EP1784557B1 - Fluid injection in a gas turbine during a cooling down period - Google Patents

Fluid injection in a gas turbine during a cooling down period Download PDF

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Publication number
EP1784557B1
EP1784557B1 EP05777877A EP05777877A EP1784557B1 EP 1784557 B1 EP1784557 B1 EP 1784557B1 EP 05777877 A EP05777877 A EP 05777877A EP 05777877 A EP05777877 A EP 05777877A EP 1784557 B1 EP1784557 B1 EP 1784557B1
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EP
European Patent Office
Prior art keywords
gas turbine
compressor
liquid
turbine
rotor
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.)
Not-in-force
Application number
EP05777877A
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German (de)
French (fr)
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EP1784557A1 (en
Inventor
Hajrudin Ceric
Giuseppe Gaio
Frank GÜNTHER
Gabriel Jungnickel-Marques
Stefan Wanz
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Siemens AG
Original Assignee
Huelfenhaus Armin
Huelsemann Gerhard
Siemens AG
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Application filed by Huelfenhaus Armin, Huelsemann Gerhard, Siemens AG filed Critical Huelfenhaus Armin
Priority to ES05777877T priority Critical patent/ES2304709T3/en
Priority to EP05777877A priority patent/EP1784557B1/en
Publication of EP1784557A1 publication Critical patent/EP1784557A1/en
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Publication of EP1784557B1 publication Critical patent/EP1784557B1/en
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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/002—Cleaning of turbomachines
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/34—Turning or inching gear
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/70—Suction grids; Strainers; Dust separation; Cleaning
    • F04D29/701—Suction grids; Strainers; Dust separation; Cleaning especially adapted for elastic fluid pumps
    • F04D29/705—Adding liquids
    • 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
    • F05D2260/212—Heat transfer, e.g. cooling by water injection

Definitions

  • the invention relates to a method for cooling a gas turbine with a compressor, a turbine unit and with a rotor, which is carried out after the operation of the gas turbine and in which the rotor is at least temporarily driven during a cooling phase at a reduced rated speed.
  • the object of the invention is to provide a method for cooling a gas turbine with a rotor, which causes even faster cooling of the gas turbine to further reduce the service life of the gas turbine.
  • the solution provides that for faster cooling at least temporarily during the cooling phase, a liquid is introduced before the compressor in the air stream, which flows through the flow channel of the compressor and the turbine unit of the gas turbine.
  • the invention is based on the idea that by introducing a liquid into the air stream, the liquid stream enriched with liquid can take up and remove a larger amount of heat per unit of time from the still heated gas turbine. This leads to faster cooling of the gas turbine than in the previously known from the prior art method.
  • the gas turbine can be cooled faster along its entire longitudinal extent along the rotor. Consequently, the compressor, the combustion chamber and the turbine unit are flowed through by the cooled air flow during the implementation of the method.
  • the air flow is cooled only after flowing through the compressor.
  • the faster cooling of the gas turbine allows inspections, inspections and maintenance to be carried out earlier by the installation staff. This reduces the service life of the gas turbine and increases its availability.
  • the embodiment of the method in which the rotational speed of the rotor during the liquid introduction is higher than the rotational speed at which no liquid introduction takes place. Due to the higher speed, more air is pumped through the gas turbine. Thus, the airflow can absorb more liquid without water retention causing cracks or crack growth on the components of the gas turbine.
  • the introduction of the liquid takes place by means of a compressor washing device.
  • Design changes to the gas turbine are not necessary for carrying out the method, so that the retrofitting of existing gas turbines for performing such a method is particularly inexpensive and easy.
  • the compressor washing device can also be used a Eindüsvoriques for a liquid which is provided at the compressor inlet and which injects a liquid in the sucked ambient air during operation of the gas turbine to increase the mass flow.
  • This method which is carried out during operation of the gas turbine, is known by the term "wet compression” or else "wet compression”.
  • FIG. 1 a gas turbine 1 with a rotatably mounted about a rotational axis 3 rotor fifth
  • the gas turbine 1 has an intake chamber 7, a compressor 9, a toroidal annular combustion chamber 11 and a turbine unit 13.
  • Both in the compressor 9 and in the turbine unit 13 guide vanes 15 and blades 17 are each arranged in rings.
  • a blade ring 19 is followed by a blade ring 21.
  • the rotor blades 17 are fastened to the rotor 5 by means of rotor disks 23, whereas the stator blades 15 are fixedly mounted on the housing 25.
  • Wreaths 21 of guide vanes 15 are likewise arranged in the turbine unit 13, which, viewed in the direction of the flow medium, is followed by a ring of rotor blades 17.
  • the respective blade profiles of the guide vanes 15 and of the rotor blades 17 extend in a radial manner in an annular flow channel 27 extending through the compressor 9 and the turbine unit 13.
  • air 29 is sucked through the intake manifold 7 and compressed by the compressor.
  • the compressed air is guided to the burners 33, which are provided on a ring lying on the annular combustion chamber 11.
  • the compressed air 29 is mixed with a fuel 35, which mixture in the annular combustion chamber 11 is burned to a hot gas 37.
  • the hot gas 37 flows through the flow channel 27 of the turbine unit 13 past guide vanes 15 and blades 17.
  • the hot gas 37 relaxes on the blades 17 of the turbine unit 13 to perform work.
  • the rotor 5 of the gas turbine 1 in a rotational movement with its rated speed, for example, 3000 min -1 or 3600 min -1 , which serves to drive the compressor 9 and to drive a working engine or generator, not shown.
  • FIG. 2 shows a cross section through the intake 7 of the gas turbine 1.
  • the air inlet-side end 39 of the compressor 9 with the centrally mounted rotor 5 is shown in cross section.
  • only a few of the guide vanes 15 arranged in the flow channel 27 are shown.
  • a device 41 for introducing, in particular injection of a liquid 43, for example distilled water, is arranged.
  • the device 41 can be, for example, a compressor washing device 45 or a injection circuit for wet compression.
  • the method for cooling the gas turbine 1 is performed.
  • the rotor 5 is driven by a rotating device, not shown, at a reduced speed, for example in the range of 80 min -1 to 160 min -1 , preferably at 120 min -1 , to cool it.
  • the rotor 5 pumps in relation to the operation
  • the gas turbine 1 thus sucks in a comparatively small air mass flow and pumps it through the section of the flow channel 27 arranged in the compressor, through the combustion chamber and through the turbine unit 13 arranged portion of the flow channel 27th
  • the cooling process is further accelerated by additionally called distilled water in front of the compressor 9 in the intake air flow during the rotary operation, also called cooling operation.
  • the evaporation of the water cools the sucked-in air flow, as a result of which, as it flows through the gas turbine 1, it increasingly absorbs and removes the heat stored in the gas turbine 1.
  • the rotational speed of the rotor 5 can be increased, for example to 4% to 10% of the nominal rotational speed.
  • the introduction of the liquid 43 can take place by suitable means both in the annular combustion chamber 11 and in the flow channel 27 of the turbine unit 13.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Separation By Low-Temperature Treatments (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Superconductors And Manufacturing Methods Therefor (AREA)
  • Nonmetallic Welding Materials (AREA)
  • Ceramic Products (AREA)

Abstract

The method involves driving a rotor intermittently, during a cooling phase at a reduced nominal rotation speed. A liquid e.g. distilled water, is brought into an air stream, which is flowed through a circular flow channel of a gas turbine, where the turbine exhibits a compressor, turbine unit and an annular combustion chamber. Blade profiles of guide vanes and rotor blades extend radially in the circular flow channel.

Description

Die Erfindung betrifft ein Verfahren zum Abkühlen einer Gasturbine mit einem Verdichter, einer Turbineneinheit und mit einem Rotor, welches im Anschluss an den Betrieb der Gasturbine durchgeführt wird und bei welchem der Rotor zumindest zeitweise während einer Abkühlphase mit verminderter Nenndrehzahl angetrieben wird.The invention relates to a method for cooling a gas turbine with a compressor, a turbine unit and with a rotor, which is carried out after the operation of the gas turbine and in which the rotor is at least temporarily driven during a cooling phase at a reduced rated speed.

Es ist bekannt, dass im Anschluss an den Betrieb einer Gasturbine der Rotor mit geringer Drehzahl angetrieben wird, um die durch den Betrieb aufgeheizte Gasturbine schneller abzukühlen. Durch die Rotation des Rotors und der an ihm angeordneten Laufschaufeln wird durch den Strömungskanal des Verdichters, die Brennkammer und die Turbineneinheit kühle Umgebungsluft gepumpt. Diese nimmt beim Durchströmen die in der Gasturbine, d.h. im Gehäuse und im Rotor, gespeicherte Wärme auf und transportiert sie ab. Hierdurch kühlt die Gasturbine schneller ab, so dass Service- bzw. Wartungsarbeiten frühzeitig angefangen werden können, denn es ist ein allgemeines Bestreben, die Stillstandszeiten einer Gasturbine zu verringern.It is known that, following operation of a gas turbine, the rotor is driven at low speed to more rapidly cool the gas turbine heated by operation. Due to the rotation of the rotor and the blades arranged on it, cool ambient air is pumped through the flow channel of the compressor, the combustion chamber and the turbine unit. This decreases as it flows through the gas turbine, i. in the housing and in the rotor, stored heat and transported away. As a result, the gas turbine cools faster, so that service or maintenance can be started early, because it is a general effort to reduce the downtime of a gas turbine.

Außerdem offenbart die US 2003/35714 A1 ein Verfahren zur Kühlung einer Turbineneinheit im Anschluss an den Betrieb der Turbine gemäß dem Oberbegriff des Anspruchs 1. Dabei wird Kühlluft über das beim Betrieb genutzte Kühlsystem unmittelbar in den Turbineneinströmbereich eingeblasen, um Hitzestauungen und ein Überhitzen der Turbine nach dem Abschalten der Turbine zu vermeiden. Ein dazu ähnliches Verfahren ist ferner aus der US 3,903,691 bekannt.In addition, the disclosed US 2003/35714 A1 a method for cooling a turbine unit following the operation of the turbine according to the preamble of claim 1. In this case, cooling air is injected via the cooling system used during operation directly into the turbine inlet to avoid heat build-up and overheating of the turbine after switching off the turbine. A similar method is further from the US 3,903,691 known.

Zudem ist aus der US 4,338,780 und aus der US 2004/88998 A1 ein Kühlsystem für eine Gasturbine bekannt, bei der in den bereits vom Verdichter zur Kühlung bereitgestellten, verdichteten Luftstrom zur Kühlluftkühlung Wasser eingedüst wird.Moreover, from the US 4,338,780 and from the US 2004/88998 A1 a cooling system for a gas turbine, in which in the already provided by the compressor for cooling, compressed air stream for cooling air cooling water is injected.

Aufgabe der Erfindung ist es, ein Verfahren zum Abkühlen einer Gasturbine mit einem Rotor anzugeben, welches ein noch schnelleres Abkühlen der Gasturbine bewirkt, um die Standzeiten der Gasturbine weiter zu verringern.The object of the invention is to provide a method for cooling a gas turbine with a rotor, which causes even faster cooling of the gas turbine to further reduce the service life of the gas turbine.

Die Aufgabe wird durch die Merkmale des Anspruchs 1 gelöst.The object is solved by the features of claim 1.

Die Lösung sieht vor, dass zur schnelleren Abkühlung zumindest zeitweise während der Abkühlphase eine Flüssigkeit vor dem Verdichter in den Luftstrom eingebracht wird, welcher den Strömungskanal des Verdichters und der Turbineneinheit der Gasturbine durchströmt.The solution provides that for faster cooling at least temporarily during the cooling phase, a liquid is introduced before the compressor in the air stream, which flows through the flow channel of the compressor and the turbine unit of the gas turbine.

Die Erfindung geht von der Idee aus, dass durch das Einbringen einer Flüssigkeit in den Luftstrom der mit Flüssigkeit angereicherte Luftstrom eine größere Wärmemenge pro Zeiteinheit aus der noch aufgeheizten Gasturbine aufnehmen und abtransportieren kann. Dies führt zum schnelleren Abkühlen der Gasturbine als bei den bisher aus dem Stand der Technik bekannten Verfahren. Dabei wird auch schon der durch den Betrieb aufgeheizte Verdichter und anschließend die Turbineneinheit gekühlt, indem der angesaugte Luftstrom bereits am eintrittsseitigen Ende des Verdichters mit der im Inneren verdampfenden Flüssigkeit angereichert wird. Hierdurch kann die Gasturbine entlang ihrer vollständigen Längserstreckung entlang des Rotors schneller abgekühlt werden. Folglich werden der Verdichter, die Brennkammer und die Turbineneinheit vom gekühlten Luftstrom während der Durchführung des Verfahrens durchströmt. Beim zitierten Stand der Technik wird der Luftstrom erst nach dem Durchströmen des Verdichters gekühlt.The invention is based on the idea that by introducing a liquid into the air stream, the liquid stream enriched with liquid can take up and remove a larger amount of heat per unit of time from the still heated gas turbine. This leads to faster cooling of the gas turbine than in the previously known from the prior art method. In this case, even the heated by the operation of the compressor and then the turbine unit is cooled by the sucked air flow is enriched already at the inlet end of the compressor with the liquid evaporating inside. As a result, the gas turbine can be cooled faster along its entire longitudinal extent along the rotor. Consequently, the compressor, the combustion chamber and the turbine unit are flowed through by the cooled air flow during the implementation of the method. In the cited prior art, the air flow is cooled only after flowing through the compressor.

Durch das schnellere Abkühlen der Gasturbine können Revisionen, Inspektionen und Wartungsarbeiten vom Montagepersonal frühzeitiger durchgeführt werden. Dies verringert die Standzeiten der Gasturbine und erhöht ihre Verfügbarkeit.The faster cooling of the gas turbine allows inspections, inspections and maintenance to be carried out earlier by the installation staff. This reduces the service life of the gas turbine and increases its availability.

Vorteilhafte Ausgestaltungen sind in den Unteransprüchen angegeben.Advantageous embodiments are specified in the subclaims.

Besonders vorteilhaft ist die Ausgestaltung des Verfahrens, bei der die Drehzahl des Rotors während der Flüssigkeitseinbringung höher ist als die Drehzahl, bei der keine Flüssigkeitseinbringung erfolgt. Durch die höhere Drehzahl wird mehr Luft durch die Gasturbine gepumpt. Somit kann der Luftstrom mehr Flüssigkeit aufnehmen, ohne dass Wasseransammlungen Risse bzw. Risswachstum an den Komponenten der Gasturbine hervorrufen.Particularly advantageous is the embodiment of the method in which the rotational speed of the rotor during the liquid introduction is higher than the rotational speed at which no liquid introduction takes place. Due to the higher speed, more air is pumped through the gas turbine. Thus, the airflow can absorb more liquid without water retention causing cracks or crack growth on the components of the gas turbine.

Vorteilhafter Weise erfolgt die Einbringung der Flüssigkeit mittels einer Verdichterwascheinrichtung. Konstruktive Änderungen an der Gasturbine sind zur Durchführung des Verfahrens nicht nötig, so dass die Nachrüstung von bereits existierenden Gasturbinen zur Durchführung eines solchen Verfahrens besonders kostengünstig und einfach möglich ist. Anstelle der Verdichterwascheinrichtung kann auch eine Eindüsvorrichtung für eine Flüssigkeit verwendet werden, welche am Verdichtereintritt vorgesehen ist und welche beim Betrieb der Gasturbine zur Erhöhung des Massenstromes eine Flüssigkeit in die angesaugte Umgebungsluft eindüst. Dieses, beim Betrieb der Gasturbine durchgeführte Verfahren, ist unter dem Begriff "Wet Compression" oder auch "nasse Verdichtung" bekannt.Advantageously, the introduction of the liquid takes place by means of a compressor washing device. Design changes to the gas turbine are not necessary for carrying out the method, so that the retrofitting of existing gas turbines for performing such a method is particularly inexpensive and easy. Instead of the compressor washing device can also be used a Eindüsvorrichtung for a liquid which is provided at the compressor inlet and which injects a liquid in the sucked ambient air during operation of the gas turbine to increase the mass flow. This method, which is carried out during operation of the gas turbine, is known by the term "wet compression" or else "wet compression".

In einer weiteren vorteilhaften Ausgestaltung der Erfindung ist es denkbar, dass eine zusätzliche Einbringung von Flüssigkeit in eine Brennkammer der Gasturbine oder in den Strömungskanal einer Turbineneinheit erfolgt. Hierdurch ist es möglich, die beim Betrieb der Gasturbine besonders thermisch belasteten Bereiche nach dem Abschalten der Gasturbine gesondert durch die entstehende Verdunstungskälte zu kühlen.In a further advantageous embodiment of the invention, it is conceivable that an additional introduction of liquid takes place in a combustion chamber of the gas turbine or in the flow channel of a turbine unit. This makes it possible to separately cool the regions which are particularly thermally stressed during operation of the gas turbine after the gas turbine has been switched off by the resulting evaporation cold.

Besonders vorteilhaft ist es, wenn als Flüssigkeit destilliertes Wasser eingebracht wird. Hierdurch können Ablagerungen im Strömungskanal der Gasturbine vermieden werden.It is particularly advantageous if distilled water is introduced as the liquid. As a result, deposits in the flow channel of the gas turbine can be avoided.

Die Erfindung wird anhand einer Zeichnung erläutert.The invention will be explained with reference to a drawing.

Es zeigt:

FIG 1
einen Längsteilschnitt durch eine Gasturbine und
FIG 2
eine Verdichterwascheinrichtung in einem Ansaughaus einer Gasturbine.
It shows:
FIG. 1
a longitudinal section through a gas turbine and
FIG. 2
a compressor washing device in an intake of a gas turbine.

Verdichter und Gasturbinen sowie deren Arbeitsweisen sind allgemein bekannt. Hierzu zeigt FIG 1 eine Gasturbine 1 mit einem um eine Rotationsachse 3 drehbar gelagerten Rotor 5.Compressors and gas turbines and their operations are well known. This shows FIG. 1 a gas turbine 1 with a rotatably mounted about a rotational axis 3 rotor fifth

Entlang der Rotationsachse 3 weist die Gasturbine 1 ein Ansaughaus 7, einen Verdichter 9, eine torusartige Ringbrennkammer 11 und eine Turbineneinheit 13 auf.Along the rotation axis 3, the gas turbine 1 has an intake chamber 7, a compressor 9, a toroidal annular combustion chamber 11 and a turbine unit 13.

Sowohl im Verdichter 9 als auch in der Turbineneinheit 13 sind Leitschaufeln 15 und Laufschaufeln 17 jeweils in Kränzen angeordnet. Im Verdichter 9 folgt einem Laufschaufelkranz 19 ein Leitschaufelkranz 21. Die Laufschaufeln 17 sind am Rotor 5 mittels Rotorscheiben 23 befestigt, wohingegen die Leitschaufeln 15 feststehend am Gehäuse 25 montiert sind.Both in the compressor 9 and in the turbine unit 13 guide vanes 15 and blades 17 are each arranged in rings. In the compressor 9, a blade ring 19 is followed by a blade ring 21. The rotor blades 17 are fastened to the rotor 5 by means of rotor disks 23, whereas the stator blades 15 are fixedly mounted on the housing 25.

Ebenso sind in der Turbineneinheit 13 Kränze 21 aus Leitschaufeln 15 angeordnet, denen jeweils in Richtung des Strömungsmediums gesehen ein Kranz aus Laufschaufeln 17 folgt.Wreaths 21 of guide vanes 15 are likewise arranged in the turbine unit 13, which, viewed in the direction of the flow medium, is followed by a ring of rotor blades 17.

Die jeweiligen Schaufelprofile der Leitschaufeln 15 und der Laufschaufeln 17 erstrecken sich strahlenförmig in einem, sich durch Verdichter 9 und die Turbineneinheit 13 erstreckenden, ringförmigen Strömungskanal 27.The respective blade profiles of the guide vanes 15 and of the rotor blades 17 extend in a radial manner in an annular flow channel 27 extending through the compressor 9 and the turbine unit 13.

Beim Betrieb der Gasturbine 1 wird vom Verdichter 9 Luft 29 durch das Ansaughaus 7 angesaugt und verdichtet. Am Austritt 31 des Verdichters 9 wird die verdichtete Luft zu den Brennern 33 geführt, welche auf einem Ring liegend an der Ringbrennkammer 11 vorgesehen sind. In den Brennern wird die verdichtete Luft 29 mit einem Brennmittel 35 vermischt, welches Gemisch in der Ringbrennkammer 11 zu einem Heißgas 37 verbrannt wird. Anschließend strömt das Heißgas 37 durch den Strömungskanal 27 der Turbineneinheit 13 an Leitschaufeln 15 und Laufschaufeln 17 vorbei. Dabei entspannt sich das Heißgas 37 an den Laufschaufeln 17 der Turbineneinheit 13 arbeitsleistend. Hierdurch wird der Rotor 5 der Gasturbine 1 in eine Drehbewegung mit seiner Nenndrehzahl, beispielsweise 3000 min-1 oder 3600 min-1, versetzt, welche zum Antrieb des Verdichters 9 und zum Antrieb einer nicht dargestellten Arbeits-Kraftmaschine oder Generators dient.During operation of the gas turbine 1 9 air 29 is sucked through the intake manifold 7 and compressed by the compressor. At the outlet 31 of the compressor 9, the compressed air is guided to the burners 33, which are provided on a ring lying on the annular combustion chamber 11. In the burners, the compressed air 29 is mixed with a fuel 35, which mixture in the annular combustion chamber 11 is burned to a hot gas 37. Subsequently, the hot gas 37 flows through the flow channel 27 of the turbine unit 13 past guide vanes 15 and blades 17. In this case, the hot gas 37 relaxes on the blades 17 of the turbine unit 13 to perform work. As a result, the rotor 5 of the gas turbine 1 in a rotational movement with its rated speed, for example, 3000 min -1 or 3600 min -1 , which serves to drive the compressor 9 and to drive a working engine or generator, not shown.

FIG 2 zeigt einen Querschnitt durch das Ansaughaus 7 der Gasturbine 1. Das für die Luft eintrittsseitige Ende 39 des Verdichters 9 mit dem zentral gelagerten Rotor 5 ist im Querschnitt dargestellt. Der Klarheit halber sind nur einige der im Strömungskanal 27 angeordneten Leitschaufeln 15 gezeigt. FIG. 2 shows a cross section through the intake 7 of the gas turbine 1. The air inlet-side end 39 of the compressor 9 with the centrally mounted rotor 5 is shown in cross section. For the sake of clarity, only a few of the guide vanes 15 arranged in the flow channel 27 are shown.

Oberhalb des Verdichtereintritts ist eine Vorrichtung 41 zur Einbringung, insbesondere Eindüsung einer Flüssigkeit 43, beispielsweise destilliertes Wasser, angeordnet. Die Vorrichtung 41 kann beispielsweise eine Verdichterwascheinrichtung 45 oder ein Eindüsrack für "Wet Compression" sein.Above the compressor inlet, a device 41 for introducing, in particular injection of a liquid 43, for example distilled water, is arranged. The device 41 can be, for example, a compressor washing device 45 or a injection circuit for wet compression.

Nach dem Betrieb der Gasturbine 1 wird das Verfahren zum Abkühlen der Gasturbine 1 durchgeführt. Dabei wird der Rotor 5 von einer nicht gezeigten Dreheinrichtung mit verminderter Drehzahl, beispielsweise im Bereich von 80 min-1 bis 160 min-1, vorzugsweise mit 120 min-1, angetrieben, um diese abzukühlen. Dabei pumpt der Rotor 5 bezogen auf den Betrieb der Gasturbine 1 eine vergleichsweise geringe Masse von Luft durch den Strömungskanal 27 der Gasturbine 1. Der Verdichter 9 saugt also einen vergleichsweise geringen Luftmassenstrom an und pumpt diesen durch den im Verdichter angeordneten Abschnitt des Strömungskanals 27, durch die Brennkammer und durch den in der Turbineneinheit 13 angeordneten Abschnitt des Strömungskanals 27.After operation of the gas turbine 1, the method for cooling the gas turbine 1 is performed. In this case, the rotor 5 is driven by a rotating device, not shown, at a reduced speed, for example in the range of 80 min -1 to 160 min -1 , preferably at 120 min -1 , to cool it. The rotor 5 pumps in relation to the operation The gas turbine 1 thus sucks in a comparatively small air mass flow and pumps it through the section of the flow channel 27 arranged in the compressor, through the combustion chamber and through the turbine unit 13 arranged portion of the flow channel 27th

Der Abkühlvorgang wird weiter beschleunigt, indem während des Drehbetriebes, auch Abkühlbetrieb genannt, in den angesaugten Luftstrom zusätzlich destilliertes Wasser vor dem Verdichter 9 eingebracht wird. Die Verdampfung des Wassers kühlt den angesaugten Luftstrom, wodurch diese beim Durchströmen der Gasturbine 1 vermehrt die in der Gasturbine 1 gespeicherte Wärme aufnehmen und abtransportieren kann. Während der Wassereinbringung kann die Drehzahl des Rotors 5, beispielsweise auf 4% bis 10% der Nenndrehzahl, erhöht werden.The cooling process is further accelerated by additionally called distilled water in front of the compressor 9 in the intake air flow during the rotary operation, also called cooling operation. The evaporation of the water cools the sucked-in air flow, as a result of which, as it flows through the gas turbine 1, it increasingly absorbs and removes the heat stored in the gas turbine 1. During the introduction of water, the rotational speed of the rotor 5 can be increased, for example to 4% to 10% of the nominal rotational speed.

Ferner kann das Einbringen der Flüssigkeit 43 durch geeignete Mittel sowohl in der Ringbrennkammer 11 als auch in den Strömungskanals 27 der Turbineneinheit 13 erfolgen.Furthermore, the introduction of the liquid 43 can take place by suitable means both in the annular combustion chamber 11 and in the flow channel 27 of the turbine unit 13.

Claims (5)

  1. Method for cooling down a gas turbine (1) with a compressor (9), a turbine unit (13) and with a rotor (5), which method is carried out after operation of the gas turbine (1), and during which the rotor (5) is driven at reduced nominal speed, at least temporarily during a cooling down phase,
    characterized in that
    for cooling a liquid (43) is introduced into the air flow upstream of the compressor (9) at least temporarily during the cooling down phase, which air flow flows through at least the flow passage (27) of the compressor (9) and the flow passage (27) of the turbine unit (13) of the gas turbine (1).
  2. Method according to claim 1,
    characterized in that
    the speed of the rotor (5) during the introduction of liquid is higher than the speed at which no introduction of liquid takes place.
  3. Method according to claim 1 or 2,
    characterized in that
    the injection of the liquid (43) is carried out by means of a compressor washing unit (45).
  4. Method according to claim 1, 2 or 3,
    characterized in that
    an additional introduction of liquid (43) into a combustion chamber of the gas turbine (1) or into the flow passage (27) of the turbine unit (13) is carried out.
  5. Method according to one of claims 1 to 4,
    characterized in that
    distilled water is introduced as liquid (43).
EP05777877A 2004-08-25 2005-08-12 Fluid injection in a gas turbine during a cooling down period Not-in-force EP1784557B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
ES05777877T ES2304709T3 (en) 2004-08-25 2005-08-12 INJECTION OF LIQUID IN A GAS TURBINE DURING A REFRIGERATION PHASE.
EP05777877A EP1784557B1 (en) 2004-08-25 2005-08-12 Fluid injection in a gas turbine during a cooling down period

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP04020155A EP1630356A1 (en) 2004-08-25 2004-08-25 Fluid injection in a gas turbine during a cooling down period
PCT/EP2005/053969 WO2006021520A1 (en) 2004-08-25 2005-08-12 Injection of liquid into a gas turbine during a cooling phase
EP05777877A EP1784557B1 (en) 2004-08-25 2005-08-12 Fluid injection in a gas turbine during a cooling down period

Publications (2)

Publication Number Publication Date
EP1784557A1 EP1784557A1 (en) 2007-05-16
EP1784557B1 true EP1784557B1 (en) 2008-03-19

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EP04020155A Withdrawn EP1630356A1 (en) 2004-08-25 2004-08-25 Fluid injection in a gas turbine during a cooling down period
EP05777877A Not-in-force EP1784557B1 (en) 2004-08-25 2005-08-12 Fluid injection in a gas turbine during a cooling down period

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP04020155A Withdrawn EP1630356A1 (en) 2004-08-25 2004-08-25 Fluid injection in a gas turbine during a cooling down period

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US (1) US7752847B2 (en)
EP (2) EP1630356A1 (en)
AT (1) ATE389785T1 (en)
DE (1) DE502005003367D1 (en)
ES (1) ES2304709T3 (en)
PT (1) PT1784557E (en)
WO (1) WO2006021520A1 (en)

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US10400629B2 (en) 2012-01-31 2019-09-03 United Technologies Corporation Gas turbine engine shaft bearing configuration
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US10823054B2 (en) * 2012-11-06 2020-11-03 Fuad AL MAHMOOD Reducing the load consumed by gas turbine compressor and maximizing turbine mass flow
WO2015038451A1 (en) * 2013-09-10 2015-03-19 United Technologies Corporation Fluid injector for cooling a gas turbine engine component
EP3023604A1 (en) 2014-11-18 2016-05-25 Siemens Aktiengesellschaft Method and system for cooling off a gas turbine
US10082089B2 (en) * 2016-08-25 2018-09-25 General Electric Company Systems and methods to improve shut-down purge flow in a gas turbine system
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US10082091B2 (en) * 2016-08-25 2018-09-25 General Electric Company Systems and methods to improve shut-down purge flow in a gas turbine system
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Also Published As

Publication number Publication date
WO2006021520A1 (en) 2006-03-02
EP1630356A1 (en) 2006-03-01
ATE389785T1 (en) 2008-04-15
DE502005003367D1 (en) 2008-04-30
EP1784557A1 (en) 2007-05-16
PT1784557E (en) 2008-06-27
ES2304709T3 (en) 2008-10-16
US20070251210A1 (en) 2007-11-01
US7752847B2 (en) 2010-07-13

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