WO2017144761A1 - Turbine à gaz, et procédé de fonctionnement associé, à deux étages de compression et refroidissement intermédiaire par machine frigorifique - Google Patents

Turbine à gaz, et procédé de fonctionnement associé, à deux étages de compression et refroidissement intermédiaire par machine frigorifique Download PDF

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Publication number
WO2017144761A1
WO2017144761A1 PCT/ES2017/070102 ES2017070102W WO2017144761A1 WO 2017144761 A1 WO2017144761 A1 WO 2017144761A1 ES 2017070102 W ES2017070102 W ES 2017070102W WO 2017144761 A1 WO2017144761 A1 WO 2017144761A1
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WIPO (PCT)
Prior art keywords
gas turbine
compressor
axial
fluid
turbine according
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Ceased
Application number
PCT/ES2017/070102
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English (en)
Spanish (es)
Inventor
Alejandro DESCO SANCHEZ
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Individual
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Individual
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Publication of WO2017144761A1 publication Critical patent/WO2017144761A1/fr
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Classifications

    • 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
    • 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
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
    • F02C7/143—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages
    • 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
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
    • F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
    • F25B11/00—Compression machines, plants or systems, using turbines, e.g. gas turbines

Definitions

  • the present invention relates to a gas turbine, and associated method of operation, which follows the Brayton thermodynamic cycle. It makes use of a two-stage compression, the working fluid being cooled to temperatures even lower than those of the first compressor's own admission, in the transition between the first and the second stage. This is achieved through the use of a refrigerating machine, driven by the axis of the turbine itself, responsible for absorbing part of the heat generated in the first stage of compression, achieving significantly higher yields than those obtained without this method, and even greater than those obtained by using the already known air-air air-liquid exchangers or other systems that will be mentioned later.
  • compressors are unable to perform reversible adiabatic processes, since they perform their work in a finite time, prevents them from acting as isentropic systems, so that as the working fluid is compressed, it gains temperature in a way greater than it would if the process were reversible.
  • This thermal gain is what motivates the need to divide the compression of the working fluid of the turbines in several stages, in order to lower its temperature between them, managing to need less work to achieve the desired final pressure than if it were used A single compression without refrigeration.
  • the present invention is framed in the sector of the technique belonging to the aerospace industry and energy production, that is, the two sectors where gas turbines are mostly used.
  • fog systems which are based on the same principle as evaporative coolers, with the exception that they make use of water sprayers that spray it on the working fluid.
  • wet compression systems by mechanical cooling base their operating principle on the injection of atomized water directly to the turbine's working fluid flow, achieving temperatures as low as desired, with the proviso that energy consumption usually makes this economically unfeasible system, as well as your space needs.
  • the gas turbine is of the type that consists of a compression system divided into several stages, theoretically adiabatic compression (according to the Bravton cycle) being applied to the working fluid, atmospheric air in this case.
  • the evaporator of the refrigerating machine makes use of the evaporator of the refrigerating machine as an exchanger built in a material with a high index of thermal conductivity (between the working fluid of the turbine and the cooling fluid) and insulated as much as possible from the outside, in order to avoid The surrounding heat absorption, we can cool the air to the desired temperature.
  • FIG. 1 schematically shows the operation of the system.
  • the interaction between the refrigerating machine and the gas turbine can be observed, the latter being the one that produces the work necessary to operate the refrigerating machine and the first one that absorbs part of the heat generated in the compression process of the working fluid of the turbine in its first compression stage.
  • FIG. 2 and FIG. 3 show respectively the thermodynamic cycle followed by the refrigerating machine and the turbine. Both cycles are represented by two Pressure-Volume diagrams. It should be noted that they have been represented as two reversible cycles, so the actual operation of both machines will differ substantially from what is embodied here. However, given the impossibility of representing irreversible cycles, it has been decided to include these two modeling, with a purely explanatory spirit.
  • the cycles have been represented by points, named from (a) to (k), which correspond to the thermodynamic state of the working fluid of each of the machines at the different points thereof. This designation can also be observed in FIG. 1, referring to the state in which the working fluid is located according to the position it occupies with respect to the system.
  • the turbine consists of a first compressor (1), a secondary compressor (2), a heat exchanger, which acts as an evaporator of the refrigerating machine (12), with indirect surface contact and cross flow (the compressed fluid in the first compressor (1) of the gas turbine gives heat to the refrigerating fluid of the refrigerating machine when it is in phase change, from liquid to gaseous), a combustion chamber ( 5) where the temperature of the working fluid of the turbine rises and with it its enthalpy and finally the turbine (3), the working fluid flowing between the different parts that constitute the system through its own ducts (4) and rotating the entire compressor (1 and 2) and turbine (3) jointly and severally thanks to an axle (13).
  • the refrigerating machine consists of a compressor (7), which raises the pressure of the working fluid, in this case cooling fluid, when it is completely in the gas phase, running it through lines or pipes (8).
  • the compressor (7) is mechanically driven by the turbine, transforming the speed of rotation of its axis (13) into a more suitable for the operation of the refrigerating machine by using a gearbox (6).
  • the refrigerant fluid travels from the compressor (7) to the condenser (9), being there where it gives heat to the outside, with the consequent change of gas phase to liquid.
  • the liquefied gas is collected in a tank (10), then traveling along the mentioned lines (8) to an expansion valve (11), where its pressure decreases sharply, leading to the phase change that will occur later in the evaporator (12 ).
  • This takes the heat necessary to change the refrigerant fluid to the gas phase of the compressed working fluid in the first stage of compression of the turbine (1).
  • the cycle begins in (a) where the fluid accesses the system, as can also be seen in FIG. 1 (there may or may not be diffusers at the turbine inlet, which slow down the air flow by increasing its pressure, depending on the application thereof) and undergoes a first transformation, it is adiabatically compressed by the first compressor (1) until it reaches (b). In the section between (b) and (c) the working fluid is cooled isobarically yielding a heat Q 2 ' in the heat exchanger (12).
  • the fluid gives a heat ⁇ V in the condenser, in an isothermal manner, also returning to a liquid state, which in turn is collected in a tank (10).
  • the fluid undergoes an abrupt decrease in its pressure, which is reflected in the interval between (k) and (g) as an adiabatic expansion.
  • the refrigerant fluid passes through the evaporator of the refrigerating machine (12) where, acting as an exchanger in the gas turbine, it collects the heat transferred by the turbine's working fluid, and completely changes from liquid to gaseous phase, which It is reflected in the diagram as an isothermal expansion between (g) and (h).
  • the present invention would have a wide range of application, both in the aerospace and energy production industries, being able, in the latter case, to complement the combined cycle or cogeneration plants in their search for the highest possible efficiency .
  • the aerospace industry would have great application when creating more efficient engines, with lower consumption and emissions of harmful gases directly into the atmosphere. It would in turn increase the service autonomy of the aforementioned aircraft, lowering the cost of transporting goods or passengers.

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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)
  • Thermal Sciences (AREA)
  • Separation By Low-Temperature Treatments (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

La présente invention concerne une turbine à gaz, et un procédé de fonctionnement associé, à deux étages de compression. Un échangeur de chaleur est intercalé entre ces deux étages, lequel est constitué par l'évaporateur d'une machine frigorifique actionnée mécaniquement par ladite turbine, préalablement à l'utilisation d'un réducteur de vitesse, dans le but de faire baisser la température du fluide de travail de la turbine dans sa transition vers le deuxième étage de compression, ce qui permet de cette façon d'atteindre la pression de fluide désirée, à la sortie du deuxième compresseur, celui-ci effectuant un travail moins intense que celui qui aurait dû être exécuté pour amener ledit fluide de travail à cette même pression dans un seul étage nécessaire de refroidissement. Ceci permet d'obtenir une meilleure efficacité de ladite turbine à gaz. La figure la plus représentative de la présente invention est la FIG.1, qui illustre de manière schématique les éléments utilisés dans celle-ci.
PCT/ES2017/070102 2016-02-26 2017-02-23 Turbine à gaz, et procédé de fonctionnement associé, à deux étages de compression et refroidissement intermédiaire par machine frigorifique Ceased WO2017144761A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ES201600171A ES2634028B1 (es) 2016-02-26 2016-02-26 Turbina de gas con dos etapas de compresión y enfriamiento intermedio mediante máquina frigorífica
ESP201600171 2016-02-26

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WO2017144761A1 true WO2017144761A1 (fr) 2017-08-31

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PCT/ES2017/070102 Ceased WO2017144761A1 (fr) 2016-02-26 2017-02-23 Turbine à gaz, et procédé de fonctionnement associé, à deux étages de compression et refroidissement intermédiaire par machine frigorifique

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ES (1) ES2634028B1 (fr)
WO (1) WO2017144761A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2719708A1 (es) * 2018-01-12 2019-07-12 Robert Art En Pedra S L Turbina de gas con al menos una etapa de compresión y expansión y método asociado de enfriamiento o calentamiento intermedio mediante máquina frigorífica

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10231827A1 (de) * 2001-07-26 2003-04-24 Alstom Switzerland Ltd Gasturbine mit integralem Ansaug-Booster-System und Verfahren zum Betrieb
EP1873375A2 (fr) * 2006-06-26 2008-01-02 Hitachi, Ltd. Système de refroidissement d'un compresseur d'une turbine à gaz
WO2009073838A1 (fr) * 2007-12-07 2009-06-11 Dresser-Rand Company Système et procédé de compression pour un système de liquéfaction de gaz
US20100058801A1 (en) * 2008-09-09 2010-03-11 Conocophillips Company System for enhanced gas turbine performance in a liquefied natural gas facility
CN203822467U (zh) * 2014-05-15 2014-09-10 中国船舶重工集团公司第七�三研究所 利用低压压气机余热发电的间冷循环燃气轮机

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10231827A1 (de) * 2001-07-26 2003-04-24 Alstom Switzerland Ltd Gasturbine mit integralem Ansaug-Booster-System und Verfahren zum Betrieb
EP1873375A2 (fr) * 2006-06-26 2008-01-02 Hitachi, Ltd. Système de refroidissement d'un compresseur d'une turbine à gaz
WO2009073838A1 (fr) * 2007-12-07 2009-06-11 Dresser-Rand Company Système et procédé de compression pour un système de liquéfaction de gaz
US20100058801A1 (en) * 2008-09-09 2010-03-11 Conocophillips Company System for enhanced gas turbine performance in a liquefied natural gas facility
CN203822467U (zh) * 2014-05-15 2014-09-10 中国船舶重工集团公司第七�三研究所 利用低压压气机余热发电的间冷循环燃气轮机

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2719708A1 (es) * 2018-01-12 2019-07-12 Robert Art En Pedra S L Turbina de gas con al menos una etapa de compresión y expansión y método asociado de enfriamiento o calentamiento intermedio mediante máquina frigorífica

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ES2634028A1 (es) 2017-09-26
ES2634028B1 (es) 2018-10-15

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