficiency also in the group of stages of first expansion.
  • the proposed solution allows obtaining high efficiencies without complicating the turbine design, which remains simply to be maintained and can be manufactured with held down costs.
  • first expansion centripetal stages
  • second expansion upstream of the centrifugal stages
  • the volumetric flow rate of the operating fluid is typically moderate
  • the turbine is anyway compact and robust, since the centrifugal stages of second expansion extend substantially radially and have very little bulk in axial direction. Exploiting the enthalpy drop available at the turbine is more efficient than what can be ascertained in known solutions, where the expansion ratio per stage is excessive and/or the aerodynamic load on blades is excessive; the proposed solution allows distributing the enthalpy drop on an optimal number of stages, almost with the same bulks with respect to known solutions, to efficiency advantage.
  • the turbine is included in a thermodynamic cycle characterized by high enthalpy drops.
  • the enthalpy drop corresponding to the expansion of the operating fluid in the group of stages of second expansion, defined by counter-rotating and fluidically interconnected rotor arrays can be relatively high, i.e. the group of stages of second expansion is able to exploit an enthalpy drop in percent equal to 30% - 50% with respect to the overall enthalpy drop of the turbine.
  • centrifugal stages of the group of stages of second expansion, and possibly of additional stages downstream are positioned on a diameter corresponding to or larger than the diameter of the second shaft and the respective bearings; this allows partially disassembling the turbine, for example partially taking out the shaft and/or bearings to get access to the other rotor disks possibly constrained to the second shaft, in order to carry out inspections or maintenance operations without having to completely disassemble the turbine.
  • the volute of the turbine can be realized with appropriate joints and flanges, to allow a simple removal of the first shaft and the respective bearings, extracting the first rotor as well.
  • the group of stages of second expansion comprises from 1 to 10 stages, depending on the turbine size.
  • the rotation speed of the first shaft is equal or greater than 1.5 times the rotation speed of the second shaft. Preferably it is lower than 4 times the rotation speed of the second shaft.
  • the arrays of rotor blades of the group of stages of first expansion are assembled in a supporting disk keyed to the first shaft at an end thereof, anyway not in the area between the bearings, according to a so called 'cantilevered' configuration.
  • the arrays of stator blades of the group of stages of first expansion are fastened to a stationary portion of the turbine, for example a volute.
  • the group of stages of second expansion is defined by only counter-rotating rotor blades fastened to the first supporting disk and to the second supporting disk, respectively, and then fastened alternately to the first shaft and the second shaft.
  • the second supporting disk is cantileverly assembled with respect to the bearings of the second shaft.
  • the first shaft can be directly coupled, i.e. with no reduction gear, with an electric generator having two poles and the second shaft can be directly coupled with an electric generator having four poles.
  • One of the advantages of having shafts rotating at different speeds also consists in being able to couple corresponding generators sized upon the number of revolutions of the respective shaft.
  • the fastest electric generator can simply have 2 poles at 50 Hz, i.e. it rotates at 3000 revolutions per minute (rpm), or 60 Hz at 3600 rpm, or else can be connected to the shaft through a revolutions' reduction gear or can even be a generator having a frequency different from the mains frequency and be directly assembled on the shaft between the bearings.
  • the rotor blades of the group of stages of first expansion and some rotor blades of the group of stages of second expansion are assembled on a common first supporting disk provided with a reversing blade assembly or channel at which the operating fluid reverses its own way of expansion from radial centripetal to radial centrifugal one.
  • the first supporting disk has, in a meridian section, a U-profile and the reversing channel or blade assembly is arranged in the most radially internal part of the U, i.e. the portion closest to the first shaft.
  • At least one array of stator blades in the group of stages of first expansion is of the type having variable pitch angle. This characteristic allows adjusting the inlet volumetric flow rate and possibly rapidly stopping the adduction of operating fluid.
  • additional expansion stages of the operating fluid can be provided that extend, with respect to the axis X-X, in a radial centripetal direction and/or axial direction, anyway at diameters greater than the last array of blades of the group of stages of second expansion.
  • the turbine comprises an array of rotor or stator blades, named angular blades, intermediate between the last stage of the group of stages of second expansion and the first axial stage, if it is present. At the angular blades the expansion direction of the operating fluid switches from substantially radial centrifugal to substantially axial and tangential with respect to an observer integral with the same angular blades.
  • the turbine comprises at least one adduction or extraction duct (or channel) of operating fluid that opens at the inlet of the arrays of angular blades.
  • the operating fluid is herein subjected to a considerable enthalpy drop (meant as production of kinetic energy at the expense of the fluid expansion) with respect to the average enthalpy drop per stage, for example equal to at least 10% of the average enthalpy drop per stage.
  • the turbine comprises an expansion chamber free of stages downstream of the group of stages of second expansion (and upstream of the additional expansion stages, if they are present), wherein at least one adduction or extraction duct of operating fluid opens into said chamber.
  • the turbine is designed to fulfill the following condition:
  • Ah ( i S; tot ) is the overall enthalpy drop performed in the groups of radial stages, either centripetal or centrifugal, calculated as the difference between the overall enthalpy drop of the turbine and the enthalpy drop performed in the groups of axial stages downstream of the groups of radial stages, and where ui is the peripheral speed at the average diameter of the first axial stage.
  • the turbine can be realized with the first shaft and the second shaft spaced apart and facing one another head to head.
  • the operating fluid is organic and its expansion occurs in a Rankine cycle, or in a Kalina cycle or, in general, in a thermodynamic cycle providing for the expansion of the operating fluid.
  • the method can concern the expansion of every fluid in a process, for example within a process of liquefaction and/or regasification of natural gas.
  • the present invention in its second aspect, relates to a method according to claim 17 for expanding a compressible operating fluid, for example gas or steam, in a turbine.
  • a compressible operating fluid for example gas or steam
  • the method comprises the steps of:
  • a turbine comprising a first shaft and a group of stages of first expansion defined by arrays of stator blades constrained to a stationary part of the turbine and arrays of rotor blades assembled on a first supporting disk fastened to said first shaft, and comprising a second shaft and a group of stages of second expansion defined by arrays of rotor blades assembled on said first supporting disk and arrays of rotor blades assembled on a second supporting disk fastened to the second shaft;
  • the method further comprises one or more of the following steps:
  • k'(is) Ah(i ot) / ( i 2 /2), where Ah(i S; to t) is defined above.
  • the group of stages of first expansion is not provided.
  • the operating fluid proceeds along a radial centripetal path, but inside a channel free of expansion stages and defined by stationary parts of the turbine, for example its volute, and possibly parts constrained to the first shaft and thereby rotating at the speed of the latter.
  • stationary parts of the turbine for example its volute, and possibly parts constrained to the first shaft and thereby rotating at the speed of the latter.
  • the other characteristics described above can also be present in this variation of the turbine and the method.
  • the embodiment for which the Applicant reserves the right of filing a divisional patent Application comprises at least one group of expansion stages defined by arrays of only rotor blades.
  • One or more arrays of rotor blades are constrained to the first shaft of the turbine and, alternated to these, one or more arrays of rotor blades are constrained to the second turbine shaft.
  • the first and second shaft rotate in opposite way on the common rotation axis; the first shaft rotates at a speed higher than the second shaft.
  • the group of expansion stages is defined by counter- rotating rotor arrays defining a radial centrifugal expansion path: the fluid expands in the radial direction away from the rotation axis of the shafts.
  • figure 1 is a schematic sectional view of a first embodiment of the turbine according to the present invention.
  • figure 2 is a schematic sectional view of the turbine shown in figure 1, with the stator parts and the rotor parts highlighted;
  • figure 3 is a schematic view, enlarged and in section, of a detail of the turbine shown in figure 1 ;
  • FIG. 4 is a schematic and sectional view of a detail of a second embodiment of the turbine according to the present invention.
  • figure 5 is a schematic and sectional view of a detail of a third embodiment of the turbine according to the present invention.
  • figure 6 is a schematic sectional view of a fourth embodiment of the turbine according to the present invention.
  • Figure 1 is a partial view, in a meridian section, of a turbine 1 according to the present invention for the expansion of a compressible operating fluid, for example an organic fluid in a Rankine cycle.
  • a compressible operating fluid for example an organic fluid in a Rankine cycle.
  • the turbine comprises a first shaft 2, whose longitudinal rotation axis is denoted by X-X, a second shaft 3 distinct from the first shaft but coaxial with respect to the latter, and an outer case 4 or volute, and at least two groups El, E2 of expansion stages, and preferably also the groups E3, E4.
  • the group El of stages of first expansion is the first group of stages the operating fluid encounters along its path inside the turbine. It is a group comprising at least one stage defined by arrays of stator blades and arrays of rotor blades alternated in radial direction with respect to the rotation axis X-X of the first shaft 2.
  • the arrays of rotor blades are in practice assembled on a supporting disk 5 keyed to the first shaft 2.
  • the arrays of rotor blades are on the contrary fastened to a stationary part of the turbine 1, as its volute 4.
  • the operating fluid is diverted between the groups El and E2 so that its expansion switches from radial centripetal to radial centrifugal, i.e. it moves away from the axis X-X.
  • the inversion occurs through appropriate passages obtained in the supporting disk 5.
  • the passages can be channels, spokes with no substantial expansion or an appropriate blade assembly characterized by an expansion with considerable enthalpy drop, preferably equal at least to 5% of the average enthalpy drop per stage.
  • the group E2 of stages of second expansion is only defined by arrays of rotor blades, i.e. no arrays stator blades are provided.
  • FIG. 3 is an enlargement of the area of groups El and E2, where different arrays of blades are clearly denoted.
  • the group El of stages of first expansion comprises a first stator array SI fastened to the volute 4, followed by a rotor array Rl assembled on the supporting disk 5, in its turn followed by a second stator array S2 also fastened to the volute 4.
  • the flow inversion occurs in channels C obtained through the supporting disk 5.
  • the group E2 of stages of second expansion alternatively comprises the rotor arrays R2, R3, R4 and R5.
  • the arrays R3 and R5 are constrained to the supporting disk 5 keyed on the first shaft 2, and therefore rotate on the axis X-X at the speed thereof.
  • the arrays R2 and R4 are constrained to a second supporting disk 6 keyed on the second shaft 3, and therefore rotate on the axis X-X at the speed of the shaft 3, in opposite way with respect to the arrays R3 and R5.
  • the rotation speed of the first shaft 2 is higher than the rotation speed of the second shaft 3, preferably at least 1.5 times and more preferably at least twice.
  • the turbine 1 is preferably provided with groups E3 and E4 of expansion stages downstream of the second group E2.
  • the group E3 is defined by arrays of stator blades S3 and S4 alternated with arrays of rotor blades R6 and R7 in radial centrifugal direction.
  • an array of angular blades AB Downstream of the group E3 an array of angular blades AB is provided as diverting the operating fluid flow in axial direction, i.e. parallel to the axis X-X and also preferably tangential, i.e. incident with respect to the plane of the drawing.
  • the angular blades AB are stator blades, but it is generally possible providing angular rotor blades.
  • the group E4 is defined by arrays of rotor blades R8, R9, RIO alternated to arrays of stator blades S5, S6 and defines an axial path.
  • the group El is on average at a diameter close to the diameter of the group E2 with respect to the axis X-X and at a smaller diameter with respect to the groups E3 and E4.
  • FIG 2 shows the turbine 1 also represented in figures 1 and 3, with the difference that the stator parts, the rotor part rotating with the first shaft 2 and the rotor part rotating with the second shaft 3 are highlighted by corresponding fillings.
  • the electric generators Gl and G2 are configured in this way: the generator Gl is directly assembled on the shaft 2 with no reduction gear, and the generator G2 is external to the shaft 3 and is coupled with the same by means of the reduction gear 11.
  • first supporting disk 5 and the second supporting disk 6 are constrained to the respective shafts 2 and 3 externally with respect to the corresponding bearings, according to a so-called 'cantilevered' configuration.
  • the bearings of the first shaft 2 are denoted by the numerals 7 and the first supporting disk 5 is external with respect to the same; similarly, the bearings of the second shaft 3 are denoted by the numerals 10 and the second supporting disk 6 is external with respect to the same and faces the first supporting disk 5.
  • Numeral references 8 and 9 identify the seals.
  • This configuration allows partially disassembling the turbine 1 in a practical way, by taking out the shafts 2 and 3 respectively from the bearings 7 and 10 and Opening' the groups of stages El, E2, etc.
  • first shaft 2 is directly connected to a generator Gl of suitable size, for example having two poles, without the interposition of a reduction gear.
  • first shaft 2 rotates at a speed of 3000 rpm.
  • second shaft 3 can be configured for the direct coupling with a corresponding generator G2, but in the example shown in the figures, the generator G2 is coupled with the shaft 2 through the interposition of the reduction gear 11.
  • the second shaft 3 rotates at a speed of 1500 rpm.
  • Figure 4 is an enlargement of the flow inversion area in a second embodiment of the turbine 1.
  • the first supporting disk 5 is U- shaped, if it is considered in meridian section.
  • Figure 5 refers to still another solution free of the group El but comprising, at the inlet, a stator blade assembly 12 having a variable pitch angle.
  • a stator blade assembly 12 having a variable pitch angle.
  • the numeral reference 13 part of the mechanism for adjusting the pitch angle of the blades is indicated.
  • Figure 6 shows a turbine ⁇ similar to that one shown in figures 1-3, but different from the latter for being free of the group El of stages of first expansion.
  • the operating fluid passes through the chamber C in radial centripetal direction, then passes through the channel C and expands through the group E2 of stages.
  • the groups E3 and E4 of stages are present.
  • the Applicant reserves the right of filing a divisional patent Application for this variation.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une turbine destinée à l'expansion d'un fluide de travail compressible, par exemple du gaz ou de la vapeur. La turbine comprend un premier groupe d'étages, désignés étages de première expansion, qui s'étend dans une direction centripète radiale, afin de réaliser une première expansion centripète, et un second groupe d'étages, désignés étages de seconde expansion, qui s'étend en aval des étages de première expansion afin de réaliser une seconde expansion centrifuge. Les réseaux de pales de rotor des étages de première expansion sont contraints à un premier arbre et les réseaux de pales de rotor des étages de seconde expansion sont contraints à un second arbre coaxial par rapport au premier arbre et sont interposés entre des réseaux supplémentaires de pales de rotor contraints au premier arbre. Le premier arbre tourne à une vitesse supérieure à celle du second arbre et dans une direction opposée. Les rotors portant les réseaux de pales de rotor sont contraints dans une configuration « en porte-à-faux » aux arbres respectifs, au niveau d'une extrémité de ceux-ci.
EP15736632.9A 2014-07-11 2015-06-15 Turbine et procédé d'expansion d'un fluide de travail avec saut d'enthalpie isentropique élevé Withdrawn EP3167158A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ITBS20140126 2014-07-11
PCT/IB2015/054505 WO2016005834A1 (fr) 2014-07-11 2015-06-15 Turbine et procédé d'expansion d'un fluide de travail avec saut d'enthalpie isentropique élevé

Publications (1)

Publication Number Publication Date
EP3167158A1 true EP3167158A1 (fr) 2017-05-17

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EP15736632.9A Withdrawn EP3167158A1 (fr) 2014-07-11 2015-06-15 Turbine et procédé d'expansion d'un fluide de travail avec saut d'enthalpie isentropique élevé

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Country Link
EP (1) EP3167158A1 (fr)
WO (1) WO2016005834A1 (fr)

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Publication number Priority date Publication date Assignee Title
CN109252900B (zh) * 2018-08-30 2021-10-08 上海理工大学 一种复合式透平

Family Cites Families (7)

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Publication number Priority date Publication date Assignee Title
FR1099735A (fr) * 1954-04-28 1955-09-08 Svenska Turbinfab Ab Turbine à écoulement radial à double rotation comprenant des groupes d'aubes espacés axialement
DE10213897A1 (de) * 2002-03-28 2003-10-09 Daimler Chrysler Ag Variabler Abgasturbolader
US6877951B1 (en) * 2003-09-23 2005-04-12 Essam T. Awdalla Rotary ram-in compressor
IT1393309B1 (it) 2009-03-18 2012-04-20 Turboden Srl Perfezionamenti ad una turbina per espansione di gas/vapore
IT1393310B1 (it) 2009-03-18 2012-04-20 Turboden Srl Turbina per espansione di gas/vapore perfezionata
ITMI20110684A1 (it) 2011-04-21 2012-10-22 Exergy Orc S R L Impianto e processo per la produzione di energia tramite ciclo rankine organico
ITBS20120008A1 (it) 2012-01-20 2013-07-21 Turboden Srl Metodo e turbina per espandere un fluido di lavoro organico in un ciclo rankine

Non-Patent Citations (2)

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Title
None *
See also references of WO2016005834A1 *

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