EP2655832A2 - Procédé permettant de faire fonctionner un système de petite turbine à gaz ainsi que système de petite turbine à gaz - Google Patents

Procédé permettant de faire fonctionner un système de petite turbine à gaz ainsi que système de petite turbine à gaz

Info

Publication number
EP2655832A2
EP2655832A2 EP11801588.2A EP11801588A EP2655832A2 EP 2655832 A2 EP2655832 A2 EP 2655832A2 EP 11801588 A EP11801588 A EP 11801588A EP 2655832 A2 EP2655832 A2 EP 2655832A2
Authority
EP
European Patent Office
Prior art keywords
turbine
compressor
stage
stages
generator
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Withdrawn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
EP11801588.2A
Other languages
German (de)
English (en)
Inventor
Franz Wimmer
Friedrich Benra
Hans-Josef Dohmen
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.)
Conpower Patente & Co KG GmbH
Original Assignee
Conpower Patente & Co KG 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 Conpower Patente & Co KG GmbH filed Critical Conpower Patente & Co KG GmbH
Publication of EP2655832A2 publication Critical patent/EP2655832A2/fr
Withdrawn legal-status Critical Current

Links

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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • 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
    • F01D15/12—Combinations with mechanical gearing
    • 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
    • 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
    • F01K25/10—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 the vapours being cold, e.g. ammonia, carbon dioxide, ether
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/34—Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
    • 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
    • F02C6/02—Plural gas-turbine plants having a common power output
    • 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
    • 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
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03341—Sequential combustion chambers or burners

Definitions

  • the invention relates to a method for operating a small-gas turbine arrangement, as well as a small-gas turbine arrangement itself
  • Micro or small gas turbines are becoming increasingly important in connection with the use of renewable energy sources or renewable raw materials. Meanwhile, techniques are known in which high process temperatures are achieved with the help of dust firing of dry biomass. With regard to the overall concept, small gas turbines are therefore important for the generation of electricity from renewable raw materials. It is also known that gas turbines currently achieve a maximum efficiency of less than 40% with the cycle processes carried out. The invention is therefore based on the object to further develop a method of the generic type to the effect that significantly higher efficiencies, and especially on the use of renewable raw materials especially
  • Core of the inventive method is that in a number of turbines, before each turbine or turbine stage a
  • Combustion chamber is arranged, and the gas outlet of each turbine or turbine stage is first introduced into the combustion chamber of the next turbine or turbine stage, and that the
  • a compressor arrangement with M stages in which the compressor stages (1 to M) (pressure medium-locking) are connected in series, and that between each two successive compressor stages, ie behind each compressor stage, a liquid evaporator medium is injected, such that also behind the last compressor is also a final injection.
  • the small gas turbine arrangement is configured with a plurality of compressor stages and a plurality of turbine stages, in the manner of a turbine circuit process.
  • desired mains frequency usually 50 or 60 Hz.
  • - Cooling by evaporation of evaporator medium for example water, but preferably not exclusively to the saturation point.
  • evaporator medium for example water
  • - Cooling energy is retained in or in the system, and represents also in this regard the cycle.
  • Evaporator media injection is the energy consumed by the cooling system (i.e., energy removal by reducing the cooling system
  • Air temperature is not discharged via the system boundary, but remains in the system (in the manner of a cycle).
  • the system is easy and effective to operate. Especially with the accruing
  • Evaporator medium and liquid fuel is used, and thus injected at those injection sites at which the evaporator medium is injected.
  • the liquid fuel initially serves as
  • Evaporating medium and fuel provide a number of advantages. Due to the multi-stage injection of the fuel, initially as the evaporator medium, there is a subsequent optimal air mixing of the fuel, and then ensures in the combustion chamber for optimal subsequent combustion. It is important in the case of the use of vaporizable liquid
  • ORC medium Organic Rankine Cycle
  • Anstellwinkels the vanes takes place in at least the first compressor stage.
  • the turbines and the compressors mechanically engage with a shaft coupled to a generator / motor arrangement, and that in a starting mode the generator is operated in the drive or motor mode and subsequently in the generator mode. So it requires only one relevant aggregate with the said
  • Short rotation crops A special exception here is the biomass IGNISCUM (CPVO 2007/0149). Although this is also a short rotation plant with at least one harvest per year, its lignin content is surprisingly high and above all, the ash melting point is well above 1,000 ° C.
  • the combustion is effective, without sooting etc, and protects the turbines by avoiding or significantly reducing deposits.
  • said biomass is so advantageous in connection with the method and the device according to the invention.
  • this biomass Igniscum has the advantage that it is both solid or dust-fine fuel, as biogas can be obtained.
  • the mixed fuel supply of simultaneously gas and dust from the same energy crop achieves extremely high levels
  • the gist of the invention is that with a number of N
  • Turbine stage is arranged a combustion chamber, and the
  • Gas output of each turbine or turbine stage is first introduced into the combustion chamber of the next turbine or turbine stage, and that the gas outlet of the last turbine or turbine stage in turn leads via a recuperation thermal energy back into the gas stream before entering the first combustion chamber of the first turbine stage.
  • the cooled outlet air from the last compressor stage ensures that recuperation becomes significantly more effective.
  • Multi-stage steam turbines with reheat are known, but small gas turbines with intermediate combustion are not common. Due to the combination of recooling and recuperation not yet used with small gas turbines and a multi-stage (at least
  • Cooling at the outlet behind each compressor stage A maximum of so much evaporator medium is introduced into the air stream that the saturation point of the air is in accordance with their
  • the evaporator medium for example water is finely injected so that it evaporates, in each case at a defined point in the process. This requires small droplets.
  • the small size of the droplets favors the ratio of drop surface to
  • Drop volume This means that the drop surface becomes large in relation to the drop volume.
  • Multi-stage compressors are known per se. With everyone
  • Compressor stage is fed to the air more energy, or the pressure of the compression process is increased.
  • the compression is kept almost isothermal and thus requires less compressor work.
  • multi-stage transmission compressors are generally known per se.
  • the invention provides an arrangement for small gas turbines in which the simultaneous
  • the injection of the evaporator medium is carried out by an injection opening arranged there, such that the evaporation already shortly before reaching the following
  • Compressor stage takes place, unless it is the injection port behind the last compressor stage, so that at the same time a drop erosion of the compressor is avoided.
  • the central shaft of the generator is provided or connected with a sun gear, and that the individual shafts of both the turbines, or
  • Turbine stages, as well as the compressor or compressor stages are provided with gear elements and the central
  • Generator assembly are arranged around, and so form a compact unit.
  • all transmission elements are arranged in an existing housing parts but ultimately in a contiguous in the assembled state housing.
  • the case may be jagged, but still connected. So also an effective heat management is possible. Mechanically, this one has
  • Figure 1 Schematic representation of the entire process.
  • Figure 2 embodiment of a compact arrangement
  • Compressor stage 1 outside air is sucked in, and before it goes into the second compressor stage 2, is between the first and second compressor stage, the first injection site 5, which may also be designed as a conduit extension, so one
  • Injection space forms. Between the compressor stage 2 and 3 is a further injection site 6, and between the third and the fourth compressor stage, the further injection site 7 is placed. Also at the output of the fourth and thus here last compressor stage 4, a further injection point 8 is placed. From there it goes then pressure-locked into the first combustion chamber 13, in which gaseous and / or liquid and / or
  • dusty solid fuel such as Igniscum powder is sprayed for combustion. From there it goes into the first turbine 10 and the first turbine stage 10. The output of the first turbine stage 10 then opens into the second combustion chamber
  • Solid fuel be sprayed.
  • a recuperator 12 is arranged between the output of the last compressor stage 4 after the cooling injection site 8, in which the at the second
  • the residual heat generated there is still remanufactured by a downstream ORC cycle.
  • this heat is passed through a heat exchanger 32, which transfers the residual heat of the primary process in a low-temperature working fluid. From there, it goes via a turbine 31 in the ORC process, which is coupled to a second generator.
  • the output of the turbine 31 is guided via a recuperation 33 in the ORC process and then fed to a capacitor 35, subsequently the ORC medium is guided in the ORC cycle process by means of pump 34.
  • All compressors and turbines arranged in the primary process are in mechanical operative engagement with each other. This can be realized by a common wave, or by a
  • Gear coupling An example of a transmission coupling is shown in FIG. Figure 2 shows a very significant
  • the compressors 1 to 4 are in this case arranged below, and the generator 20 is centrally placed around the axis (central shaft) not shown here centrally.
  • the compressor 1 has the adjusting means for the
  • the turbines 10 and 11 are placed above the generator 20, with the first turbine 10 in the front and the second turbine in the back. Between the individual compressor stages, the water or evaporator media injection sites are placed.
  • the invention thus described is a specific gas turbine cycle process that utilizes continuous water injection to recirculate the compression process, that uses the energy of the combustion gas to a very high degree in the context of recuperative heat transfer, and the multiple combustion to another

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un procédé permettant de faire fonctionner un système de petite turbine à gaz, ainsi qu'un système de petite turbine à gaz comportant au moins un compresseur/étage de compresseur et au moins une turbine ou un étage de turbine, le compresseur et les turbines/étages de turbine agissant sur un axe de générateur pour la production de courant. L'invention vise à obtenir une nette augmentation du rendement. A cet effet, pour un nombre N de turbines ou d'étages de turbine, une chambre de combustion est agencée avant chaque turbine ou étage de turbine et la sortie de gaz de chaque turbine ou de chaque étage de turbine est tout d'abord introduite dans la chambre de combustion de la turbine suivante ou de l'étage de turbine suivant, et l'évacuation de gaz de la dernière turbine ou du dernier étage de turbine retourne par récupération de l'énergie thermique dans le flux de gaz avant l'entrée dans la première chambre de combustion du premier étage de turbine.
EP11801588.2A 2010-12-14 2011-11-23 Procédé permettant de faire fonctionner un système de petite turbine à gaz ainsi que système de petite turbine à gaz Withdrawn EP2655832A2 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102010054501 2010-12-14
DE201110102599 DE102011102599A1 (de) 2010-12-14 2011-05-27 Verfahren zum Betrieb einer Kleingasturbinenanordnung, sowie Kleingasturbinenanordnung selbst
PCT/EP2011/005890 WO2012079694A2 (fr) 2010-12-14 2011-11-23 Procédé permettant de faire fonctionner un système de petite turbine à gaz ainsi que système de petite turbine à gaz

Publications (1)

Publication Number Publication Date
EP2655832A2 true EP2655832A2 (fr) 2013-10-30

Family

ID=46144873

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11801588.2A Withdrawn EP2655832A2 (fr) 2010-12-14 2011-11-23 Procédé permettant de faire fonctionner un système de petite turbine à gaz ainsi que système de petite turbine à gaz

Country Status (3)

Country Link
EP (1) EP2655832A2 (fr)
DE (1) DE102011102599A1 (fr)
WO (1) WO2012079694A2 (fr)

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* Cited by examiner, † Cited by third party
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US11359576B1 (en) 2021-04-02 2022-06-14 Ice Thermal Harvesting, Llc Systems and methods utilizing gas temperature as a power source
US11480074B1 (en) 2021-04-02 2022-10-25 Ice Thermal Harvesting, Llc Systems and methods utilizing gas temperature as a power source
US11592009B2 (en) 2021-04-02 2023-02-28 Ice Thermal Harvesting, Llc Systems and methods for generation of electrical power at a drilling rig
US11493029B2 (en) 2021-04-02 2022-11-08 Ice Thermal Harvesting, Llc Systems and methods for generation of electrical power at a drilling rig
US11644015B2 (en) 2021-04-02 2023-05-09 Ice Thermal Harvesting, Llc Systems and methods for generation of electrical power at a drilling rig
US12312981B2 (en) 2021-04-02 2025-05-27 Ice Thermal Harvesting, Llc Systems and methods utilizing gas temperature as a power source
US11293414B1 (en) 2021-04-02 2022-04-05 Ice Thermal Harvesting, Llc Systems and methods for generation of electrical power in an organic rankine cycle operation
US11486370B2 (en) 2021-04-02 2022-11-01 Ice Thermal Harvesting, Llc Modular mobile heat generation unit for generation of geothermal power in organic Rankine cycle operations
US11255315B1 (en) 2021-04-02 2022-02-22 Ice Thermal Harvesting, Llc Controller for controlling generation of geothermal power in an organic Rankine cycle operation during hydrocarbon production
US11421663B1 (en) 2021-04-02 2022-08-23 Ice Thermal Harvesting, Llc Systems and methods for generation of electrical power in an organic Rankine cycle operation
US12534990B2 (en) 2022-12-29 2026-01-27 Ice Thermal Harvesting, Llc Power generation assemblies for hydraulic fracturing systems and methods
US12180861B1 (en) 2022-12-30 2024-12-31 Ice Thermal Harvesting, Llc Systems and methods to utilize heat carriers in conversion of thermal energy

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0924406A1 (fr) * 1997-12-18 1999-06-23 Asea Brown Boveri AG Turbine à gaz avec un générateur de vapeur et un récupérateur disposés en parallèle dans les gaz d'échappement
GB2398606A (en) * 2003-02-21 2004-08-25 Alstom Technology Ltd Method and system for operating a partially closed cycle turbocharged gas turbine engine

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1239888B (de) * 1961-12-15 1967-05-03 Prvni Brnenska Strojirna Gasdampfturbinenanlage
US5806298A (en) * 1996-09-20 1998-09-15 Air Products And Chemicals, Inc. Gas turbine operation with liquid fuel vaporization
GB2348695A (en) * 1999-04-06 2000-10-11 James Engineering Gas turbines
DE102005049962A1 (de) * 2005-10-19 2007-04-26 Rheinmetall Landsysteme Gmbh Elektrischer Energieerzeuger

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0924406A1 (fr) * 1997-12-18 1999-06-23 Asea Brown Boveri AG Turbine à gaz avec un générateur de vapeur et un récupérateur disposés en parallèle dans les gaz d'échappement
GB2398606A (en) * 2003-02-21 2004-08-25 Alstom Technology Ltd Method and system for operating a partially closed cycle turbocharged gas turbine engine

Also Published As

Publication number Publication date
WO2012079694A8 (fr) 2013-07-11
DE102011102599A1 (de) 2012-06-14
WO2012079694A2 (fr) 2012-06-21
WO2012079694A3 (fr) 2013-11-07

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