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5 EP 2 713 017 A2 6 superheater, respectively. [0024] At the outlet of the superheater 11 the working fluid circulating in the second closed loop 5 is in a super- heated, gaseous, high-pressure state. The high-pres- sure, superheated working fluid is then expanded in the turboexpander 13. Exhausted fluid exiting the turboex- pander 13 at a second, low pressure level, flows through the heat recuperator 15 and is finally condensed in a condenser 17. The condensation is obtained for instance by means of heat exchange between the condensing working fluid and external air or water. [0025] In the recuperator 15 low-temperature heat con- tained in the expanded fluid exiting the turboexpander 13 is exchanged against the cold pressurized fluid in the liquid state delivered by the circulating pump 7. [0026] In the exemplary embodiment illustrated in Fig. 2, the turboexpander 13 is used as a mechanical drive for driving a load. The turboexpander 13 can be mechan- ically connected by means of a mechanical transmission 19 to a driven turbomachine 21. For instance, the driven turbomachine 21 can be a compressor, for example a centrifugal compressor or an axial compressor. In other embodiments, the turbomachine 21 can be a pump or another driven turbomachine. [0027] In some exemplary embodiments, not shown, the first closed loop 4 can be omitted. In this case heat is directly transferred from the gas turbine discharge to the organic Rankine cycle. The heater 9 and superheater 11 can be integrated in the heat exchanger 3. A more compact installation is obtained, with reduced heat loss- es and increased overall efficiency of the system. [0028] In some embodiments, the turboexpander 13 can be a multistage, integrally geared turboexpander. In Fig.2 the turboexpander 13 is represented as a two- stage, integrally geared turboexpander. [0029] A fraction of the heat contained in the combus- tion gases discharged from the gas turbine 1 is thus trans- formed into useful mechanical power increasing the over- all efficiency of the system and the overall mechanical power produced thereby. [0030] The above described heat-recovery system has been described for improving the efficiency of a gas tur- bine installation, where the hot combustion gases of the gas turbine are cooled prior to being discharged in the atmosphere. The temperature range of the combustion gases is suitable for transforming the heat into mechan- ical power using an organic Rankine cycle. The thermo- dynamic cycle does not require water and can therefore be used where water is unavailable and a common steam cycle could not be used. [0031] The driven turbomachine 21, for instance a cen- trifugal compressor, can be used e.g. to process a refrig- erant fluid in an LNG system or can be used to forward a gas in a pipeline. [0032] Figs.3 and 4 schematically illustrate the main features of a two-stage turboexpander 13, which can be used in the ORC cycle 5 in Fig.2. The turboexpander 13 comprises a first, high pressure stage 13A and a second, low pressure stage 13B. The working fluid enters the first, high pressure stage 13A of the turboexpander 13, exits the first turboexpander stage 13A to be delivered through a pipe 24 to the inlet of the second, low pressure stage 13B of the turboexpander 13. [0033] A mechanical transmission 19 is provided be- tween the two-stage turboexpander 13 and the driven turbomachine 21. [0034] In the exemplary embodiment of Fig.3, the me- chanical transmission 19 comprises a gearbox 20 with two driving inlet shafts and one driven outlet shaft. Said driving inlet shafts are the shafts of the integrally geared multi-stage turboexpander 13. The outlet shaft is con- nected to the shaft of the driven turbomachine 21. Ref- erence number 31A designates the first inlet shaft on which a first impeller of the first, high pressure stage 13A of the turboexpander 13 is connected. The first inlet shaft 31A, therefore, rotates at the rotary speed of the impeller of the first, high pressure stage of the turboexpander 13. The impeller of the second, low pressure stage 13B of the turboexpander 13 is connected on a second inlet shaft 31B, which rotates at the rotary speed of the impeller of the second, low pressure stage 13B of the turboexpander 13. [0035] As best shown in Fig. 4, which illustrates a sche- matic representation of the mechanical transmission 19 in a front view according to line IV-IV of Fig. 3, the gear box 20 comprises a first gear 33A mounted on the first inlet shaft 31A and a second gear 33B mounted on the second inlet shaft 31B. The two gears 33A and 33B mesh with a central crown wheel 34. A third gear 33C of the gearbox 20 is mounted on an output shaft 19A, which is connected, for example through joints 22, to the shaft of the driven turbomachine 21. [0036] The first, second and third gears 33A, 33B and 33C advantageously have a diameter smaller than the diameter of the central crown wheel 34. [0037] In some embodiments, the third gear 33C has a diameter smaller than that the diameter of the central crown wheel 34, in order to augment the rotary speed of output shaft 19A connected to the driven turbomachine 21. [0038] A higher speed of the output shaft 19A allows to drive easily a centrifugal compressor 21 that requires to rotate at a higher rotary speed. [0039] The first and second gears 33A and 33B have different diameters in order to provide optimal rotary speed for each impeller of said first and second stage of the turboexpander 13. [0040] Advantageously this integrally geared solution is particularly useful in LNG systems or pipeline com- pression stations. [0041] Additionally the embodiment of Figs 3 and 4 im- proves the efficiency of the expansion phase, because each impeller can rotate at its optimal rotary speed. [0042] Moreover, the embodiment comprising a plural- ity of impellers allows exploiting the whole pressure drop of the high-pressure, superheated working fluid. 5 10 15 20 25 30 35 40 45 50 55 4PDF Image | organic rankine cycle for mechanical drive applications
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