EP1505254A2 - Gas turbine and associated cooling method - Google Patents

Gas turbine and associated cooling method Download PDF

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Publication number
EP1505254A2
EP1505254A2 EP04103627A EP04103627A EP1505254A2 EP 1505254 A2 EP1505254 A2 EP 1505254A2 EP 04103627 A EP04103627 A EP 04103627A EP 04103627 A EP04103627 A EP 04103627A EP 1505254 A2 EP1505254 A2 EP 1505254A2
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EP
European Patent Office
Prior art keywords
gas turbine
steam
cooling
air
cooling device
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.)
Granted
Application number
EP04103627A
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German (de)
French (fr)
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EP1505254B1 (en
EP1505254A3 (en
Inventor
Dilip Mukherjee
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Ansaldo Energia Switzerland AG
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Alstom Technology AG
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Publication of EP1505254A3 publication Critical patent/EP1505254A3/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
    • F05D2260/2322—Heat transfer, e.g. cooling characterized by the cooling medium steam

Definitions

  • the present invention relates to a gas turbine, in particular in one Power plant.
  • the invention also relates to an associated method for cooling the gas turbine.
  • Steam is due to its higher heat capacity and its lower viscosity, in principle, a better cooling medium than air. Steam In addition to cooling air also reduces the specific compressor power through the elimination of the pressure losses of the cooling air and reduces the NOX emissions by a lower at the same turbine inlet temperature Combustion chamber temperature.
  • the steam cooling can be designed as an open or closed system become.
  • an open system eg film cooling of the blades
  • the Steam after he has fulfilled his cooling task, added to the working gas and thus acts as an efficiency and efficiency enhancer on the gas turbine.
  • the present invention as characterized in the claims deals with the problem, for a gas turbine initially mentioned kind to provide an improved embodiment, with which in particular a Higher performance and extended life of critical components can be achieved.
  • the invention is based on the general idea, in a gas turbine, which with a conventional air cooling device for cooling parts of Gas turbine is formed by means of air, in addition a steam cooling device provide, which for cooling parts of the gas turbine by means of steam is trained.
  • the cooling of a rotor and a stator of the gas turbine Conventionally carried out with air, while additionally a small amount of steam e.g. from entering the turbine to exiting the turbine along a Rotor shell flows parallel to the hot gas flow. Steam is due to his higher heat capacity and its lower viscosity in principle a better Cooling medium as air. Steam instead of cooling air also reduces the required Coolant volume by approx. 50%.
  • the essential advantage of the invention is that the performance of the additionally with steam cooled gas turbine compared to the conventional one air-cooled gas turbine increases by about 2 to 5%. This results from the higher turbine inlet temperature, which leads to a higher power. It is also noteworthy that only a comparatively small, purposeful applied amount of steam is needed, in conjunction with the air cooling a to achieve intensive cooling of the gas turbine.
  • the steam cooling device may be designed at least for cooling the inner inner lining and / or the inner outer lining of the combustion chamber and / or the guide vanes and / or hub-side covering elements of the vanes, and / or for a steam guide to do so is formed, that from the row of vanes along a rotor shell, a vapor film is formed.
  • This steam film protects the rotor from contact with the hot gas flow and thus leads to an extended life of the critical components of the gas turbine.
  • the Steam cooling device for cooling an upstream region of the Guide vanes and the air cooling device for cooling a downstream side Be formed portion of the vanes offers the advantage that the Guide vanes in the thermally more heavily loaded inflow area intensively with steam be cooled.
  • the invention uses the knowledge that for cooling the thermally less heavily polluted outflow area the air cooling sufficient, whereby with comparatively little energy a sufficient Blade cooling is achieved. If the injected for cooling steam over Outlets again exits into the hot gas stream, he produced at the Outer skin of the respective vane a fine vapor layer, which over the guide vanes and this similar to the rotor shell described above Protects against direct contact with the hot gas stream and thus to Robustness of the gas turbine contributes.
  • the steam required for the steam cooling device can advantageously from a Waste heat boiler are taken from a steam turbine, which with the Gas turbine is coupled.
  • the steam cooling thus requires no additional Steam generator.
  • a gas turbine 1 according to the invention comprises a combustion chamber 2 (burner not shown), a stator 5, a rotor 8 and a partially shown air cooling device 31 and also only partially shown steam cooling device 32nd
  • the combustion chamber 2 is of a surrounded inner lining 3 and an inner outer lining 4.
  • a hot gas stream 28 heated in the combustion chamber 2 strikes at least one row of guide vanes 6 with a plurality of guide vanes 7, which each have an inflow-side region 14 and an outflow-side region 15.
  • a blade row 9 with a plurality of blades 10, which form part of the rotor 8.
  • the steam cooling device 32 comprises a first cooling channel 24, which is arranged in the inner outer lining and, during operation of the steam cooling device 32, flows through vapor D.
  • the first cooling channel 24 communicates at the end via an outer cover plate 29 with a third cooling channel 25, which is integrated in the guide blade 7.
  • the third cooling channel 25 is arranged in the inflow-side region 14 of the guide vane 7 and has outlet openings 27, which communicate with the hot gas stream 28 on an outer side of the respective vane 7.
  • the third cooling channel 27 communicates at the end with hub-side cover elements 11, so that the remaining, not exited through the outlet openings 27 steam D flows into the hub-side cover 11 and this also cools.
  • outlet openings 27 ' are provided on the hub-side covering elements 11, from which the vapor D exits into the gas turbine 1 in the region of an inlet 21.
  • the goal here is that most of the vapor D exits through the outlet openings 27 '.
  • a second cooling channel 23 which is substantially parallel to the hot gas stream 28 in Direction of the vanes 7 runs.
  • the second cooling channel 23 communicates at the end via outlet openings 27 ", which in the region of the hub side Covering elements 11 are arranged, with the hot gas stream 28 at the entrance of the Gas turbine 1.
  • the steam D required for the steam cooling device 32 can advantageously not shown steam generators, in particular from a waste heat boiler, a Startup steam generator or a steam turbine can be removed, which with the gas turbine is coupled. An additional steam generator for the Steam cooling is therefore not required.
  • the air cooling device 31 comprises a fourth cooling channel 26 of FIG is integrated into the guide vanes 7 in the downstream region 15.
  • the cooling channel 26 is the input side with a cooling air source, not shown, beispw.
  • the fourth Cooling channel 26 is traversed by air L and cooled by this.
  • the blade row 9 Downstream of the guide vane row 6 is the blade row 9 with several Blades 10 arranged.
  • the blades 10 are as in conventional Gas turbine 1 cooled with air L, which in the illustrated embodiment the rotor side flows into the blades 10.
  • the air cooling device 31 is both according to the illustrated embodiment for cooling the blades 10 as well as downstream of the vanes. 7 arranged heat accumulation elements 19 is formed. The cooling of the Heat storage elements 19 takes place by cooling the hot gas stream 28 facing away from the heat accumulation elements 19. Additionally or alternatively can according to FIG. 1 air L immediately downstream of the blades 10 in the Gas turbine 1 are blown and thus cooling the furnishedstauicide 19 on the hot gas stream 28 side facing or cause and / or reinforce the rotor shell 12.
  • the usual cooling medium of hot gas components in a gas turbine 1 is air L, which from an end or intermediate stage of a not shown Compressor is removed.
  • Critical places are the inside Interior trim 3 and the inside 4 of the outer lining Combustion chamber 2, the first row of vanes 6, the first blade row. 9 and the turbine rotor 8.
  • the invention proposes a combined cooling by means of steam D and Air L ahead.
  • the preferably slightly superheated steam D of the steam cooling device 32 flows in designated cooling channels 23 of the inner lining 3 (Inner liner) and cooling channels 24 of the inner outer lining 4 (Outer liner) from the burner side.
  • the inflowing steam D emerges from the end of the first cooling channel 24 and then is a Leitschaufelau jointplatte 29 in a followed by the third cooling channel 25 forwarded.
  • the steam D flows into the hub-side cover plate 11 of the guide vane 7 and via outlet openings 27 'in the gas turbine 1.
  • the steam D flows via outlet openings 27 in the upstream region 14 of the guide vanes 7 in The gas turbine 1.
  • the goal here is that the majority of the steam D at the Hub exits.
  • Another vapor stream D is fed to the inner liner 3 on the burner side and flows through cooling channels 23 of the inner liner 3 parallel to the hot gas stream 28th to the outlet opening 27 "in the region of the hub-side cover 11th
  • the two vapor streams D of the inner liner 3 and the hub side Cover plate 11 form due to the higher density of the vapor D opposite the hot gas stream 28 during the expansion along the turbine 1 downstream of the Guide vanes 7 a steam curtain or film 13 of a certain current thickness along the rotor shell 12 or at the edge of the hot gas flow 28.
  • This Steam film 13 protects the rotor 8 from contact with the hot gas stream 28 and leads thereby to an extended life of the critical components of Gas turbine 1.
  • the inner lining 3 and the inner outer lining 4 are cooled with steam D.
  • the steam required for this is approx. 50% of the amount of cooling air.
  • the slightly overheated steam D required for cooling is preferably removed from a waste heat boiler, not shown. there can be provided that both the first cooling channel 24 and the second Cooling channel 23 from a common or separate waste heat boiler (s) can be fed.
  • the power of the operated with the combined air or steam cooling Gas turbine 1 takes over the conventional air-cooled gas turbine about 2 to 5 percent, resulting in a combined gas turbine steam turbine plant
  • the steam turbine power decreases due to the removal of the slightly superheated steam D from the waste heat boiler slightly, whereas the heat output of the waste heat boiler as a result of larger amount of gas turbine increases. Almost the largest part of this Performance is therefore due to the relaxation of the steam after cooling the inner lining 3,4 and the guide vanes 7 at a much higher Temperature and recovered at up to 1 bar in the gas turbine 1.
  • the Saved cooling air amount of the guide vanes 7 flows through the combustion chamber. 2 and takes part in the combustion process, whereby an additional power of the Gas turbine 1 is achieved.
  • the gas turbine 1 is shown in another embodiment, which is designed to carry out a sequential combustion.
  • a high-pressure combustion chamber 2 'and a Hochdruckleitschaufelsch 22 are provided with a plurality of Hochdruckleitschaufeln 16 and at least one high-pressure blade row 17 with a plurality of high-pressure blades 18, which are followed downstream of a low-pressure combustion chamber and a low-pressure turbine, not shown.
  • the high pressure blades 18 and the high pressure vanes 16 are cooled at least in their Anström Jardin with steam D, while the trailing edges of the high pressure vanes 16 can be cooled either also with steam or conventional with air.
  • the design of the various cooling channels is designed so that a certain amount of steam flows through the high-pressure guide vanes 16 into the hub-side cover elements 11.
  • a large part of the steam D then flows into the gas turbine 1 via outlet openings 27 'in a manner similar to that in FIG.
  • the other part of the steam D flows into a gap 30, which is arranged below the rotor shell 12 and between the high pressure vanes 16 and the high pressure blades 18 to be sucked from there by the high pressure blades 18 for cooling.
  • a portion of the steam D blocks the described gap 30 between Hochdruckleit- and high-pressure blades 16,18 with a certain amount of blown steam D.
  • the remaining components are air-cooled.
  • gas turbine 1 with sequential combustion produces the exited through the outlet openings 27 'vapor D a Steam film 13, which surrounds the rotor shell 12 and this before direct Contact with the hot gas stream 28 protects.
  • Fig. 3 is a variant for cooling a High pressure compressor 20 shown.
  • the invention provides, in a gas turbine 1, which with a conventional Air cooling device 31 for cooling parts of the gas turbine 1 by means of air is formed, in addition to provide a steam cooling device 32, which for Cooling of parts of the gas turbine 1 is formed by means of steam.
  • the cooling of the rotor 8 and the stator 5 is conventional with air L executed.
  • the advantages of the invention are that the performance of the additional with Steam D cooled gas turbine 1 compared to the conventional air-cooled Gas turbine 1, e.g. by about 2 to 5%, increases and at the same time due to the Steam films 13 a longer life of the critical components can be achieved can.

Abstract

The gas turbine (1) has at least one combustion chamber (2) enclosed by inner cladding (3) and outer cladding (4), a stator (6) with at least one row of blades, a rotor (8) with at least one row of blades, an air cooler (31) for cooling parts of the gas turbine with air and an additional steam cooler (32) for cooling parts of turbine with steam. An independent claim is also included for the following: (a) a method of cooling a gas turbine.

Description

Die vorliegende Erfindung betrifft eine Gasturbine, insbesondere in einer Kraftwerksanlage. Die Erfindung betrifft außerdem ein zugehöriges Verfahren zum Kühlen der Gasturbine.The present invention relates to a gas turbine, in particular in one Power plant. The invention also relates to an associated method for cooling the gas turbine.

Stand der TechnikState of the art

Ein Großteil der benötigten elektrischen Energie wird in Kraftwerken mit Hilfe von Dampf- und/oder Gasturbinen erzeugt. Der Wirkungsgrad dieser Anlagen ist entscheidend durch die Eintrittstemperatur des Arbeitsmediums (Gas oder Dampf) bestimmt. Sollen höhere Wirkungsgrade realisiert werden, so muss man zu höheren Temperaturen übergehen. Durch diese Temperaturerhöhungen wird jedoch sehr schnell die Grenze der Materialbeanspruchung erreicht. Deshalb ist zur Steigerung des Wirkungsgrades eine verstärkte Kühlung der Dampfund/oder Gasturbine erforderlich. Das übliche Kühlmedium der heißgasführenden Bauteile in einer Gasturbine ist Luft, entnommen aus der End- oder Zwischenstufe des Verdichters. Kritische Stellen sind dabei die Brennkammerauskleidung, die erste Leitschaufelreihe, die erste Laufschaufelreihe, der Turbinenrotor und der hintere Verdichterabschnitt. Generell ist aber auch eine Kühlung von Dampf- oder Gasturbinen mittels Dampf bekannt (DE 3003347). Dampf ist aufgrund seiner höheren Wärmekapazität und seiner kleineren Viskosität prinzipiell ein besseres Kühlmedium als Luft. Dampf anstelle von Kühlluft reduziert zudem die spezifische Verdichterleistung durch den Wegfall der Druckverluste der Kühlluft und vermindert die NOX-Emissionen durch eine bei gleicher Turbineneintrittstemperatur niedrigere Brennkammertemperatur.Much of the required electrical energy is used in power plants with the help of Steam and / or gas turbines generated. The efficiency of these systems is crucial by the inlet temperature of the working medium (gas or Steam). If higher efficiencies are to be realized, then one has to move to higher temperatures. Due to these temperature increases is However, very quickly reached the limit of material stress. Therefore To increase the efficiency of an increased cooling of the steam and / or Gas turbine required. The usual cooling medium of the hot gas Components in a gas turbine is air, taken from the end or Intermediate stage of the compressor. Critical places are the Combustion lining, the first row of vanes, the first Blade row, the turbine rotor and the rear compressor section. In general, however, is also a cooling of steam or gas turbines by means of steam known (DE 3003347). Steam is due to its higher heat capacity and its lower viscosity, in principle, a better cooling medium than air. steam In addition to cooling air also reduces the specific compressor power through the elimination of the pressure losses of the cooling air and reduces the NOX emissions by a lower at the same turbine inlet temperature Combustion chamber temperature.

Die Dampfkühlung kann als offenes oder als geschlossenes System ausgeführt werden. Bei einem offenen System (z. B. Filmkühlung der Schaufeln) wird der Dampf, nachdem er seine Kühlaufgabe erfüllt hat, dem Arbeitsgas zugemischt und wirkt dadurch leistungs- und wirkungsgradsteigernd auf die Gasturbine.The steam cooling can be designed as an open or closed system become. In an open system (eg film cooling of the blades) the Steam, after he has fulfilled his cooling task, added to the working gas and thus acts as an efficiency and efficiency enhancer on the gas turbine.

Darstellung der ErfindungPresentation of the invention

Die vorliegende Erfindung, wie sie in den Ansprüchen gekennzeichnet ist, beschäftigt sich mit dem Problem, für eine Gasturbine eingangs erwähnter Art eine verbesserte Ausführungsform anzugeben, mit welcher insbesondere eine höhere Leistung sowie eine verlängerte Lebensdauer der kritischen Bauteile erreicht werden kann.The present invention as characterized in the claims deals with the problem, for a gas turbine initially mentioned kind to provide an improved embodiment, with which in particular a Higher performance and extended life of critical components can be achieved.

Erfindungsgemäß wird dieses Problem durch die Gegenstände der unabhängigen Ansprüche gelöst. Vorteilhafte Ausführungsformen sind Gegenstand der abhängigen Ansprüche.According to the invention, this problem is solved by the objects of solved independent claims. Advantageous embodiments are Subject of the dependent claims.

Die Erfindung beruht auf dem allgemeinen Gedanken, bei einer Gasturbine, welche mit einer herkömmlichen Luftkühleinrichtung zur Kühlung von Teilen der Gasturbine mittels Luft ausgebildet ist, zusätzlich eine Dampfkühleinrichtung vorzusehen, welche zur Kühlung von Teilen der Gasturbine mittels Dampf ausgebildet ist. The invention is based on the general idea, in a gas turbine, which with a conventional air cooling device for cooling parts of Gas turbine is formed by means of air, in addition a steam cooling device provide, which for cooling parts of the gas turbine by means of steam is trained.

Beispielsweise wird die Kühlung eines Rotors und eines Stators der Gasturbine konventionell mit Luft ausgeführt, während zusätzlich eine kleine Dampfmenge z.B. vom Eintritt in die Turbine bis zum Austritt aus der Turbine entlang eines Rotormantels parallel zum Heißgasstrom strömt. Dampf ist aufgrund seiner höheren Wärmekapazität und seiner kleineren Viskosität prinzipiell ein besseres Kühlmedium als Luft. Dampf anstelle von Kühlluft reduziert zudem die benötigte Kühlmediummenge um ca. 50 %.For example, the cooling of a rotor and a stator of the gas turbine Conventionally carried out with air, while additionally a small amount of steam e.g. from entering the turbine to exiting the turbine along a Rotor shell flows parallel to the hot gas flow. Steam is due to his higher heat capacity and its lower viscosity in principle a better Cooling medium as air. Steam instead of cooling air also reduces the required Coolant volume by approx. 50%.

Der wesentliche Vorteil der Erfindung besteht darin, dass die Leistung der zusätzlich mit Dampf gekühlten Gasturbine gegenüber der konventionellen luftgekühlten Gasturbine um ca. 2 bis 5 % zunimmt. Dies resultiert aus der höheren Turbineneintrittstemperatur, welche zu einer höheren Leistung führt. Bemerkenswert ist außerdem, dass nur eine vergleichsweise kleine, gezielt applizierte Dampfmenge benötigt wird, um zusammen mit der Luftkühlung eine intensive Kühlung der Gasturbine zu erzielen.The essential advantage of the invention is that the performance of the additionally with steam cooled gas turbine compared to the conventional one air-cooled gas turbine increases by about 2 to 5%. This results from the higher turbine inlet temperature, which leads to a higher power. It is also noteworthy that only a comparatively small, purposeful applied amount of steam is needed, in conjunction with the air cooling a to achieve intensive cooling of the gas turbine.

Gemäß einer bevorzugten Ausführungsform der erfindungsgemäßen Lösung kann vorgesehen sein, dass die Dampfkühleinrichtung zumindest zur Kühlung der innenliegenden Innenverkleidung und/oder der innenliegenden Außenverkleidung der Brennkammer und/oder der Leitschaufeln und/oder nabenseitiger Abdeckelemente der Leitschaufeln ausgebildet ist, und/oder dass eine Dampfführung so ausgebildet ist, dass ab der Leitschaufelreihe entlang eines Rotormantels ein Dampffilm entsteht.
Dieser Dampffilm schützt den Rotor vor Kontakt mit dem Heißgasstrom und führt dadurch zu einer verlängerten Lebensdauer der kritischen Bauteile der Gasturbine.According to a preferred embodiment of the solution according to the invention, provision may be made for the steam cooling device to be designed at least for cooling the inner inner lining and / or the inner outer lining of the combustion chamber and / or the guide vanes and / or hub-side covering elements of the vanes, and / or for a steam guide to do so is formed, that from the row of vanes along a rotor shell, a vapor film is formed.
This steam film protects the rotor from contact with the hot gas flow and thus leads to an extended life of the critical components of the gas turbine.

Entsprechend einer bevorzugten Ausführungsform der Erfindung kann die Dampfkühleinrichtung zur Kühlung eines anströmseitigen Bereichs der Leitschaufeln und die Luftkühleinrichtung zur Kühlung eines abströmseitigen Bereichs der Leitschaufeln ausgebildet sein. Dies bietet den Vorteil, dass die Leitschaufeln im thermisch stärker belasteten Anströmbereich intensiv mit Dampf gekühlt werden. Die Erfindung nutzt dabei die Erkenntnis, dass zur Kühlung des thermisch weniger stark belasteten Abströmungsbereichs die Luftkühlung ausreicht, wodurch mit vergleichsweise wenig Energie eine hinreichende Schaufelkühlung erreicht wird. Sofern der zur Kühlung eingeblasene Dampf über Austrittsöffnungen wieder in den Heißgasstrom austritt, erzeugt er an der Außenhaut der jeweiligen Leitschaufel eine feine Dampfschicht, welche sich über die Leitschaufeln legt und diese ähnlich dem Rotormantel in oben beschriebener Weise vor direktem Kontakt mit dem Heißgasstrom schützt und damit zur Robustheit der Gasturbine beiträgt.According to a preferred embodiment of the invention, the Steam cooling device for cooling an upstream region of the Guide vanes and the air cooling device for cooling a downstream side Be formed portion of the vanes. This offers the advantage that the Guide vanes in the thermally more heavily loaded inflow area intensively with steam be cooled. The invention uses the knowledge that for cooling the thermally less heavily polluted outflow area the air cooling sufficient, whereby with comparatively little energy a sufficient Blade cooling is achieved. If the injected for cooling steam over Outlets again exits into the hot gas stream, he produced at the Outer skin of the respective vane a fine vapor layer, which over the guide vanes and this similar to the rotor shell described above Protects against direct contact with the hot gas stream and thus to Robustness of the gas turbine contributes.

Der für die Dampfkühleinrichtung benötigte Dampf kann vorteilhaft aus einem Abhitzekessel einer Dampfturbine entnommen werden, welche mit der Gasturbine gekoppelt ist. Die Dampfkühlung erfordert somit keinen zusätzlichen Dampferzeuger.The steam required for the steam cooling device can advantageously from a Waste heat boiler are taken from a steam turbine, which with the Gas turbine is coupled. The steam cooling thus requires no additional Steam generator.

Weitere wichtige Merkmale und Vorteile der vorliegenden Erfindung ergeben sich aus den Unteransprüchen, aus den Zeichnungen und aus der zugehörigen Figurenbeschreibung anhand der Zeichnungen.Other important features and advantages of the present invention will become apparent from the subclaims, from the drawings and from the associated Description of the figures with reference to the drawings.

Kurze Beschreibung der ZeichnungenBrief description of the drawings

Bevorzugte Ausführungsbeispiele der Erfindung sind in den Zeichnungen dargestellt und werden in der nachfolgenden Beschreibung näher erläutert, wobei sich gleiche Bezugszeichen auf gleiche oder ähnliche oder funktional gleiche Merkmale bezieht. Preferred embodiments of the invention are shown in the drawings and are explained in more detail in the following description, wherein the same reference numerals to the same or similar or functionally identical Features relates.

Es zeigen, jeweils schematisch

Fig. 1
einen Längsschnitt durch eine erfindungsgemäße Gasturbine,
Fig. 2
eine Darstellung wie in Fig. 1, jedoch bei einer anderen Ausführungsform,
Fig. 3
einen Längsschnitt durch einen Hochdruckverdichter.
It show, each schematically
Fig. 1
a longitudinal section through a gas turbine according to the invention,
Fig. 2
4 shows a representation as in FIG. 1, but in another embodiment,
Fig. 3
a longitudinal section through a high pressure compressor.

Wege zur Ausführung der ErfindungWays to carry out the invention

Entsprechend Fig. 1 umfasst eine Gasturbine 1 nach der Erfindung eine Brennkammer 2 (Brenner nicht dargestellt), einen Stator 5, einen Rotor 8 sowie eine nur teilweise dargestellte Luftkühleinrichtung 31 und eine ebenfalls nur zum Teil dargestellte Dampfkühleinrichtung 32. Die Brennkammer 2 wird von einer innenliegenden Innenverkleidung 3 und einer innenliegenden Außenverkleidung 4 umgeben. In Strömungsrichtung nach der Brennkammer 2 trifft ein in der Brennkammer 2 erhitzter Heißgasstrom 28 auf zumindest eine Leitschaufelreihe 6 mit mehreren Leitschaufeln 7, welche jeweils einen anströmseitigen Bereich 14 und einen abströmseitigen Bereich 15 aufweisen. Danach folgt eine Laufschaufelreihe 9 mit mehreren Laufschaufeln 10, welche einen Teil des Rotors 8 bilden.
Gemäß Fig. 1 umfasst die Dampfkühleinrichtung 32 einen ersten Kühlkanal 24, der in der innenliegenden Außenverkleidung angeordnet und im Betrieb der Dampfkühleinrichtung 32 von Dampf D durchströmt ist. Der erste Kühlkanal 24 kommuniziert endseitig über eine Außendeckplatte 29 mit einem dritten Kühlkanal 25, welcher in die Leitschaufel 7 integriert ist. Der dritte Kühlkanal 25 ist im anströmseitigen Bereich 14 der Leitschaufel 7 angeordnet und weist Austrittsöffnungen 27 auf, welche auf einer Außenseite der jeweiligen Leitschaufel 7 mit dem Heißgasstrom 28 in Verbindung stehen. Der dritte Kühlkanal 27 kommuniziert endseitig mit nabenseitigen Abdeckelementen 11, so dass der restliche, nicht durch die Austrittsöffnungen 27 ausgetretene Dampf D in die nabenseitigen Abdeckelemente 11 einströmt und diese ebenfalls kühlt. Ähnlich den Austrittsöffnungen 27 am anströmseitigen Bereich 14 der Leitschaufel 7 sind Austrittsöffnungen 27' an den nabenseitigen Abdeckelementen 11 vorgesehen, aus welchen der Dampf D im Bereich eines Eintritts 21 in die Gasturbine 1 austritt. Das Ziel ist hierbei, dass der größte Teil des Dampfes D durch die Austrittsöffnungen 27' austritt.1, a gas turbine 1 according to the invention comprises a combustion chamber 2 (burner not shown), a stator 5, a rotor 8 and a partially shown air cooling device 31 and also only partially shown steam cooling device 32nd The combustion chamber 2 is of a surrounded inner lining 3 and an inner outer lining 4. In the direction of flow after the combustion chamber 2, a hot gas stream 28 heated in the combustion chamber 2 strikes at least one row of guide vanes 6 with a plurality of guide vanes 7, which each have an inflow-side region 14 and an outflow-side region 15. This is followed by a blade row 9 with a plurality of blades 10, which form part of the rotor 8.
According to FIG. 1, the steam cooling device 32 comprises a first cooling channel 24, which is arranged in the inner outer lining and, during operation of the steam cooling device 32, flows through vapor D. The first cooling channel 24 communicates at the end via an outer cover plate 29 with a third cooling channel 25, which is integrated in the guide blade 7. The third cooling channel 25 is arranged in the inflow-side region 14 of the guide vane 7 and has outlet openings 27, which communicate with the hot gas stream 28 on an outer side of the respective vane 7. The third cooling channel 27 communicates at the end with hub-side cover elements 11, so that the remaining, not exited through the outlet openings 27 steam D flows into the hub-side cover 11 and this also cools. Similar to the outlet openings 27 on the inflow-side region 14 of the guide vane 7, outlet openings 27 'are provided on the hub-side covering elements 11, from which the vapor D exits into the gas turbine 1 in the region of an inlet 21. The goal here is that most of the vapor D exits through the outlet openings 27 '.

Des weiteren ist in der innenliegenden Innenverkleidung 3 ein zweiter Kühlkanal 23 angeordnet, welcher im Wesentlichen parallel zum Heißgasstrom 28 in Richtung der Leitschaufeln 7 verläuft. Der zweite Kühlkanal 23 kommuniziert endseitig über Austrittsöffnungen 27", welche im Bereich der nabenseitigen Abdeckelemente 11 angeordnet sind, mit dem Heißgasstrom 28 am Eingang der Gasturbine 1.Furthermore, in the inner lining 3, a second cooling channel 23, which is substantially parallel to the hot gas stream 28 in Direction of the vanes 7 runs. The second cooling channel 23 communicates at the end via outlet openings 27 ", which in the region of the hub side Covering elements 11 are arranged, with the hot gas stream 28 at the entrance of the Gas turbine 1.

Der für die Dampfkühleinrichtung 32 benötigte Dampf D kann vorteilhaft von nicht dargestellten Dampfgeneratoren, insbesondere aus einem Abhitzekessel, einem Startup-Dampferzeuger oder einer Dampfturbine entnommen werden, welche mit der Gasturbine gekoppelt ist. Ein zusätzlicher Dampferzeuger für die Dampfkühlung wird somit nicht benötigt.The steam D required for the steam cooling device 32 can advantageously not shown steam generators, in particular from a waste heat boiler, a Startup steam generator or a steam turbine can be removed, which with the gas turbine is coupled. An additional steam generator for the Steam cooling is therefore not required.

Gemäß Fig. 1 umfasst die Luftkühleinrichtung 31 einen vierten Kühlkanal 26 der im abströmseitigen Bereich 15 in die Leitschaufeln 7 integriert ist. Der Kühlkanal 26 ist eingangsseitig mit einer nicht dargestellten Kühlluftquelle, beispw. einer End- oder Zwischenstufe eines Verdichters, verbunden und kann ausgangsseitig über Austrittsöffnungen 27''' mit dem Heißgasstrom 28 bzw. einem Inneren der Gasturbine 1 kommunizieren. Im Unterschied zum ersten, zweiten und dritten Kühlkanal 24,23,25 und den nabenseitigen Abdeckelementen 11, wird der vierte Kühlkanal 26 von Luft L durchströmt und durch diese gekühlt.According to FIG. 1, the air cooling device 31 comprises a fourth cooling channel 26 of FIG is integrated into the guide vanes 7 in the downstream region 15. The cooling channel 26 is the input side with a cooling air source, not shown, beispw. A End or intermediate stage of a compressor, connected and output side via outlet openings 27 '' 'with the hot gas stream 28 or an interior of the Gas turbine 1 communicate. Unlike the first, second and third Cooling channel 24,23,25 and the hub-side cover members 11, the fourth Cooling channel 26 is traversed by air L and cooled by this.

Stromab der Leitschaufelreihe 6 ist die Laufschaufelreihe 9 mit mehreren Laufschaufeln 10 angeordnet. Die Laufschaufeln 10 sind wie bei herkömmlichen Gasturbinen 1 mit Luft L gekühlt, welche in der dargestellten Ausführungsform rotorseitig in die Laufschaufeln 10 einströmt.Downstream of the guide vane row 6 is the blade row 9 with several Blades 10 arranged. The blades 10 are as in conventional Gas turbine 1 cooled with air L, which in the illustrated embodiment the rotor side flows into the blades 10.

Die Luftkühleinrichtung 31 ist gemäß der dargestellten Ausführungsform sowohl zur Kühlung der Laufschaufeln 10 als auch von stromab der Leitschaufeln 7 angeordneten Wärmestauelementen 19 ausgebildet. Die Kühlung der Wärmestauelemente 19 erfolgt dabei durch eine Kühlung der dem Heißgasstrom 28 abgewandten Seite der Wärmestauelemente 19. Zusätzlich oder alternativ kann gemäß Fig. 1 Luft L unmittelbar stromab der Laufschaufeln 10 in die Gasturbine 1 eingeblasen werden und somit eine Kühlung der Wärmestauelemente 19 auf der dem Heißgasstrom 28 zugewandten Seite bzw. des Rotormantels 12 bewirken und/oder verstärken.The air cooling device 31 is both according to the illustrated embodiment for cooling the blades 10 as well as downstream of the vanes. 7 arranged heat accumulation elements 19 is formed. The cooling of the Heat storage elements 19 takes place by cooling the hot gas stream 28 facing away from the heat accumulation elements 19. Additionally or alternatively can according to FIG. 1 air L immediately downstream of the blades 10 in the Gas turbine 1 are blown and thus cooling the Wärmestauelemente 19 on the hot gas stream 28 side facing or cause and / or reinforce the rotor shell 12.

Im Folgenden soll kurz die Funktionsweise der kombinierten Luft-/Dampfkühlung der erfindungsgemäßen Gasturbine 1 erläutert werden:In the following is briefly the operation of the combined air / steam cooling the gas turbine 1 of the invention are explained:

Das übliche Kühlmedium heißgasführender Bauteile in einer Gasturbine 1 ist Luft L, welche aus einer End- oder Zwischenstufe eines nicht dargestellten Verdichters entnommen wird. Kritische Stellen sind dabei die innenliegende Innenverkleidung 3 und die innenliegende Aussenverkleidung 4 der Brennkammer 2, die erste Leitschaufelreihe 6, die erste Laufschaufelreihe 9 sowie der Turbinenrotor 8. The usual cooling medium of hot gas components in a gas turbine 1 is air L, which from an end or intermediate stage of a not shown Compressor is removed. Critical places are the inside Interior trim 3 and the inside 4 of the outer lining Combustion chamber 2, the first row of vanes 6, the first blade row. 9 and the turbine rotor 8.

Um die Turbinenleistung zu erhöhen und die Lebensdauer der Gasturbine 1 zu verlängern, schlägt die Erfindung eine kombinierte Kühlung mittels Dampf D und Luft L vor.To increase turbine performance and increase the life of the gas turbine 1 extend, the invention proposes a combined cooling by means of steam D and Air L ahead.

Der vorzugsweise leicht überhitzte Dampf D der Dampfkühleinrichtung 32 strömt in dafür vorgesehene Kühlkanäle 23 der innenliegenden Innenverkleidung 3 (Innenliner) und Kühlkanäle 24 der innenliegenden Außenverkleidung 4 (Außenliner) von der Brennerseite her ein.The preferably slightly superheated steam D of the steam cooling device 32 flows in designated cooling channels 23 of the inner lining 3 (Inner liner) and cooling channels 24 of the inner outer lining 4 (Outer liner) from the burner side.

Der eingeströmte Dampf D tritt am Ende des ersten Kühlkanals 24 aus diesem aus und wird anschließend über eine Leitschaufelaußendeckplatte 29 in einen sich daran anschließenden dritten Kühlkanal 25 weitergeleitet. Nach der Kühlung der Außendeckplatte 29 und des angeströmten Bereichs 14 der Leitschaufel 7 strömt der Dampf D in die nabenseitige Abdeckplatte 11 der Leitschaufel 7 und über Austrittsöffnungen 27' in die Gasturbine 1. Gleichzeitig strömt der Dampf D über Austrittsöffnungen 27 im anströmseitigen Bereich 14 der Leitschaufeln 7 in die Gasturbine 1. Das Ziel ist hierbei, dass der größte Teil des Dampfes D an der Nabe austritt.The inflowing steam D emerges from the end of the first cooling channel 24 and then is a Leitschaufelaußendeckplatte 29 in a followed by the third cooling channel 25 forwarded. After cooling the outer cover plate 29 and the flowed-14 portion of the guide vane. 7 the steam D flows into the hub-side cover plate 11 of the guide vane 7 and via outlet openings 27 'in the gas turbine 1. At the same time the steam D flows via outlet openings 27 in the upstream region 14 of the guide vanes 7 in The gas turbine 1. The goal here is that the majority of the steam D at the Hub exits.

Ein weiterer Dampfstrom D wird dem Innenliner 3 an der Brennerseite zugeführt und strömt durch Kühlkanäle 23 des Innenliners 3 parallel zum Heißgasstrom 28 bis zur Austrittsöffnung 27" im Bereich der nabenseitigen Abdeckelemente 11. Die beiden Dampfströme D des Innenliners 3 und der nabenseitigen Abdeckplatte 11 bilden auf Grund der höheren Dichte des Dampfes D gegenüber dem Heißgasstrom 28 bei der Entspannung entlang der Turbine 1 stromab der Leitschaufeln 7 einen Dampfschleier bzw. -film 13 einer gewissen Stromdicke entlang des Rotormantels 12 bzw. randseitig des Heißgasstroms 28. Dieser Dampffilm 13 schützt den Rotor 8 vor Kontakt mit dem Heißgasstrom 28 und führt dadurch zu einer verlängerten Lebensdauer der kritischen Bauteile der Gasturbine 1.Another vapor stream D is fed to the inner liner 3 on the burner side and flows through cooling channels 23 of the inner liner 3 parallel to the hot gas stream 28th to the outlet opening 27 "in the region of the hub-side cover 11th The two vapor streams D of the inner liner 3 and the hub side Cover plate 11 form due to the higher density of the vapor D opposite the hot gas stream 28 during the expansion along the turbine 1 downstream of the Guide vanes 7 a steam curtain or film 13 of a certain current thickness along the rotor shell 12 or at the edge of the hot gas flow 28. This Steam film 13 protects the rotor 8 from contact with the hot gas stream 28 and leads thereby to an extended life of the critical components of Gas turbine 1.

Die innenliegende Innenverkleidung 3 sowie die innenliegende Außenverkleidung 4 werden mit Dampf D gekühlt. Die hierfür benötigte Dampfmenge beträgt ca. 50 % der Kühlluftmenge. Der zur Kühlung benötigte leicht überhitzte Dampf D wird vorzugsweise einem nicht dargestellten Abhitzekessel entnommenen. Dabei kann vorgesehen sein, dass sowohl der erste Kühlkanal 24 als auch der zweite Kühlkanal 23 aus einem gemeinsamen oder aus separaten Abhitzekessel(n) gespeist werden können.The inner lining 3 and the inner outer lining 4 are cooled with steam D. The steam required for this is approx. 50% of the amount of cooling air. The slightly overheated steam D required for cooling is preferably removed from a waste heat boiler, not shown. there can be provided that both the first cooling channel 24 and the second Cooling channel 23 from a common or separate waste heat boiler (s) can be fed.

Die Leistung der mit der kombinierten Luft- bzw. Dampfkühlung betriebenen Gasturbine 1 nimmt gegenüber der konventionellen luftgekühlten Gasturbine um ca. 2 bis 5 Prozent zu, was sich bei einer kombinierten Gasturbinen-Dampfturbinen-Anlage wie folgt erklären lässt: Die Dampfturbinenleistung nimmt infolge der Entnahme des leicht überhitzten Dampfes D aus dem Abhitzekessel leicht ab, wohingegen die Wärmeleistung des Abhitzekessels in Folge der größeren Menge aus der Gasturbine zunimmt. Fast der größte Teil dieser Leistung wird deshalb infolge der Entspannung des Dampfes nach der Kühlung der Innenverkleidung 3,4 und der Leitschaufeln 7 bei einer wesentlich höheren Temperatur und bei bis zu 1 bar in der Gasturbine 1 zurückgewonnen. Die eingesparte Kühlluftmenge der Leitschaufeln 7 strömt durch die Brennkammer 2 und nimmt am Verbrennungsprozess teil, wodurch eine Mehrleistung der Gasturbine 1 erreicht wird.The power of the operated with the combined air or steam cooling Gas turbine 1 takes over the conventional air-cooled gas turbine about 2 to 5 percent, resulting in a combined gas turbine steam turbine plant Explains as follows: The steam turbine power decreases due to the removal of the slightly superheated steam D from the waste heat boiler slightly, whereas the heat output of the waste heat boiler as a result of larger amount of gas turbine increases. Almost the largest part of this Performance is therefore due to the relaxation of the steam after cooling the inner lining 3,4 and the guide vanes 7 at a much higher Temperature and recovered at up to 1 bar in the gas turbine 1. The Saved cooling air amount of the guide vanes 7 flows through the combustion chamber. 2 and takes part in the combustion process, whereby an additional power of the Gas turbine 1 is achieved.

Entsprechend Fig. 2 ist die Gasturbine 1 in einer anderen Ausführungsform dargestellt, welche zur Durchführung einer sequentiellen Verbrennung ausgebildet ist. Hierzu sind zusätzlich eine Hochdruckbrennkammer 2' sowie eine Hochdruckleitschaufelreihe 22 mit mehreren Hochdruckleitschaufeln 16 und mindestens eine Hochdrucklaufschaufelreihe 17 mit mehreren Hochdrucklaufschaufeln 18 vorgesehen, welche stromab von einer nicht dargestellten Niederdruckbrennkammer und einer Niederdruckturbine gefolgt werden.
Hierbei werden die Hochdrucklaufschaufeln 18 und die Hochdruckleitschaufeln 16 zumindest in ihrem Anströmbereich mit Dampf D gekühlt, während die Hinterkanten der Hochdruckleitschaufeln 16 entweder ebenfalls mit Dampf oder aber herkömmlich mit Luft gekühlt werden können. Die Konstruktion der verschiedenen Kühlkanäle wird dabei so ausgestaltet, dass eine gewisse Dampfmenge durch die Hochdruckleitschaufeln 16 in die nabenseitigen Abdeckelemente 11 strömt. Ein großer Teil des Dampfes D strömt danach ähnlich wie in Fig. 1 über Austrittsöffnungen 27' in die Gasturbine 1 ein. Der andere Teil des Dampfes D strömt in einen Zwischenraum 30, welcher unterhalb des Rotormantels 12 und zwischen den Hochdruckleitschaufeln 16 und den Hochdrucklaufschaufeln 18 angeordnet ist, um von dort von den Hochdrucklaufschaufeln 18 zur Kühlung angesaugt zu werden. Gleichzeitig sperrt ein Teil des Dampfes D den beschriebenen Zwischenraum 30 zwischen Hochdruckleit- und Hochdrucklaufschaufeln 16,18 mit einer gewissen Menge an ausgeblasenem Dampf D. Die restlichen Bauteile werden luftgekühlt.2, the gas turbine 1 is shown in another embodiment, which is designed to carry out a sequential combustion. For this purpose, in addition, a high-pressure combustion chamber 2 'and a Hochdruckleitschaufelreihe 22 are provided with a plurality of Hochdruckleitschaufeln 16 and at least one high-pressure blade row 17 with a plurality of high-pressure blades 18, which are followed downstream of a low-pressure combustion chamber and a low-pressure turbine, not shown.
Here, the high pressure blades 18 and the high pressure vanes 16 are cooled at least in their Anströmbereich with steam D, while the trailing edges of the high pressure vanes 16 can be cooled either also with steam or conventional with air. The design of the various cooling channels is designed so that a certain amount of steam flows through the high-pressure guide vanes 16 into the hub-side cover elements 11. A large part of the steam D then flows into the gas turbine 1 via outlet openings 27 'in a manner similar to that in FIG. The other part of the steam D flows into a gap 30, which is arranged below the rotor shell 12 and between the high pressure vanes 16 and the high pressure blades 18 to be sucked from there by the high pressure blades 18 for cooling. At the same time, a portion of the steam D blocks the described gap 30 between Hochdruckleit- and high-pressure blades 16,18 with a certain amount of blown steam D. The remaining components are air-cooled.

Auch bei der in Fig. 2 dargestellten Gasturbine 1 mit sequenzieller Verbrennung erzeugt der durch die Austrittsöffnungen 27' ausgetretene Dampf D einen Dampffilm 13, welcher sich um den Rotormantel 12 legt und diesen vor direktem Kontakt mit dem Heißgasstrom 28 schützt.Also in the illustrated in Fig. 2 gas turbine 1 with sequential combustion produces the exited through the outlet openings 27 'vapor D a Steam film 13, which surrounds the rotor shell 12 and this before direct Contact with the hot gas stream 28 protects.

Gemäß Fig. 3 ist eine Ausführungsvariante zur Kühlung eines Hochdruckverdichters 20 gezeigt. Hierbei sind geeignete Wärmestauelemente 19 zwischen den Hochdruckleitschaufeln 16 und den Hochdrucklaufschaufeln 18 am Rotormantel 12 angeordnet und mit leicht überhitztem Dampf D, welcher am According to Fig. 3 is a variant for cooling a High pressure compressor 20 shown. Here are suitable heat storage elements 19th between the high pressure vanes 16 and the high pressure blades 18 at Rotor shell 12 arranged and with slightly superheated steam D, which am

Ende des Hochdruckverdichters 20 zugeführt und nach einer gewissen Strecke am Ende des Hochdruckverdichters 20 wieder zurückgeführt wird, gekühlt.End of the high pressure compressor 20 fed and after a certain distance is returned at the end of the high pressure compressor 20, cooled.

Zusammenfassend lassen sich die wesentlichen Merkmale der erfindungsgemäßen Lösung wie folgt charakterisieren:In summary, the essential features of inventive solution characterized as follows:

Die Erfindung sieht vor, bei einer Gasturbine 1, welche mit einer herkömmlichen Luftkühleinrichtung 31 zur Kühlung von Teilen der Gasturbine 1 mittels Luft ausgebildet ist, zusätzlich eine Dampfkühleinrichtung 32 vorzusehen, welche zur Kühlung von Teilen der Gasturbine 1 mittels Dampf ausgebildet ist.The invention provides, in a gas turbine 1, which with a conventional Air cooling device 31 for cooling parts of the gas turbine 1 by means of air is formed, in addition to provide a steam cooling device 32, which for Cooling of parts of the gas turbine 1 is formed by means of steam.

Die Kühlung des Rotors 8 und des Stators 5 wird konventionell mit Luft L ausgeführt. Zusätzlich strömt nun eine kleine Dampfmenge vom Eintritt 21 in die Gasturbine 1 bis zum Austritt aus der Gasturbine 1 entlang des Rotormantels 12 parallel zum Heißgasstrom 28. Auf Grund der höheren Dichte des Dampfes D gegenüber dem Heißgasstrom 28 bleibt dadurch ein Dampffilm 13 am Rotormantel 12 bestehen und schützt diesen vor direktem Kontakt mit dem Heißgasstrom 28.The cooling of the rotor 8 and the stator 5 is conventional with air L executed. In addition, now flows a small amount of steam from the inlet 21 in the Gas turbine 1 to the exit from the gas turbine 1 along the rotor shell 12th parallel to the hot gas stream 28. Due to the higher density of the steam D relative to the hot gas stream 28 thereby remains a vapor film 13 on Rotor shell 12 are made and protects it from direct contact with the Hot gas stream 28.

Die Vorteile der Erfindung bestehen darin, dass die Leistung der zusätzlich mit Dampf D gekühlten Gasturbine 1 gegenüber der konventionellen luftgekühlten Gasturbine 1, z.B. um ca. 2 bis 5 %, zunimmt und gleichzeitig aufgrund des Dampffilms 13 eine höhere Lebensdauer der kritischen Bauteile erreicht werden kann. The advantages of the invention are that the performance of the additional with Steam D cooled gas turbine 1 compared to the conventional air-cooled Gas turbine 1, e.g. by about 2 to 5%, increases and at the same time due to the Steam films 13 a longer life of the critical components can be achieved can.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Gasturbinegas turbine
22
Brennkammercombustion chamber
33
innenliegende Innenverkleidunginside lining
44
innenliegende Außenverkleidunginternal outer panel
55
Statorstator
66
Leitschaufelreihevane row
77
Leitschaufelvane
88th
Rotorrotor
99
LaufschaufelreiheBlade row
1010
Laufschaufelblade
1111
nabenseitige Abdeckelementehub-side cover elements
1212
Rotormantelsrotor shell
1313
Dampffilmvapor film
1414
anströmseitiger Bereichon the upstream side
1515
abströmseitiger Bereichdownstream area
1616
HochdruckleitschaufelHochdruckleitschaufel
1717
HochdrucklaufschaufelreiheHigh pressure blade row
1818
HochdrucklaufschaufelHigh pressure blade
1919
WärmestauelementeHeat storage elements
2020
HochdruckverdichterHigh-pressure compressors
2121
Eintrittentry
2222
HochdruckleitschaufelreiheHochdruckleitschaufelreihe
2323
zweiter Kühlkanal second cooling channel
2424
erster Kühlkanalfirst cooling channel
2525
dritter Kühlkanalthird cooling channel
2626
vierter Kühlkanalfourth cooling channel
2727
Austrittsöffnungoutlet opening
2828
HeißgasstromHot gas stream
2929
AußendeckplatteOuter cover plate
3030
Zwischenraumgap
3131
LuftkühleinrichtungAir cooling device
3232
DampfkühleinrichtungSteam cooling device
DD
Dampfsteam
LL
Luftair

Claims (11)

Gasturbine (1), insbesondere in einer Kraftwerksanlage, mit wenigstens einer Brennkammer (2) und mit einer die Brennkammer (2) umgebenden innenliegenden Innenverkleidung (3) und mit einer innenliegenden Außenverkleidung (4), mit einem Stator (5), welcher mindestens eine Leitschaufelreihe (6) mit mehreren Leitschaufeln (7) aufweist, mit einem Rotor (8), welcher mindestens eine Laufschaufelreihe (9) mit mehreren Laufschaufeln (10) aufweist, mit einer Luftkühleinrichtung (31), welche zur Kühlung von Teilen der Gasturbine (1) mittels Luft (L) ausgebildet ist, wobei zusätzlich eine Dampfkühleinrichtung (32) vorgesehen ist, welche zur Kühlung von Teilen der Gasturbine (1) mittels Dampf (D) ausgebildet ist. Gas turbine (1), in particular in a power plant, with at least one combustion chamber (2) and with an inner lining (3) surrounding the combustion chamber (2) and with an inner outer lining (4), with a stator (5) which has at least one row of guide vanes (6) with a plurality of guide vanes (7), a rotor (8) having at least one blade row (9) with a plurality of blades (10), with an air-cooling device (31), which is designed to cool parts of the gas turbine (1) by means of air (L), wherein additionally a steam cooling device (32) is provided which is designed to cool parts of the gas turbine (1) by means of steam (D). Gasturbine, nach Anspruch 1,
dadurch gekennzeichnet, dass die Dampfkühleinrichtung (32) zumindest zur Kühlung der innenliegenden Innenverkleidung (3) und/oder der innenliegenden Außenverkleidung (4) und/oder der Leitschaufeln (7) und/oder nabenseitiger Abdeckelemente (11) der Leitschaufeln (7) ausgebildet ist, und/oder dass eine Dampfführung so ausgebildet ist, dass ab der Leitschaufelreihe (6) entlang eines Rotormantels (12) ein Dampffilm (13) entsteht. Gas turbine, according to claim 1,
characterized, that the steam cooling means (32) is formed at least for cooling the inner liner (3) and / or the inside outer panel (4) and / or of the guide vanes (7) and / or hub side cover elements (11) of the guide vanes (7), and / or a steam guide is formed in such a way that a vapor film (13) arises from the row of guide blades (6) along a rotor shell (12). Gasturbine, nach Anspruch 1 oder 2,
dadurch gekennzeichnet, dass die Luftkühleinrichtung (31) zumindest zur Kühlung der Laufschaufeln (10) und/oder von stromab der Leitschaufelreihe (6) angeordneten Wärmestauelementen (19) ausgebildet ist.Gas turbine according to claim 1 or 2,
characterized in that the air cooling device (31) is designed at least for cooling the rotor blades (10) and / or from downstream of the guide blade row (6) arranged heat accumulation elements (19). Gasturbine nach einem der Ansprüche 1 bis 3,
dadurch gekennzeichnet, dass die Dampfkühleinrichtung (32) zur Kühlung der Leitschaufeln (7) in einem anströmseitigen Bereich (14) und die Luftkühleinrichtung (31) zur Kühlung der Leitschaufeln (7) in einem abströmseitigen Bereich (15) ausgebildet sind.Gas turbine according to one of claims 1 to 3,
characterized in that the steam cooling device (32) for cooling the guide vanes (7) in an upstream region (14) and the air cooling device (31) for cooling the guide vanes (7) in a downstream region (15) are formed. Gasturbine nach einem der Ansprüche 1 bis 4,
dadurch gekennzeichnet, dass die Gasturbine (1 ) zur Durchführung einer sequentieller Verbrennung ausgebildet ist, dass zusätzlich eine Hochdruckbrennkammer (2') vorgesehen ist, die mit einer diese umgebenden innenliegenden Innenverkleidung (3) und einer innenliegenden Außenverkleidung (4) versehen ist, dass mindestens eine Hochdruckleitschaufelreihe (22) mit mehreren Hochdruckleitschaufeln (16) vorgesehen ist, dass mindestens eine Hochdrucklaufschaufelreihe (17) mit mehreren Hochdrucklaufschaufeln (18) vorgesehen ist. Gas turbine according to one of claims 1 to 4,
characterized, in that the gas turbine (1) is designed to carry out a sequential combustion, in that a high-pressure combustion chamber (2 ') is additionally provided, which is provided with a surrounding inner lining (3) and an inner outer lining (4) surrounding it, that is provided with a plurality of Hochdruckleitschaufeln (16) at least one Hochdruckleitschaufelreihe (22) in that at least one high-pressure blade row (17) with a plurality of high-pressure blades (18) is provided. Gasturbine, nach Anspruch 5,
dadurch gekennzeichnet, dass die Dampfkühleinrichtung (32) zumindest zur Kühlung der Hochdruckleitschaufeln (16) und/oder nabenseitiger Abdeckelemente (11) der Hochdruckleitschaufeln (16) und/oder der Hochdrucklaufschaufeln (18) ausgebildet ist, und/oder dass eine Dampfführung so ausgebildet ist, dass ab der Hochdruckleitschaufelreihe (22) entlang eines Rotormantels (12) ein Dampffilm (13) entsteht. Gas turbine, according to claim 5,
characterized, that the steam cooling means (32) at least for cooling the Hochdruckleitschaufeln (16) and / or hub side cover elements (11) of the Hochdruckleitschaufeln (16) and / or the high-pressure moving blades is formed (18), and / or a steam guide is formed such that a vapor film (13) arises from the high-pressure guide blade row (22) along a rotor shell (12). Gasturbine, nach Anspruch 5 oder 6,
dadurch gekennzeichnet, dass die Luftkühleinrichtung (31) zumindest zur Kühlung der innenliegenden Innenverkleidung (3) der Hochdruckbrennkammer (2') und/oder der innenliegenden Außenverkleidung (4) der Hochdruckbrennkammer (2') und/oder der Hinterkante der Hochdruckleitschaufeln (16) und/oder von stromab der Hochdruckleitschaufelreihe (22) angeordneten Wärmestauelementen (19) ausgebildet ist.Gas turbine according to claim 5 or 6,
characterized in that the air cooling device (31) at least for cooling the inner lining (3) of the high pressure combustion chamber (2 ') and / or the inner outer lining (4) of the high pressure combustion chamber (2') and / or the trailing edge of the Hochdruckleitschaufeln (16) and / or from the high pressure vane row (22) arranged heat accumulation elements (19) is formed. Gasturbine, nach einem der Ansprüche 5 bis 7,
dadurch gekennzeichnet, dass die Dampfkühleinrichtung (32) zumindest zur teilweisen Kühlung eines Hochdruckverdichters (20) ausgebildet ist.Gas turbine according to one of claims 5 to 7,
characterized in that the steam cooling device (32) is designed at least for partial cooling of a high-pressure compressor (20). Gasturbine nach einem der Ansprüche 5 bis 8,
dadurch gekennzeichnet, dass die Dampfkühleinrichtung (32) zur Entnahme von Dampf (D) mit einem Abhitzekessel einer Dampfturbine verbunden ist, die mit der Gasturbine (1) gekoppelt ist.Gas turbine according to one of claims 5 to 8,
characterized in that the steam cooling device (32) for removing steam (D) is connected to a waste heat boiler of a steam turbine, which is coupled to the gas turbine (1). Verfahren zum Kühlen einer Gasturbine (1), insbesondere in einer Kraftwerksanlage, umfassend eine Brennkammer (2), mit einer die Brennkammer (2) umgebenden innenliegenden Innenverkleidung (3) und mit einer innenliegenden Außenverkleidung (4), einen Stator (5), welcher mindestens eine Leitschaufelreihe (6) mit mehreren Leitschaufeln (7) aufweist, einen Rotor (8), welcher mindestens eine Laufschaufelreihe (9) mit mehreren Laufschaufeln (10) aufweist, bei dem Teile der Gasturbine (1) mittels einer Luftkühleinrichtung (31) mit Luft (L) gekühlt werden, während andere Teile der Gasturbine (1) mittels einer Dampfkühleinrichtung (32) mit Dampf (D) gekühlt werden. Method for cooling a gas turbine (1), in particular in a power plant, comprising a combustion chamber (2) with an inner lining (3) surrounding the combustion chamber (2) and with an inner outer lining (4), a stator (5) which has at least one row of guide vanes (6) with a plurality of guide vanes (7), a rotor (8) having at least one blade row (9) with a plurality of blades (10), in which parts of the gas turbine (1) are cooled by air (L) by means of an air-cooling device (31), while other parts of the gas turbine (1) are cooled by steam (D) by means of a steam-cooling device (32). Verfahren nach Anspruch 10,
gekennzeichnet durch,
die kennzeichnenden Merkmale wenigstens eines der Ansprüche 2 bis 9.Method according to claim 10,
characterized by
the characterizing features of at least one of claims 2 to 9.
EP04103627.8A 2003-08-08 2004-07-28 Gas turbine and associated cooling method Not-in-force EP1505254B1 (en)

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Also Published As

Publication number Publication date
EP1505254B1 (en) 2017-01-25
US7040097B2 (en) 2006-05-09
EP1505254A3 (en) 2012-07-04
US20050172634A1 (en) 2005-08-11
DE10336432A1 (en) 2005-03-10
CN100507237C (en) 2009-07-01
CN1580520A (en) 2005-02-16

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