WO2014161661A1 - Procédé et système de cogénération de chaleur/énergie avec une machine à combustion interne pour mettre en œuvre le procédé - Google Patents

Procédé et système de cogénération de chaleur/énergie avec une machine à combustion interne pour mettre en œuvre le procédé Download PDF

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Publication number
WO2014161661A1
WO2014161661A1 PCT/EP2014/000878 EP2014000878W WO2014161661A1 WO 2014161661 A1 WO2014161661 A1 WO 2014161661A1 EP 2014000878 W EP2014000878 W EP 2014000878W WO 2014161661 A1 WO2014161661 A1 WO 2014161661A1
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WO
WIPO (PCT)
Prior art keywords
flow
bypass
exhaust gas
combustion chamber
temperature
Prior art date
Application number
PCT/EP2014/000878
Other languages
German (de)
English (en)
Inventor
Axel Widenhorn
Thilo KISSEL
Dominik LEBKÜCHNER
Original Assignee
Dürr Systems GmbH
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 Dürr Systems GmbH filed Critical Dürr Systems GmbH
Publication of WO2014161661A1 publication Critical patent/WO2014161661A1/fr

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Classifications

    • 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
    • F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
    • 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
    • F02C9/48—Control of fuel supply conjointly with another control of the plant
    • F02C9/50—Control of fuel supply conjointly with another control of the plant with control of working fluid flow
    • F02C9/52—Control of fuel supply conjointly with another control of the plant with control of working fluid flow by bleeding or by-passing the working fluid
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • 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
    • F05D2270/05—Purpose of the control system to affect the output of the engine
    • F05D2270/053—Explicitly mentioned power

Definitions

  • the invention relates to a method for operating an internal combustion engine in a combined heat and power system and a combined heat and power system with such an internal combustion engine for carrying out the method.
  • Combined heat and power systems of this type include in a known design in addition to the internal combustion engine itself nor a drivable by the internal combustion engine power converter, in particular in the form of an electric generator and a waste heat for the use of waste heat contained in the exhaust gas of the internal combustion engine.
  • a micro gas turbine is based on a single shaft system with the compressor, turbine and generator mounted on a central shaft.
  • the mentioned micro gas turbines are provided with a recuperator.
  • the recuperator is a heat exchanger usually integrated in the system in which the thermal energy of the exhaust gas is transferred to the compressed combustion air.
  • the compressed in the compressor and thus preheated combustion air is thus in the recuperator further heated.
  • In the combustion chamber of this compressed and preheated air fuel is supplied and burned, whereby the temperature further increases.
  • the system is designed and optimized for one operating point.
  • the recuperator ensures both the combustion air as well as the
  • the invention is therefore based on the object to provide an operating method for an internal combustion engine in a cogeneration system, by means of which an improved fuel efficiency can be achieved with varying heat requirement.
  • the invention is further based on the object of specifying a combined heat and power system with an internal combustion engine, which has an improved fuel efficiency with varying heat demand.
  • the combined heat and power system with a controllable fuel mass flow supplied internal combustion engine, a drive connected to the internal combustion engine force transducer, in particular a generator, a powered by the internal combustion engine waste heat, in particular for heating an optional heat exchanger, a recuperator with at least a controllable with respect to a flow bypass line and a control unit comprises.
  • the associated operating method according to the invention comprises the following method steps, wherein the control unit is designed to carry out the method in the cogeneration system with these steps:
  • a fuel mass flow leading into the combustion system is adjusted to provide a first mechanical power to the power take-off device and a first thermal power to the waste heat device;
  • a second operating state is brought about, including the flow through the at least one bypass line with increasing thermal Power requirement is increased and reduced with decreasing thermal power consumption;
  • the fuel mass flow leading into the combustion chamber system is increased with increasing thermal power requirement and reduced with decreasing thermal power requirement.
  • the invention Design and process concept allows for the same electrical power a larger thermal performance is provided with improved fuel efficiency.
  • the partial load capacity is also significantly extended, since a low electrical or mechanical output, a high thermal output is made possible. These two variables were previously more interdependent in their dependence.
  • the variety of possible operating states is considerably expanded.
  • the internal combustion engine can be integrated even more in the processes.
  • the use of the bypass lines leads to lower pressure losses in the flow guide, whereby a possible reduction in the electrical efficiency due to lack of recuperation can be at least partially compensated. Transient processes with changing temperature requirements can be carried out with good fuel efficiency.
  • the fuel mass flow is adjusted such that the first mechanical power of the first operating state remains at least approximately the same even in the second operating state.
  • the fuel mass flow is adjusted by means of a closed control loop such that the mechanical power is adjusted independently of the operating state to an at least approximately constant value. With little effort, a high accuracy of the power control and the temperature control in the system can be achieved.
  • the internal combustion engine may be a piston engine or the like and is preferably designed as a gas turbine device, in particular as a micro gas turbine.
  • the gas turbine apparatus or the micro gas turbine has a combustion chamber system, a turbine arranged on a turbine shaft and fired by the combustion chamber system, and a compressor, which is preferably arranged non-rotatably on the turbine shaft.
  • the compressor is designed and configured to supply the combustor system with a compressed oxidant stream, in particular a compressed combustion air stream.
  • the combustion chamber system has at least one controllable fuel supply.
  • the recuperator is provided and configured to transmit at least part of the thermal power of an exhaust gas flow of the combustion chamber system to the oxidant flow. For this purpose, the following method steps are provided:
  • the micro gas turbine is initially operated in the first operating state, in which by the exothermic reaction by means of the combustion chamber a reference temperature in the exhaust gas flow, in particular a turbine outlet temperature of the exhaust gas flow in the amount of a defined nominal temperature prevails, and at the output side of the recuperator in the region of the waste heat a useful temperature of the Exhaust gas flow prevails;
  • the fuel mass flow is adjusted substantially in synchronism with the adaptation of the flow through the at least one bypass line in such a way that a change in the Reference temperature to the target temperature is at least partially counteracted.
  • another reference temperature such as the turbine inlet temperature or the combustion chamber temperature
  • another reference temperature such as the turbine inlet temperature or the combustion chamber temperature
  • the fuel mass flow is preferably adjusted in such a way that the reference temperature is kept at the approximately constant value at the setpoint temperature. This ensures that the internal combustion engine or the micro gas turbine is operated at its design operating point with optimum fuel efficiency.
  • the at least one bypass line has an actuator drivable or adjustable control, in particular a control valve or a control valve for controlling the gas flow, wherein a leading to the combustion chamber fuel line via an actuator drivable or adjustable control, in particular a control valve, a control valve and / or a fuel injector for controlling the fuel flow, wherein the control unit is operatively connected to the control of the at least one bypass line and the control element of the fuel line, and preferably wherein the control of the at least one bypass line, the control element of the fuel line, the control unit and in particular a temperature sensor Part of a closed loop for regulation the mechanical power output of the internal combustion engine are.
  • a control loop can be achieved a very accurate temperature control, as a result, the efficiency of the micro gas turbine and the combined heat and power system remains optimal overall even with varying, transient heat requirements.
  • the bypass line is designed as a cold air bypass for bypassing the combustion air area.
  • the useful temperature of the exhaust gas flow is adjusted by changing the combustion air flow through the cold air bypass.
  • the cold air bypass and its control operates at relatively low temperatures, so that its thermal load is low and the structural design can be kept simple.
  • the bypass line is designed as an exhaust bypass for bypassing the exhaust area.
  • the useful temperature of the exhaust gas flow is adjusted by changing the exhaust gas flow through the exhaust gas bypass.
  • the thermal design of the recuperator requires reliability in the case of closed bypass lines, in which case the heat load of the recuperator is highest. Proceeding from this, opening the exhaust gas bypass leads to a reduction in temperature and thus to a reduction in the temperature load. This makes it easy to keep the design simple and increase the life.
  • both a cold air bypass and an exhaust gas bypass are provided.
  • a control or regulation of the combustion chamber temperature is carried out by coordinated and mutual adjustment of the fuel mass flow and the flow rates through the two bypass lines.
  • Temperature control of individual components of the combined heat and power system to control or keep low.
  • Fig. 1 in a schematic block diagram of an inventively trained
  • FIG. 2 a variant of the arrangement according to FIG. 1, in which an exhaust area of the recuperator can be bypassed by means of a bypass line formed as an exhaust bypass, and wherein the combustion chamber temperature of the micro gas turbine is tracked by the control unit with varying flow through the exhaust gas bypass,
  • FIG. 3 is a schematic block diagram of another inventively designed combined heat and power system both with a cold air bypass according to FIG. 1 and with an exhaust gas bypass according to FIG. 2.
  • FIG. 1 shows in a schematic block diagram a first exemplary embodiment of a combined heat and power system 1, which is supplied with a controllable fuel mass flow combustion engine, a drive connected to the internal combustion engine force converter 3, a powered by the internal combustion engine waste heat in particular Heating of an optionally provided heat exchanger 4, a recuperator 5 with at least one controllable with respect to a flow bypass line 6 and a control unit 20 includes.
  • the internal combustion engine may be a piston engine or the like and is in the preferred embodiment shown a gas turbine device, here a micro gas turbine 2.
  • the nominal power of the micro gas turbine 2 is preferably in a range of 25 kW inclusive up to and including 500 kW.
  • the micro gas turbine 2 is formed as a single-shaft turbine with a central and continuous turbine shaft 19, and further comprises an on the turbine shaft 19 rotationally fixed compressor 17 for an oxidant stream, here combustion air, a combustion chamber system 8 for the combustion of fuel with the 'compacted Combustion air, and a non-rotatably mounted on the turbine shaft 19 and fired by the combustion chamber system 8 turbine 18 for the relaxation of the resulting compressed and hot exhaust gases while obtaining mechanical energy.
  • the turbine shaft 19 is rotationally driven, which in turn drives the compressor 17 attached to the turbine shaft 19 and the force converter 3 also attached to it or thus driven thereto.
  • the force transducer 3 is in the preferred embodiment shown an electric generator for the production of electrical energy, but may also be another type of engine, for example, to provide mechanical energy or a combination of both.
  • the exhaust gas flow 16 is removed from thermal power and supplied to the heat user.
  • the exhaust gas stream 16 can also be used directly, for example, for a drying process.
  • a first operating state or initial or normal state described below that by means of the compressor 17 Combustion air is sucked from the environment. It may be appropriate to use this intake combustion air simultaneously as cooling air for the force transducer 3. In this case, the intake combustion air undergoes a first
  • the combustion air is in the compressor to a
  • Combustion air flow 15 compressed at about 4 bar pressure and preheated to about 220 ° C.
  • the compressed and preheated combustion air stream 15 is passed through a combustion air region 13 of the recuperator 5 and further heated to about 600 ° C, optionally up to 620 ° C.
  • the combustion air flow 15 is passed through the combustion chamber system 8, in which also fuel is introduced by means of a schematically indicated fuel line 11.
  • the combustion chamber system 8 is preferably designed for the flameless oxidation of the fuel (FLOX combustion), but can also be designed for a diffusion-based or premixed oxidation.
  • FLOX combustion the combustion chamber system indicated here only schematically is divided in practice into a pilot stage and a downstream main stage.
  • the combustion produces a compressed exhaust gas flow 16 with a renewed increase in combustion chamber temperature.
  • the combustion chamber temperature on the input side of the turbine 18 is in the amount of a defined nominal combustion chamber temperature of up to 960 ° C.
  • the first operating state can also be, for example, in the case of a lower mechanical or electrical energy requirement at the force transducer 3, a partial load state with a lower nominal combustion chamber temperature.
  • the exhaust stream 16 is expanded in the turbine 18, with its temperature dropping to about 650 ° C.
  • This still hot exhaust gas stream 16 is passed through an exhaust gas region 14 of the recuperator 5 which is fluidically separated from the combustion air region 13 but connected in a heat-transmitting manner.
  • a heat transfer from exhaust gas flow 16 to the combustion air flow 15 instead, wherein the combustion air flow 15 is heated as described above, and wherein the exhaust gas flow 16 is further cooled to a useful temperature of about 300 ° C.
  • the exhaust gas stream 16 After passing through the recuperator 5, the exhaust gas stream 16 is led to the downstream heat removal device with the optional heat exchanger 4, where a first thermal power is provided to the waste heat device, and where by means of the waste heat device as needed in the exhaust gas stream cooled to useful temperature 16 still included Waste heat can be dissipated and used as thermal energy.
  • a first mechanical power is provided at the output device, here at the force converter 3, converted into electrical power in the generator, and supplied to the user.
  • a second operating state is brought about according to the invention, including the temperature of the exhaust gas stream 16 in the region of the heat exchanger 4 is also changed .
  • at least one, in the embodiment of FIG. 1 exactly one with respect to their flow controllable bypass line 6 is provided, which is designed here as a cold air bypass for bypassing the combustion air region 13.
  • the bypass line 6 is provided with a controllable by an actuator or adjustable control element, in particular with a
  • Control valve 9 or a master key for controlling the Gäs presspoundes provided, wherein the control valve 9 is connected via an indicated data and control line to the control unit 20 and is driven by the latter.
  • the exhaust gas temperature of the exhaust gas stream 16 by increasing the combustion air flow through the Cold air bypass increased.
  • the control valve 9 via the control unit as needed partially or completely opened, as a result, a more or less pronounced partial flow of the combustion air flow 15, with fully open control valve 9 even approximately the entire combustion air flow 15 is not through the combustion air region 13 of the recuperator 5, but is directed around this.
  • the exhaust gas temperature of the exhaust gas stream 16 is reduced by reducing the combustion air flow through the cold air bypass.
  • the useful temperature of the exhaust stream 16 can be adjusted downstream of the recuperator 5 in a range between the undisturbed temperature already described above directly downstream of the compressor 17 and the useful temperature already described without bypass insert.
  • a control throttle 22 is optionally arranged, which is connected via a schematically indicated data and control line to the control unit 20 and is driven by the latter.
  • the control throttle 22 is kept fully open in order to allow unimpeded flow of the combustion air flow 15 through the recuperator.
  • FIG. 2 shows a variant of the arrangement according to FIG. 1, in which at least one bypass line 7, which is controllable in this case with respect to its flow rate, is likewise provided for the increase of the temperature of the exhaust gas flow 16 as required.
  • the bypass line 7 according to FIG. 2 is designed as an exhaust gas bypass for bypassing the exhaust gas region 14.
  • the bypass line 7 is provided with a controllable by an actuator or adjustable control, in particular with a control valve 10 or a control valve for controlling the gas flow, the control valve 10 is connected via an indicated data and control line to the control unit 20 and is controlled by the latter ,
  • the control valve 10 is partially or fully opened as required by the control unit, as a result, a more or less pronounced partial flow of the exhaust gas stream 16, with fully open control valve 10 even approximately the entire exhaust stream 16 not through the exhaust gas portion 14 of the recuperator 5, but is directed around this.
  • a control valve 10 or a control valve for controlling the gas flow the control valve 10 is connected via an indicated data and control line to the control unit 20 and is controlled by the latter .
  • the control valve 10 is partially or fully opened as required by the control unit, as a result, a more or less pronounced partial flow of the exhaust gas stream 16, with fully open control valve 10 even approximately the entire exhaust stream 16 not through the exhaust gas portion 14 of the recuperator 5, but is directed around this.
  • the exhaust gas flow 16 in the recuperator 5 is removed as a result only a reduced or no amount of heat more.
  • the exhaust gas temperature of the exhaust gas stream 16 is reduced by reducing the exhaust gas flow through the exhaust gas bypass.
  • the useful temperature of the exhaust gas stream 16 can be adjusted downstream of the recuperator 5 in a range between the undisturbed temperature already described above directly downstream of the compressor 17 and the useful temperature already described without bypass insert.
  • a control throttle 23 is arranged, which is connected via a schematically indicated data and control line to the control unit 20 and is driven by the latter.
  • the control throttle 23 is kept fully open in order to allow unimpeded flow of the exhaust gas flow 16 through the recuperator.
  • the control throttle 23 is - as shown here - preferably arranged on the output side of the exhaust gas region 14, but can also be positioned on the input side of it.
  • FIG. 3 shows a further variant of the arrangements according to FIGS. 1, 2, in which two bypass lines 6, 7 controllable with respect to their flow rate are provided for the increase in the temperature of the exhaust gas stream 16, namely the bypass line 6 designed as a cold air bypass
  • the physical design of the bypass lines 6, 7 and the control of the control valves 9, 10 and the control throttles 22, 23 is identical as described above, with the difference that here Both bypass lines are present and operated as needed alternately or in combination with each other.
  • a control or regulation of the combustion chamber temperature is carried out by coordinated and mutual adjustment of the fuel mass flow and the flow rates through the two bypass lines 6, 7.
  • the recuperator 5 When the control valves 9, 10 are fully open, the recuperator 5 at least approximately assumes the ambient temperature, since neither heat from the combustion air flow 15 nor from the exhaust gas flow 16 is introduced here. In addition to extended possibilities for Temperaturtuhrung the combustion air flow 15 and the exhaust gas flow 16, there are also additional opportunities that
  • Temperature load of individual components of the combined heat and power system 1 to control or keep low.
  • the control valve 12 By means of the control valve 12, the fuel mass flow can be changed starting from the initial state described above. During combustion, more or less heat energy is released compared to the first operating state, whereby a deviation of the combustion chamber temperature from the nominal combustion chamber temperature is at least reduced. Preferably, the fuel mass flow is changed in its amount so far that the combustion chamber temperature is maintained at least approximately constant on the combustion chamber target temperature.
  • the at least one control valve 9, 10 of the at least one bypass line 6, 7, the control valve 12 of the fuel line 11, the control throttles 22, 23, the control unit 20 and a temperature sensor 21 form a closed loop.
  • Temperature sensor 21 is arranged here by way of example at the outlet of turbine 18 for determining the turbine outlet temperature, but may also be positioned at another suitable location, for example at the inlet of turbine 18 or in combustion chamber system 8. In any case, by means of the temperature sensor 21 either directly or indirectly via known thermodynamic relationships the
  • the exhaust gas temperatures can be adjusted freely and continuously between about 170 and 670 ° C, preferably between 200 and 650 ° C. As a result, the range of application of the micro gas turbine 2 and thus of the combined heat and power system 1 is considerably increased.
  • the design and method concept according to the invention makes it possible to provide greater thermal output with improved efficiency for the same electrical output.
  • the partial load capacity is also significantly extended, since a low electrical or mechanical output, a high thermal output is made possible. These two variables were previously more interdependent in their dependence.
  • micro gas turbine 2 can be integrated even more into the processes, or can better follow the process requirements.
  • bypass lines 6, 7 leads to lower pressure losses in the flow guide, whereby a possible reduction of the electrical efficiency due to lack of recuperation can be at least partially compensated. Transient processes with changing temperature requirements can be carried out with good efficiency.

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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)
  • Control Of Turbines (AREA)

Abstract

L'invention concerne un procédé de fonctionnement d'une machine à combustion interne dans un système de cogénération de chaleur/énergie (1) ainsi qu'un système de cogénération de chaleur/énergie (1) comprenant une telle machine à combustion interne. Le système de cogénération de chaleur/énergie (1) comprend la machine à combustion interne dotée d'un système de chambre de combustion (8), un transducteur de force (3) relié en entraînement à la machine à combustion interne, un dispositif à dissipation de chaleur alimenté par la machine à combustion interne, un récupérateur (5) muni d'au moins une conduite de dérivation (6, 7) à débit réglable, ainsi qu'une unité de commande (20). Dans un premier état opérationnel, un débit massique de combustible acheminé dans le système de chambre de combustion (8) est réglé de telle sorte qu'une première puissance mécanique est délivrée au dispositif moteur ainsi qu'une première puissance thermique au dispositif à dissipation de chaleur. En présence d'un besoin en puissance thermique du consommateur de chaleur qui varie par rapport au premier état opérationnel, un deuxième état opérationnel est mis en action afin d'accroître le débit dans ladite conduite de dérivation (6, 7) lorsque le besoin en puissance thermique augmente et de le réduire lorsque le besoin en puissance thermique diminue, et/ou pour la mise en action du deuxième état opérationnel, notamment de manière sensiblement synchrone avec la variation du débit dans ladite conduite de dérivation (6, 7), le débit massique de combustible acheminé dans le système de chambre de combustion (8) est accru lorsque le besoin en puissance thermique augmente et réduit lorsque le besoin en puissance thermique diminue.
PCT/EP2014/000878 2013-04-05 2014-04-02 Procédé et système de cogénération de chaleur/énergie avec une machine à combustion interne pour mettre en œuvre le procédé WO2014161661A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102013005764.7 2013-04-05
DE102013005764.7A DE102013005764A1 (de) 2013-04-05 2013-04-05 Verfahren und Kraft-Wärme-Kopplungssystem mit einer Verbrennungskraftmaschine zur Ausführung des Verfahrens

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WO2014161661A1 true WO2014161661A1 (fr) 2014-10-09

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WO (1) WO2014161661A1 (fr)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104864415A (zh) * 2015-05-29 2015-08-26 陈文煜 一种适用于多种燃料的微型燃气轮机发电系统
DE102016201974A1 (de) 2016-02-10 2017-08-10 Dürr Systems Ag Verfahren zum Betreiben einer Wärmekraftmaschine und Wärmekraftmaschine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2322430A1 (de) * 1973-05-04 1974-11-21 Volkswagenwerk Ag Ortsbewegliche gasturbinenanlage
GB2014662A (en) * 1978-02-16 1979-08-30 English Electric Co Ltd Gas Turbine Plant Providing Shaft Power and Heat
JP2005030318A (ja) * 2003-07-07 2005-02-03 Ishikawajima Harima Heavy Ind Co Ltd ガスタービン
JP2006283655A (ja) * 2005-03-31 2006-10-19 Mitsui Eng & Shipbuild Co Ltd ガスタービンコージェネシステムの余剰蒸気量制御方式
ES2387724A1 (es) * 2010-03-05 2012-09-28 Universidad Nacional De Educación A Distancia Sistema de regeneración parcial en turbinas de gas de ciclos combinados con una o varias fuentes de calor.

Family Cites Families (2)

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Publication number Priority date Publication date Assignee Title
GB692072A (en) * 1950-06-01 1953-05-27 Oerlikon Maschf Method of regulating gas turbine plants
GB858397A (en) * 1958-06-04 1961-01-11 Bbc Brown Boveri & Cie Improvements in or relating to turbines

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2322430A1 (de) * 1973-05-04 1974-11-21 Volkswagenwerk Ag Ortsbewegliche gasturbinenanlage
GB2014662A (en) * 1978-02-16 1979-08-30 English Electric Co Ltd Gas Turbine Plant Providing Shaft Power and Heat
JP2005030318A (ja) * 2003-07-07 2005-02-03 Ishikawajima Harima Heavy Ind Co Ltd ガスタービン
JP2006283655A (ja) * 2005-03-31 2006-10-19 Mitsui Eng & Shipbuild Co Ltd ガスタービンコージェネシステムの余剰蒸気量制御方式
ES2387724A1 (es) * 2010-03-05 2012-09-28 Universidad Nacional De Educación A Distancia Sistema de regeneración parcial en turbinas de gas de ciclos combinados con una o varias fuentes de calor.

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