WO2014053421A1 - A turboexpander and driven turbomachine system - Google Patents
A turboexpander and driven turbomachine system Download PDFInfo
- Publication number
- WO2014053421A1 WO2014053421A1 PCT/EP2013/070265 EP2013070265W WO2014053421A1 WO 2014053421 A1 WO2014053421 A1 WO 2014053421A1 EP 2013070265 W EP2013070265 W EP 2013070265W WO 2014053421 A1 WO2014053421 A1 WO 2014053421A1
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- WIPO (PCT)
- Prior art keywords
- turboexpander
- guide vanes
- inlet guide
- fluid
- driven
- Prior art date
Links
- 239000012530 fluid Substances 0.000 claims abstract description 61
- 230000009347 mechanical transmission Effects 0.000 claims abstract description 8
- 238000012545 processing Methods 0.000 claims abstract description 8
- 238000000034 method Methods 0.000 claims description 24
- 238000011084 recovery Methods 0.000 claims description 12
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- 238000013461 design Methods 0.000 description 9
- 230000008569 process Effects 0.000 description 7
- 239000008186 active pharmaceutical agent Substances 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 4
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- 239000000567 combustion gas Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000008016 vaporization Effects 0.000 description 3
- RGSFGYAAUTVSQA-UHFFFAOYSA-N Cyclopentane Chemical compound C1CCCC1 RGSFGYAAUTVSQA-UHFFFAOYSA-N 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000010248 power generation Methods 0.000 description 2
- 239000006200 vaporizer Substances 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 239000013529 heat transfer fluid Substances 0.000 description 1
- DMEGYFMYUHOHGS-UHFFFAOYSA-N heptamethylene Natural products C1CCCCCC1 DMEGYFMYUHOHGS-UHFFFAOYSA-N 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 239000003507 refrigerant Substances 0.000 description 1
- 238000005057 refrigeration Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 238000000844 transformation Methods 0.000 description 1
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
-
- 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
- F01K13/00—General layout or general methods of operation of complete plants
- F01K13/02—Controlling, e.g. stopping or starting
-
- 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
- F01K23/00—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids
- F01K23/02—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled
- F01K23/06—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle
- F01K23/10—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle with exhaust fluid of one cycle heating the fluid in another cycle
-
- 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
- F01K23/00—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids
- F01K23/02—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled
- F01K23/06—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle
- F01K23/10—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle with exhaust fluid of one cycle heating the fluid in another cycle
- F01K23/101—Regulating means specially adapted therefor
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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
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/18—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
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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
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
-
- 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
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/08—Adaptations for driving, or combinations with, pumps
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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
- F01D17/00—Regulating or controlling by varying flow
-
- 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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/02—Purpose of the control system to control rotational speed (n)
- F05D2270/024—Purpose of the control system to control rotational speed (n) to keep rotational speed constant
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/301—Pressure
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/301—Pressure
- F05D2270/3011—Inlet pressure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/301—Pressure
- F05D2270/3013—Outlet pressure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/303—Temperature
Definitions
- Embodiments of the subject matter disclosed herein generally relate to systems comprising turboexpanders and driven turbomachines and methods for operating the same.
- Turboexpanders are widely used for industrial refrigeration, oil and gas processing and in low temperature processes. In some known applications turboexpanders are used in heat recovery cycles to drive an electric generator. US 2011/0305556 discloses a system and method for power generation including a turboexpander with at least two expansion stages for heat recovery and mechanical power generation to drive an electric generator. In this known application the turboexpander is introduced in a Rankine cycle.
- EP 2400117 discloses the application of a turboexpander-compressor system according to the prior art, wherein the same fluid is processed in the turboexpander and in the compressor.
- Fig. 1 illustrates the turboexpander-compressor system of the prior art.
- the system is labeled 200.
- a turboexpander 210 has a turboexpander impeller 212.
- the turboexpander 210 receives an inlet gas flow at 214. Inside the turboexpander 210 the gas may expand and thus cause rotation of the turboexpander impeller 212.
- the expanded gas exits the turboexpander 210 at 216.
- a pressure pi and a temperature Tl of the inlet gas flow at 214, as well as a pressure p2 and a temperature T2 of the gas flow at the exit side 216 have values close to predetermined values.
- the turboexpander-compressor system operates in off-design conditions.
- the pressure pi of the incoming gas flow at 214 may be adjusted to become again close to the respective rated value, using, for example, a first set of moveable input guide vanes (IGV1) 218.
- the first set of moveable input guide vanes 218 are located at an inlet of the turboexpander 210.
- a compressor 224 has a compressor impeller 226.
- the compressor 224 receives the gas flow from the turboexpander 210 and delivers a compressed gas flow at the delivery side 228.
- the pressure of the gas flow may be altered due to other process components (e.g., separators, coolers, valves) and pressure losses, so that the gas flow at 216 has pressure p3 when entering the compressor 224.
- the mechanical work generated by the expansion of the gas in the turboexpander rotates the turboexpander impeller 212.
- the turboexpander impeller 212 is mounted on the same shaft 230 as the compressor impeller 226.
- the compressor impeller 226 therefore rotates due to the mechanical work generated during the expansion of the gas in the turboexpander 210.
- the rotation of the compressor impeller 226 provides energy used to compress the gas in the compressor 224.
- the mechanical work necessary to rotate the compressor impeller 226 affects the rotating speed u of the shaft 230 and, thereby, indirectly affects the process of expanding the gas inside the turboexpander 210.
- the turboexpander efficiency is related to a ratio of the rotating speed u of the shaft 230 and the enthalpy drop ⁇ across the turboexpander 210.
- the gas expansion in the turboexpander 210 may be considered approximately an isoentropic process.
- the characteristic parameters (i.e., pi, Tl, p2 and T2) of the gas expansion in the turboexpander 210 and the rotating speed u of the shaft 230 may not vary independently. Therefore, in off-design conditions, in order to maximize the turboexpander efficiency, the pressure p3 of the gas flow at the inlet 216 of the compressor 224 may be controlled, for example, by a second set of moveable inlet guide vanes IGV2 232 provid- ed at the compressor inlet. By modifying the pressure p3 of the gas flow 216 input in the compressor 224, the rotating speed u of the shaft 230 is modified and, therefore, the efficiency of the turboexpander 210 can be maximized.
- a controller 240 receives information regarding the pressure pi and the temperature Tl of the gas flow at the inlet side 214 of the turboexpander 210, the pressure p3 of the gas flow at the inlet 216 of the compressor 224, and the rotating speed u of the shaft 230, by suitable sensors.
- the controller 240 may send commands CI to IGV1 218 in order to adjust the pressure pi of the gas flow at the turboexpander inlet 214 to be within a predetermined range. Based on monitoring the acquired information, the controller 240 determines when the turboexpander-compressor system 200 functions in off-design conditions.
- the controller 240 determines that the turboexpander- compressor system 200 functions in off-design conditions, the controller 240 sends commands C2 to the second set of IGV2 232 to adjust the pressure p3 of the gas input into the compressor in order to maximize a ratio R between the rotating speed u of the shaft 230 and the enthalpy drop ⁇ across the turboexpander 210.
- the same controller controls the moveable inlet guide vanes of the turboexpander and the moveable inlet guide vanes of the compressor to optimize the efficiency of the system, based on the assumption that the same fluid is processed in the two turbomachines.
- the turboexpander-driven turbomachine system may include: a turboexpander configured for expanding a first fluid and comprising at least one expander stage with one expander impeller; at least a first set of moveable inlet guide vanes at the inlet of the expander stage; and a driven turbomachine configured for processing a second flu- id and comprising at least one turbomachine impeller provided with a second set of moveable inlet guide vanes at the inlet of the turbomachine impeller.
- the system may further include a mechanical transmission between the turboexpander and the driven turbomachine.
- the system may further comprise a controller connected to the second set of moveable inlet guide vanes and configured for controlling the second set of moveable inlet guide vanes to adjust the rotary speed of said driven turbomachine and said turboexpander.
- the first fluid can be processed in a closed heat re- covery thermodynamic cycle, and the moveable inlet guide vanes of the first set are used to adjust the operating conditions of the turboexpander based on the heat available from a heat source.
- the second fluid can e.g.
- the moveable inlet guide vanes of the second set are used for instance to adjust the flow rate of the second fluid through the driven tur- bomachine, to set, adjust or maintain the desired rotary speed of the system.
- the mechanical transmission is configured so as to provide a fixed transmission ratio between the turboexpander and the driven turbomachine.
- the turboexpander has a single impeller mounted on a shaft.
- the driven turbomachine has at least one impeller mounted on the same shaft, so that the two machines rotate at the same rotary speed, the transmission ratio being 1.
- a single shaft can be formed by one or more shaft portions. Joints can be provided to connect two or more shaft portions to one another. Joints can be rigid joints, elastic joints, or clutches or the like.
- the turboexpander can comprise more than one stage, each stage including at least one impeller. At least one or preferably all the impellers can be provided with respective moveable inlet guide vanes. If more than one set of moveable inlet guide vanes is provided, at the inlet of more than one stage, each set of moveable inlet guide vanes can be controlled independently of the other for op- timal operation of each turboexpander stage.
- the multistage turboexpander can be a so-called integrally geared turboexpander.
- An integrally geared turboexpander can include a central toothed wheel, meshing with two or more gears peripherally arranged around the axis of the toothed wheel.
- Each gear is mounted on a shaft of a corresponding turboex- pander impeller.
- each turboexpander stage can rotate at its own rotary speed, the speed ratio between the shafts being optimized to maximize the overall efficiency of the turboexpander.
- a further gear mounted on a power output shaft can mesh with the central toothed wheel.
- the power output shaft can in turn support one or more impellers of the driven turbomachine. With this arrangement, a fixed rotary speed ratio is provided between the power output shaft and each driving shaft of each turboexpander stage.
- the first set of moveable inlet guide vanes is configured for controlling at least one parameter of the first fluid, which is processed by the turboexpander.
- each impeller can be provided with its own first set of moveable inlet guide vanes.
- each set of moveable inlet guide vanes provided for the turboexpander can be designed for controlling at least one parameter of the first fluid entering the respective turboexpander stage.
- the parameter of the first fluid is a fluid pressure at the inlet of the turboexpander stage, or at each turboexpander stage provided with moveable inlet guide vanes.
- the controller is configured for receiving information on the rotary speed of the driven turbomachine and for control- ling the second set of moveable inlet guide vanes to adjust the rotary speed at a desired speed value. Since typically a fixed transmission ratio exists between the shaft of the driven turbomachine and the shaft of the turboexpander, or of the shaft of each turboexpander stage, controlling the rotary speed of the driven turbomachine implies also controlling the rotary speed of the turboexpander or of each turboexpander stage. Generally speaking, the controller can be configured to control the rotary speed according to any desired function.
- the controller is configured for maintaining the rotary speed at a fixed desired value, or within an allowable value range around a constant speed value, e.g. +/- 2% about the desired rotary speed, said values being only by way of example and not limiting the scope of the present disclosure.
- the first set of moveable inlet guide vanes at the inlet of the turboexpander, and/or each first set of moveable inlet guide vanes at the inlet of each turboexpander stage can be controlled for maximizing the power generated by the turboexpander.
- a controller and a servo-actuator can be provided for con- trolling said first set(s) of moveable inlet guide vanes.
- the controller can be configured for adapting the position of the moveable inlet guide vanes according to one or more parameters of the first fluid, flowing through the turboexpander, in order to maximize the energy recovered by expanding the fluid in the turboexpander.
- the fluid processed by the turboexpander is a working fluid of a closed thermodynamic cycle, for instance the fluid of a heat recovery cycle.
- the heat recovery cycle can be a Rankine cycle.
- the heat recovery cycle is an organic Rankine cycle.
- the heat recovery cycle can include a condenser, a pump, heat exchanging arrangements, for recovering heat from a heat source and vaporizing the fluid being processed by the heat recovery thermodynamic cycle.
- the cycle can include a heater and a super-heater arranged in series along the circuit of the working fluid, between the pump and the turboexpander.
- efficiency of the cycle can be increased by a recuperator, where heat in the expanded fluid exiting the turboexpander is transferred to the pressurized, cold fluid delivered by the pump.
- the driven turbomachine may comprise a pump or a compressor, e.g. a centrifugal compressor or centrifugal pump.
- the driven turbomachine can be a single-stage or multi-stage turbomachine.
- the disclosure generally relates to a method for operating a system comprising a turboexpander, a turbomachine mechanically driven by the turboexpander, at least a first set of moveable inlet guide vanes at the turboexpander, a second set of moveable inlet guide vanes at the driven turbomachine.
- the method comprises the steps of: expanding a first fluid through said turboexpander and producing mechanical power therewith; rotating said driven turbomachine by means of said power; processing a second fluid through said driven turbomachine; controlling said second set of moveable inlet guide vanes for adjusting the rotary speed of said driven turbomachine and said turboexpander.
- a further step of controlling the second set of moveable inlet guide vanes to maintain the rotary speed within a range around a constant value can further be provided.
- Fur- thermore also a step of controlling the first set of moveable inlet guide vanes for maximizing the power produced by said turboexpander can be provided.
- turboexpander and/or the driven turbomachine comprises more than one stage
- each stage can be provided with the respective set of moveable inlet guide vanes.
- first set of moveable inlet guide vanes can include a single set of moveable inlet guide vanes at the inlet of one turboexpander impeller, or more than one set, at the inlet of more than one such impeller.
- second set of moveable inlet guide vanes can include a single set of moveable inlet guide vanes at the inlet of one impeller of the driven turbomachine, or more than one set, at the inlet of more than one driven impeller.
- the method can comprise the step of recovering heat from a heat source by means of the first fluid processed by the turboexpander, and partly converting the heat in mechanical power in the turboexpander.
- the first fluid can be processed in a closed thermodynamic cycle, the method including the steps of condensing, pressurizing, heating, vaporizing the first fluid; expanding the first fluid in the turboexpander generating power and condensing again the expanded fluid.
- the method can include recovering heat from an upper thermodynamic cycle, such as a gas turbine cycle.
- the method can include the step of recovering heat from a source of renewable energy, such as a solar plant, by means of a solar concentrator, for instance.
- FIG. 1 illustrates a turboexpander-compressor system of the prior art
- Fig. 2 illustrates a heat recovery system with a turboexpander driving a driven tur- bomachine according to one embodiment of the present disclosure
- Fig. 3 illustrates a section of an integrally geared two-stage turboexpander driving a compressor according to one embodiment of the subject matter disclosed herein;
- Fig. 4 illustrates a schematic of the gear arrangement of the turboexpander- compressor system of Fig. 3; and
- Fig. 5 illustrates a block diagram of the method for controlling the inlet guide vanes of the driven turbomachine.
- Fig. 2 a possible application of the turboexpander-driven turbomachine system is illustrated and will be described in greater detail here below. It should be understood that the application of the turboexpander and driven turbomachine system of Fig. 2 is only one exemplary embodiment of possible applications and uses of a system according to the subject matter disclosed herein. Specifically, in the embodiment illustrated in Fig.2 the turboexpander recovers heat from a gas turbine driving a turbomachinery, such as a centrifugal compressor. However, it shall be understood that the source of heat to be recovered by means of the turboexpander could be any other heat source, e.g. a solar concentrator, a diesel engine for driving an electric generator, or the like.
- a gas turbine driving a turbomachinery
- the source of heat to be recovered by means of the turboexpander could be any other heat source, e.g. a solar concentrator, a diesel engine for driving an electric generator, or the like.
- reference number 1 designates a gas turbine for driving a driven turbomachinery, such as a compressor or compressor train 2, e.g. a centrifugal compressor or a centrifugal-compressor train.
- the compressor 2 can belong to a compressor system for processing a refrigerant in a natural gas liquefaction system.
- the gas turbine 1 can be used for electric generation purposes, rather than for mechanical drive. In such case the gas turbine 1 would be loaded with an electric generator.
- the gas turbine 1 generates combustion gases, which flow through a heat recovery exchanger 3 before being discharged in the atmosphere.
- a first closed loop 4 is used to remove heat from the heat exchanger 3 and deliver it to a second closed loop 5.
- a heat transfer fluid for example diathermic oil, is used to transfer heat removed from the combustion gases into the closed loop 5.
- Reference number 6 designates a circulating pump of closed loop 4.
- the second closed loop 5 is a thermodynamic cycle.
- a working fluid circulating in the closed loop 5 is subject to thermodynamic transformations including condensing, pumping, heating, vaporizing, expanding, to transform heat energy into mechanical energy.
- the thermodynamic cycle performed in closed loop 5 is based on the Rankine cycle principle.
- a suitable working fluid for example cyclopentane, or another suitable organic fluid usable in an organic Rankine cycle, is used in the second closed loop 5.
- the second closed loop 5 comprises a circulating pump 7, a vaporizer 9, a superheater 11, a turboexpander 13, a recuperator 15 and a condenser 17. Additional components can be present in the circuit, as known to those skilled in the art.
- the working fluid in the liquid state circulating in the second closed loop 5 is pumped at a first, higher pressure level by the circulating pump 7.
- the pressurized fluid is heated in the vaporizer 9 and in the superheater 11 by means of heat recovered by the fluid circulating in the first closed loop 4.
- the working fluid circulating in the second closed loop 5 is in a superheated, gaseous, high- pressure state.
- the high-pressure, superheated working fluid is then expanded in the turboexpander 13.
- Exhausted fluid exiting the turboexpander 13 flows through the heat recuperator 15 and is finally condensed in condenser 17.
- the condenser 17 can include a liquid/air heat exchanger. In the recuperator low-temperature heat contained 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.
- the turboexpander 13 is mechani- cally connected by means of a mechanical transmission 19 to a driven turbo machine 21.
- the driven turbomachine 21 can be a compressor, for example a centrifugal compressor. In other embodiments, the driven turbomachine 21 can be a pump.
- turboexpander 13 can be a multi- stage, integrally geared turboexpander. In the schematic representation of Fig. 2, however, the turboexpander 13 is illustrated in a simplified manner as a single stage turboexpander.
- the turboexpander 13 is provided with a first set of moveable inlet guide vanes 23, which can be controlled by a first controller 25, based on parameters of the thermody- namic cycle performed in the second driven loop 5, in order to optimize the efficiency of the turboexpander 13, i.e. in order to maximize the mechanical power generated by the turboexpander 13.
- the mechanical power generated by the turboexpander 13 can fluctuate, e.g. depending upon the operating conditions of the gas turbine 1.
- the temperature and the flow rate of the combustion gases can vary upon variation of the power generated by the gas turbine 1 , which is in turn determined by the mechanical power required to drive the driven turbomachinery 2. This affects the operation of the turboexpander 13.
- the thermodynamic cycle 5 can be used to recover heat from a different heat source, for example from a solar concentrator.
- the heat source from which the thermodynamic cycle 5 receives heat to be transformed into mechanical power can undergo fluctuations, which require adjustment of the operating conditions of the turboexpander 13, in order to maximize the available mechanical power on the power output shaft of the turboexpander 13.
- the driven turbomachine 21, e.g. a centrifugal compressor processes a fluid which is different from the fluid circulating in the thermodynamic cycle 5.
- the driven turbomachine 21 can be a compressor used to forward a gas in a pipeline.
- the compressor 21 is provided with a second set of moveable inlet guide vanes 27.
- a con- trailer 29 can be used to adjust the position of the moveable inlet guide vanes 27 based on the operating parameters of the compressor 21 and on the rotary speed thereof.
- the operating parameters of the compressor 21 are substantially represented by the inlet or suction pressure PI, the inlet or suction temperature Tl, the outlet or delivery pressure P2, and the outlet or delivery temperature T2.
- the rotary speed of the compressor 21 is linked to the rotary speed of the turboexpander 13, since the mechanical transmission 19 provides for a fixed ratio between the rotary speed of the turboexpander 13 and of the driven turbomachine or compressor 21. If a direct drive is provided, such as schematically represented by shaft 19, the ratio can be 1. In general terms, if a different rotary speed is required, a gearbox can be arranged between the turboexpander 13 and the compressor 21.
- the movable inlet guide vanes 27 of the driven turbomachine or compressor 21 are controlled such that the rotary speed of the driven turbomachine 21 , and therefore the rotary speed of the turboexpander 13 is maintained at a constant value or around a constant value within a range of tolerance.
- the first set of moveable inlet guide vanes 23 is used by controller 25 to optimize the operation of the turboexpander 13 based on the conditions in the thermodynamic cycle 5, thus maximizing the mechanical power output of the turboexpander 13, while the controller 29 adjusts the second set of moveable inlet guide vanes 27 to control the rotary speed of the turbomachinery such that said speed is maintained at around a constant value, representing the design speed of the turboexpander 13, i.e. the speed at which the turboexpander 13 has the maximum efficiency.
- the second set of moveable inlet guide vanes 27 is controlled so that the rotary speed of the turbomachinery is maintained around the desired set value, taking into consideration the operating parameters of the driven turbomachine 21, in particular the inlet or suction pressure PI and the outlet or delivery pressure P2, these two parameters being determined by the conditions, which must be maintained within the fluid which is processed by the driven turbomachine 21.
- the turboexpander 13 can be a single stage turboexpander with a single impeller mounted on a shaft, and provided with a single set of first moveable inlet guide vanes, as schematically shown in Fig.2.
- the impeller of the driven turbomachine 21 can be mounted on the opposite end of the shaft.
- the driven turbomachine 21 can be a multistage or a single stage turbomachine.
- Figs.3 and 4 schematically illustrate the main features of a multistage turboexpander 13, and more specifically a two-stage turboexpander having 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 through a respective first set of moveable inlet guide vanes 23 A, 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.
- reference number 23B designates the respective first set of moveable inlet guide vanes of the low pressure stage 13B of turboexpander 13.
- the two sets of moveable inlet guide vanes 23 A and 23B are controlled by a controller 25 in order to maximize the efficiency of the two-stage turboexpander 13. Maximization of a two-stage turboexpander in a heat recovery system, for example using an organic Rankine cycle, can be based for instance on an algorithm described in US 2011/0305556, the content of which is incorporated herein by reference.
- reference number 19 designates a mechanical transmission between the two-stage turboexpander 13 and the driven turbomachine 21, e.g. again a compressor, for instance a centrifugal compressor.
- Reference number 27 designates the second set of inlet guide vanes placed at the inlet of the driven turbomachine 21.
- PI and Tl indicate the inlet pressure and the inlet temperature at the suction side of the turbomachine 21.
- P2 and T2 designate the outlet pressure and outlet temperature at the delivery side of the driven turbomachine 21.
- the mechanical transmission 19 comprises a gearbox 20 with two driving inlet shafts and one driven outlet shaft.
- Reference number 31 A designates the first inlet shaft on which a first impeller of the first, high pressure stage 13A of the turboexpander 13 is supported.
- the first inlet shaft 31 A 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 supported on a second inlet shaft 3 IB which rotates at the rotary speed of the impeller of the second, low pressure stage 13B of the turboexpander 13.
- the gear box 20 comprises a first gear 33 A mounted on the first inlet shaft 31 A and a second gear 33B mounted on the second shaft 3 IB.
- 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.
- the transmission ratios between the components 33A, 33B, 33C, 34 of the gearbox 20 are selected such that the two stages 13 A, 13B of the two-stage turboexpanders 13 can rotate at the required design speed and drive the driven turbomachine 21 at the designed speed of the latter.
- controller 29 By means of controller 29 and a suitable servo-actuator 40, the rotary speed of the driven turbomachine 21 and consequently the rotary speed of the first turboexpander stage 13A and the second turboexpander stage 13B can be controlled and adjusted.
- a sensor 41 detects for example the rotary speed of the output shaft 19A of gearbox 20 and said parameter is used as a control parameter by the controller 29 to adjust the second set of moveable inlet guide vanes 27 of the compressor 21 in order, for example, to maintain the rotary speed at the required value or within a range of tolerance around said value.
- the control algorithm performed by the controller 29 is summarized in Fig. 5. This algorithm applies irrespective of the number of stages of the turboexpander 13, which is controlled independently of the driven turbomachine 21 by the controller 25, for example using the algorithm disclosed in the above mentioned US 2011/0305556.
- the diagram illustrates the following.
- the sensor 41 measures the actual rotary speed, indicated as SI in Fig. 5, and said value is delivered to controller 29.
- the controller 29 checks whether the measured speed SI is within a range of tolerance around a set operating speed, which corresponds to design speed of the two turboexpander stages 13 A, 13B, the speed ratio of the gearbox 20 being taken into consideration.
- the required constant speed is designated DS. +/- AS designates a range of tolerance around the desired speed value DS. If the measured value SI is within the range of tolerance no action is taken and the controller 29 reiterates the algorithm step.
- the controller checks whether such measured value is lower than the minimum acceptable speed value DS-AS. If this is the case, the controller 29 generates a signal which, by means of the servo-actuator 40, closes the second set of moveable inlet guide vanes. Otherwise, i.e. if the measured value SI is above DS+AS, the controller causes the second set of moveable inlet guide vanes to open.
- a rotary speed drop under the minimum admissible value DS-AS indicates that the power available from the turboexpander 13 is insufficient to process the flow rate of the fluid currently flowing through the driven turbomachine 21.
- Clos- ing the set of moveable inlet guide vanes 27 of the driven turbomachine 21 reduces the flow rate of the fluid processed by the driven turbomachine 21, thus increasing the rotary speed back to a value within the admissible range of tolerance around value DS.
- the mechanical power available from the turboexpander 13 is higher than that required for processing the actual flow rate of the fluid flowing through the driven turbomachine 21.
- a higher flow rate can be processed in order to fully exploit the available mechanical power on the output shaft 19 A, and therefore the moveable inlet guide vanes 27 of the driven turbomachine 21 are opened to allow a higher flow rate to be processed.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Turbines (AREA)
- Control Of Positive-Displacement Air Blowers (AREA)
Abstract
Description
Claims
Priority Applications (9)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
MX2015004159A MX2015004159A (en) | 2012-10-01 | 2013-09-27 | A turboexpander and driven turbomachine system. |
EP13773212.9A EP2917506B1 (en) | 2012-10-01 | 2013-09-27 | A turboexpander and driven turbomachine system |
CN201380051456.4A CN104822906B (en) | 2012-10-01 | 2013-09-27 | Turbo-expander and driven turbine wheel machine system |
KR1020157008415A KR20150060742A (en) | 2012-10-01 | 2013-09-27 | A turboexpander and driven turbomachine system |
RU2015110478A RU2643281C2 (en) | 2012-10-01 | 2013-09-27 | Installation with turboexpander and drive turbomachine |
BR112015007309A BR112015007309A2 (en) | 2012-10-01 | 2013-09-27 | turboexpander and driven turbomachine system and method of operating a system |
US14/432,839 US10066499B2 (en) | 2012-10-01 | 2013-09-27 | Turboexpander and driven turbomachine system |
AU2013326661A AU2013326661A1 (en) | 2012-10-01 | 2013-09-27 | A turboexpander and driven turbomachine system |
CA2886300A CA2886300C (en) | 2012-10-01 | 2013-09-27 | A turboexpander and driven turbomachine system |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
IT000196A ITFI20120196A1 (en) | 2012-10-01 | 2012-10-01 | "A TURBOEXPANDER AND DRIVEN TURBOMACHINE SYSTEM" |
ITFI2012A000196 | 2012-10-01 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2014053421A1 true WO2014053421A1 (en) | 2014-04-10 |
Family
ID=47278385
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2013/070265 WO2014053421A1 (en) | 2012-10-01 | 2013-09-27 | A turboexpander and driven turbomachine system |
Country Status (11)
Country | Link |
---|---|
US (1) | US10066499B2 (en) |
EP (1) | EP2917506B1 (en) |
KR (1) | KR20150060742A (en) |
CN (1) | CN104822906B (en) |
AU (1) | AU2013326661A1 (en) |
BR (1) | BR112015007309A2 (en) |
CA (1) | CA2886300C (en) |
IT (1) | ITFI20120196A1 (en) |
MX (1) | MX2015004159A (en) |
RU (1) | RU2643281C2 (en) |
WO (1) | WO2014053421A1 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
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US20170023011A1 (en) * | 2014-03-11 | 2017-01-26 | Nuovo Pignone Srl | Turbomachine assembly |
EP3482490B1 (en) * | 2016-07-08 | 2022-06-01 | Nuovo Pignone Tecnologie - S.r.l. | Variable speed transmission with auxiliary driver and system using same |
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ITFI20120193A1 (en) * | 2012-10-01 | 2014-04-02 | Nuovo Pignone Srl | "AN ORGANIC RANKINE CYCLE FOR MECHANICAL DRIVE APPLICATIONS" |
FR3007462B1 (en) * | 2013-06-21 | 2017-11-24 | Hispano-Suiza | TURBOMACHINE ACCESSORY BOX EQUIPPED WITH CENTRIFUGAL PUMP |
WO2016128319A1 (en) * | 2015-02-09 | 2016-08-18 | Nuovo Pignone Tecnologie Srl | A turboexpander-generator unit and a method for producing electric power |
IT201600077686A1 (en) * | 2016-07-26 | 2018-01-26 | Turboden Spa | METHOD OF CONTROL OF A COMPRESSOR MECHANICALLY COUPLED TO A TURBINE |
KR102348113B1 (en) * | 2017-05-11 | 2022-01-07 | 현대자동차주식회사 | Waste heat recovery expander apparatus and waste heat recovery system |
EP3714222B1 (en) * | 2017-11-21 | 2024-08-28 | Aestus Energy Storage, LLC | Thermal storage system charging |
US10895409B2 (en) * | 2017-11-21 | 2021-01-19 | Aestus Energy Storage, LLC | Thermal storage system charging |
CN107965355A (en) * | 2017-11-28 | 2018-04-27 | 西安交通大学 | A kind of combination power device |
US10570783B2 (en) | 2017-11-28 | 2020-02-25 | Hanwha Power Systems Co., Ltd | Power generation system using supercritical carbon dioxide |
KR102592235B1 (en) * | 2019-03-11 | 2023-10-20 | 한화파워시스템 주식회사 | Supercritical CO2 generation system |
AU2020101347B4 (en) * | 2020-07-13 | 2021-03-18 | Volt Power Group Limited | A waste heat recovery system |
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- 2013-09-27 CA CA2886300A patent/CA2886300C/en active Active
- 2013-09-27 BR BR112015007309A patent/BR112015007309A2/en not_active IP Right Cessation
- 2013-09-27 CN CN201380051456.4A patent/CN104822906B/en active Active
- 2013-09-27 US US14/432,839 patent/US10066499B2/en active Active
- 2013-09-27 RU RU2015110478A patent/RU2643281C2/en active
- 2013-09-27 KR KR1020157008415A patent/KR20150060742A/en not_active Application Discontinuation
- 2013-09-27 MX MX2015004159A patent/MX2015004159A/en unknown
- 2013-09-27 EP EP13773212.9A patent/EP2917506B1/en active Active
- 2013-09-27 WO PCT/EP2013/070265 patent/WO2014053421A1/en active Application Filing
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Also Published As
Publication number | Publication date |
---|---|
BR112015007309A2 (en) | 2017-08-08 |
CA2886300C (en) | 2020-08-25 |
RU2015110478A (en) | 2016-11-27 |
CN104822906B (en) | 2017-10-10 |
CN104822906A (en) | 2015-08-05 |
EP2917506A1 (en) | 2015-09-16 |
RU2643281C2 (en) | 2018-01-31 |
AU2013326661A1 (en) | 2015-04-09 |
ITFI20120196A1 (en) | 2014-04-02 |
US10066499B2 (en) | 2018-09-04 |
KR20150060742A (en) | 2015-06-03 |
US20150292349A1 (en) | 2015-10-15 |
CA2886300A1 (en) | 2014-04-10 |
EP2917506B1 (en) | 2019-11-06 |
MX2015004159A (en) | 2015-07-06 |
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