EP1436491A1 - Method for conditioning a compressor airflow and device therefor - Google Patents

Method for conditioning a compressor airflow and device therefor

Info

Publication number
EP1436491A1
EP1436491A1 EP02765281A EP02765281A EP1436491A1 EP 1436491 A1 EP1436491 A1 EP 1436491A1 EP 02765281 A EP02765281 A EP 02765281A EP 02765281 A EP02765281 A EP 02765281A EP 1436491 A1 EP1436491 A1 EP 1436491A1
Authority
EP
European Patent Office
Prior art keywords
stator
stream
water
outlet
axial compressor
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP02765281A
Other languages
German (de)
French (fr)
Inventor
Hans Ulrich Frutschi
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1436491A1 publication Critical patent/EP1436491A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
    • F02C7/143—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages
    • F02C7/1435—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages by water injection
    • 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
    • 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

Definitions

  • the present invention relates to the field of gas turbine technology. It relates to a method for conditioning a compressor air flow according to the preamble of claim 1 and a device for carrying out the method.
  • An axial compressor 1 as is shown schematically in the single figure, comprises a rotor 2 rotatable about an axis 9, a stator 3, and a plurality of blade rings, which are alternately made up of runner fastened to the rotor 2. blades 4 and fixed to the stator 3 guide vanes 5. For the sake of simplicity, only one blade of a blade ring is shown in the figure.
  • the axial compressor 1 sucks in air at an inlet, which is compressed in the flow channel formed between the rotor 2 and the inner wall of the stator 3 and exits at an outlet 10 under increased pressure. If the axial compressor is part of a gas turbine system, the compressed air emerging at the outlet 10 is fed to a subsequent combustion chamber and used there for the combustion of a fuel. The resulting hot gases are then expanded in a subsequent gas turbine with work performed.
  • the air stream sucked in at the inlet 11 can be divided into two streams, namely a main stream A, which flows in the middle of the flow channel, and an edge stream B, which flows along the inner wall of the stator 3. If air is now taken from an outlet 6 located between inlet 11 and outlet 10 for cooling purposes, this air essentially comes from the marginal stream B, while the main stream A is further compressed behind the outlet 6.
  • the polytropic efficiency of the axial compressor 1 is not constant over the radial extent of the rotor and guide blades 4 and 5.
  • the central air flow is compressed with a higher degree of efficiency than the current paths lying on the rotor 2 and on the inner wall of the stator 3.
  • the (branched off) air removed at outlet 6 therefore has a significantly higher temperature than the air at location 7 in the central stream.
  • the object is achieved by the entirety of the features of claims 1 and 4.
  • the essence of the invention is to introduce water into the boundary stream between the inlet and the outlet, which water evaporates while the boundary stream is cooling. As a result, the marginal flow that is later used as cooling air is cooled in a simple manner, without the other functions of the compressor being influenced thereby.
  • the water is introduced into the axial compressor such that it forms a thin film of water on the inner wall of the stator.
  • the water is injected into the marginal stream through a plurality of nozzles distributed over the circumference of the stator.
  • a preferred embodiment of the device according to the invention is characterized in that the means for introducing the water comprise a plurality of nozzles which are arranged distributed around the circumference of the stator.
  • the invention will be explained in more detail below on the basis of exemplary embodiments in connection with the drawing.
  • the single figure shows a schematic representation of a preferred embodiment of the axial compressor according to the invention.
  • water H 2 O
  • the water supplied via the nozzles 8 forms a thin water film on the inner wall of the stator 3 due to the air flow in the flow channel. This water film is in contact with the boundary stream B and evaporates while the boundary stream B is cooling. The cooled boundary stream B is then at the outlet 6 Cooling air is available for the subsequent gas turbine.
  • the nozzles 8 are preferably arranged between adjacent rotor blades 4 and guide blades 5, so that the water film can form well.
  • the cooling effect of the evaporating water film is at a maximum if the nozzles 8 are furthermore arranged in the flow direction just behind the inlet 11 of the axial compressor 1.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention concerns a method for conditioning a compressor airflow (A, B) whereby an airflow (A, B) is sucked at an inlet (11) of an axial compressor (1) comprising, axially arranged a central rotor (2) and a stator (3) enclosing the rotor (2), and compressed on the path conveying said airflow towards the outlet (10). The sucked airflow (A, B) consists of a main flow (A) and a marginal flow (B) adjacent to the inner wall of the stator (3), and an exhaust orifice (6) located before the outlet (10) in the forward direction of flow enables the tapping of the marginal flow (B) to be used as cooling air. The temperature of the cooling air is simply and efficiently lowered by introducing water in the marginal flow (B) between the inlet (11) and the exhaust orifice (6), said water being evaporated when the marginal flow (B) is being cooled.

Description

BESCHREIBUNG DESCRIPTION
VERFAHREN ZUR KONDITIONIERUNG EINES VERDICHTERLUFTSTROMES SOWIE VORRICHTUNG ZUR DURCHFÜHRUNG DES VERFAHRENSMETHOD FOR CONDITIONING A COMPRESSOR AIRFLOW AND DEVICE FOR IMPLEMENTING THE METHOD
TECHNISCHES GEBIETTECHNICAL AREA
Die vorliegende Erfindung bezieht sich auf das Gebiet der Gasturbinentechnik. Sie betrifft ein Verfahren zur Konditionierung eines Verdichterluftstromes gemäss dem Oberbegriff des Anspruchs 1 sowie eine Vorrichtung zur Durchführung des Verfah- rens.The present invention relates to the field of gas turbine technology. It relates to a method for conditioning a compressor air flow according to the preamble of claim 1 and a device for carrying out the method.
STAND DER TECHNIKSTATE OF THE ART
Ein Axialverdichter 1 , wie er in der einzigen Figur schematisch dargestellt ist, umfasst einen um eine Achse 9 drehbaren Rotor 2, einen Stator 3, sowie eine Mehrzahl von Schaufelkränzen, die abwechselnd aus am Rotor 2 befestigten Lauf- schaufeln 4 und am Stator 3 befestigten Leitschaufeln 5 bestehen. Der Einfachheit halber ist in der Figur nur jeweils eine Schaufel eines Schaufelkranzes dargestellt.An axial compressor 1, as is shown schematically in the single figure, comprises a rotor 2 rotatable about an axis 9, a stator 3, and a plurality of blade rings, which are alternately made up of runner fastened to the rotor 2. blades 4 and fixed to the stator 3 guide vanes 5. For the sake of simplicity, only one blade of a blade ring is shown in the figure.
Der Axialverdichter 1 saugt an einem Eingang Luft an, die in dem zwischen Rotor 2 und Innenwand des Stators 3 gebildeten Strömungskanal verdichtet wird und unter erhöhtem Druck an einem Ausgang 10 austritt. Ist der Axialverdichter Teil einer Gasturbinenanlage, wird die am Ausgang 10 austretende verdichtete Luft einer nachfolgenden Brennkammer zugeführt und dort zur Verbrennung eines Brennstoffes verwendet. Die entstehenden heissen Gase werden dann in einer nachfolgenden Gasturbine unter Arbeitsleistung entspannt.The axial compressor 1 sucks in air at an inlet, which is compressed in the flow channel formed between the rotor 2 and the inner wall of the stator 3 and exits at an outlet 10 under increased pressure. If the axial compressor is part of a gas turbine system, the compressed air emerging at the outlet 10 is fed to a subsequent combustion chamber and used there for the combustion of a fuel. The resulting hot gases are then expanded in a subsequent gas turbine with work performed.
Der am Eingang 11 angesaugte Luftstrom kann in zwei Ströme unterteilt werden, nämlich einen Hauptstrom A, der in der Mitte des Strömungskanals strömt, und einen Randstrom B, der an der Innenwand des Stators 3 entlangströmt. Wird nun zu Kühlungszwecken an einem zwischen Eingang 11 und Ausgang 10 befindlichen Auslass 6 Luft entnommen, entstammt diese Luft im wesentlichen dem Randstrom B, während der Hauptstrom A hinter dem Auslass 6 weiterverdichtet wird.The air stream sucked in at the inlet 11 can be divided into two streams, namely a main stream A, which flows in the middle of the flow channel, and an edge stream B, which flows along the inner wall of the stator 3. If air is now taken from an outlet 6 located between inlet 11 and outlet 10 for cooling purposes, this air essentially comes from the marginal stream B, while the main stream A is further compressed behind the outlet 6.
Der polytrope Wirkungsgrad des Axialverdichters 1 ist über der radialen Erstreckung der Lauf- und Leitschaufeln 4 bzw. 5 nicht konstant. Der zentrale Luftstrom wird mit einem besseren Wirkungsgrad verdichtet als die am Rotor 2 und an der Innenwand des Stators 3 anliegenden Strombahnen. Die am Auslass 6 entnommene (abgezweigte) Luft weist daher eine wesentlich höhere Temperatur auf als die Luft am Ort 7 im zentralen Strom.The polytropic efficiency of the axial compressor 1 is not constant over the radial extent of the rotor and guide blades 4 and 5. The central air flow is compressed with a higher degree of efficiency than the current paths lying on the rotor 2 and on the inner wall of the stator 3. The (branched off) air removed at outlet 6 therefore has a significantly higher temperature than the air at location 7 in the central stream.
Für den Fall, dass die am Auslass 6 entnommene Luftmenge als Kühlluft einer Gasturbine dienen soll, ist diese Temperaturüberhöhung von Nachteil. Anstatt einfach eine Nachkühlung dieses Luftstromes (B) vorzunehmen, die meistens ei- nen Verlust an Wirkungsgrad der Gasturbinenanlage nach sich zieht, weil mehr Brennstoff erforderlich ist, wäre es wünschenswert, nicht nur die Temperaturüber- höhung während der Verdichtung zu verhindern, sondern sogar eine Temperaturabsenkung des Randstromes B zu erreichen.In the event that the amount of air removed at outlet 6 is to serve as cooling air for a gas turbine, this temperature increase is disadvantageous. Instead of simply post-cooling this air flow (B), which usually results in a loss in the efficiency of the gas turbine system because more fuel is required, it would be desirable not only to To prevent increase during compression, but even to achieve a temperature decrease in the marginal flow B.
DARSTELLUNG DER ERFINDUNGPRESENTATION OF THE INVENTION
Es ist Aufgabe der Erfindung, ein Verfahren zur Konditionierung eines Verdichterluftstromes zu schaffen, welches die Nachteile bekannter Verfahren vermeidet und auf einfache und wirkungsvolle Weise eine Reduzierung der Temperatur des ver- dichteten Randstromes am Auslass ermöglicht, sowie eine Vorrichtung zur Durchführung des Verfahrens anzugeben.It is an object of the invention to provide a method for conditioning a compressor air flow which avoids the disadvantages of known methods and enables the temperature of the compressed edge flow at the outlet to be reduced in a simple and effective manner, and to provide a device for carrying out the method.
Die Aufgabe wird durch die Gesamtheit der Merkmale der Ansprüche'1 und 4 gelöst. Der Kern der Erfindung besteht darin, zwischen dem Eingang und dem Aus- lass Wasser in den Randstrom einzubringen, welches unter Abkühlung des Randstromes verdampft. Hierdurch wird auf einfache Weise der später als Kühlluft verwendete Randstrom abgekühlt, ohne dass die übrigen Funktionen des Verdichters davon beeinflusst werden.The object is achieved by the entirety of the features of claims 1 and 4. The essence of the invention is to introduce water into the boundary stream between the inlet and the outlet, which water evaporates while the boundary stream is cooling. As a result, the marginal flow that is later used as cooling air is cooled in a simple manner, without the other functions of the compressor being influenced thereby.
Bevorzugt wird dies dadurch erreicht, dass das Wasser so in den Axialverdichter eingebracht wird, dass es an der Innenwand des Stators einen dünnen Wasserfilm bildet. Insbesondere wird das Wasser durch mehrere über den Umfang am Stator verteilt angeordnete Düsen in den Randstrom eingedüst.This is preferably achieved in that the water is introduced into the axial compressor such that it forms a thin film of water on the inner wall of the stator. In particular, the water is injected into the marginal stream through a plurality of nozzles distributed over the circumference of the stator.
Eine bevorzugte Ausgestaltung der Vorrichtung nach der Erfindung zeichnet sich dadurch aus, dass die Mittel zum Einbringen des Wassers mehrere Düsen umfassen, welche am Umfang des Stators verteilt angeordnet sind.A preferred embodiment of the device according to the invention is characterized in that the means for introducing the water comprise a plurality of nozzles which are arranged distributed around the circumference of the stator.
Weitere Ausgestaltungen ergeben sich aus den abhängigen Ansprüchen. KURZE ERLÄUTERUNG DER FIGURENFurther configurations result from the dependent claims. BRIEF EXPLANATION OF THE FIGURES
Die Erfindung soll nachfolgend anhand von Ausführungsbeispielen im Zusammenhang mit der Zeichnung näher erläutert werden. Die einzige Figur zeigt eine schematisierte Darstellung eines bevorzugten Ausführungsbeispiels des erfin- dungsgemässen Axialverdichters.The invention will be explained in more detail below on the basis of exemplary embodiments in connection with the drawing. The single figure shows a schematic representation of a preferred embodiment of the axial compressor according to the invention.
WEGE ZUR AUSFÜHRUNG DER ERFINDUNGWAYS OF CARRYING OUT THE INVENTION
Wesentliche Teile und Funktionen des in der Figur dargestellten Axialverdichters sind bereits im Zusammenhang mit der Erläuterung des Standes der Technik beschrieben worden. Gemäss einem bevorzugten Ausführungsbeispiel der Erfindung wird nun beim Axialverdichter 1 über mehrere am Umfang des Stators 3 angeord- nete Düsen 8 Wasser (H20) in den Strömungskanal zwischen Rotor 2 und Stator 3 zugeführt. Das über die Düsen 8 zugeführte Wasser bildet aufgrund der Luftströmung im Strömungskanal einen dünnen Wasserfilm auf der Innenwand des Stators 3. Dieser Wasserfilm steht in Kontakt mit dem Randstrom B und verdampft unter Abkühlung des Randstroms B. Am Auslass 6 steht dann der abgekühlte Randstrom B als Kühlluft für die nachfolgende Gasturbine zur Verfügung.Essential parts and functions of the axial compressor shown in the figure have already been described in connection with the explanation of the prior art. According to a preferred exemplary embodiment of the invention, water (H 2 O) is now fed into the flow channel between the rotor 2 and the stator 3 in the axial compressor 1 via a plurality of nozzles 8 arranged on the circumference of the stator 3. The water supplied via the nozzles 8 forms a thin water film on the inner wall of the stator 3 due to the air flow in the flow channel. This water film is in contact with the boundary stream B and evaporates while the boundary stream B is cooling. The cooled boundary stream B is then at the outlet 6 Cooling air is available for the subsequent gas turbine.
Bevorzugt sind die Düsen 8 zwischen benachbarten Laufschaufeln 4 und Leitschaufeln 5 angeordnet, damit sich der Wasserfilm gut ausbilden kann. Die Kühlwirkung des verdampfenden Wasserfilms ist maximal, wenn die Düsen 8 darüber hinaus in Strömungsrichtung kurz hinter dem Eingang 11 des Axialverdichters 1 angeordnet sind.The nozzles 8 are preferably arranged between adjacent rotor blades 4 and guide blades 5, so that the water film can form well. The cooling effect of the evaporating water film is at a maximum if the nozzles 8 are furthermore arranged in the flow direction just behind the inlet 11 of the axial compressor 1.
BEZUGSZEICHENLISTELIST OF REFERENCE NUMBERS
1 Axialverdichter1 axial compressor
2 Rotor2 rotor
3 Stator 4 Laufschaufel3 stator 4 moving blades
5 Leitschaufel5 guide vane
6 Auslass6 outlet
7 Ort (Hauptstrom)7 place (main stream)
8 Düse8 nozzle
9 Achse9 axis
10 Ausgang10 exit
11 Eingang11 entrance
A HauptstromA main current
B Randstrom (Kühlluftstrom) B edge flow (cooling air flow)

Claims

PATENTANSPRÜCHE
1. Verfahren zur Konditionierung eines Verdichterluftstromes (A, B), bei welchem Verfahren in einem Axialverdichter (1 ), der in einer koaxialen Anordnung einen zentralen Rotor (2) und einen den Rotor (2) umgebenden Stator (3) umfasst, ein Luftstrom (A, B) an einem Eingang (11 ) angesaugt und auf dem Weg zu einem Ausgang (10) verdichtet wird, wobei sich der angesaugte Luftstrom (A, B) aus einem Hauptstrom (A) und einem an der Innenwand des Stators (3) anliegenden Randstrom (B) zusammensetzt, und an einem in Strömungsrichtung vor dem Ausgang (10) liegenden Auslass (6) Luft aus dem Randstrom (B) zur Verwendung als Kühlluft entnommen wird, dadurch gekennzeichnet, dass zwischen dem Eingang (11 ) und dem Auslass (6) Wasser in den Randstrom (B) eingebracht wird, welches unter Abkühlung des Randstromes (B) verdampft.1. A method for conditioning a compressor air flow (A, B), in which method an air flow in an axial compressor (1) which, in a coaxial arrangement, comprises a central rotor (2) and a stator (3) surrounding the rotor (2) (A, B) is sucked in at an inlet (11) and compressed on the way to an outlet (10), the suctioned air stream (A, B) being composed of a main stream (A) and one on the inner wall of the stator (3 ) adjoining edge stream (B), and at an outlet (6) lying in the flow direction before the outlet (10), air is removed from the edge stream (B) for use as cooling air, characterized in that between the inlet (11) and the Outlet (6) water is introduced into the marginal stream (B), which evaporates while cooling the marginal stream (B).
2. Verfahren nach Anspruch 1 , dadurch gekennzeichnet, dass das Wasser so in den Axialverdichter (1 ) eingebracht wird, dass es an der Innenwand des Stators (3) einen dünnen Wasserfilm bildet.2. The method according to claim 1, characterized in that the water is introduced into the axial compressor (1) in such a way that it forms a thin film of water on the inner wall of the stator (3).
3. Verfahren nach Anspruch 2, dadurch gekennzeichnet, dass das Wasser durch mehrere über den Umfang am Stator (3) verteilt angeordnete Düsen (8) in den Randstrom (B) eingedüst wird.3. The method according to claim 2, characterized in that the water is injected through a plurality of nozzles (8) distributed over the circumference on the stator (3) into the marginal stream (B).
4. Vorrichtung zur Durchführung des Verfahrens nach Anspruch 1 , dadurch gekennzeichnet, dass am Stator (3) des Axialverdichters (1 ) Mittel (8) zum Einbringen des Wassers in den Randstrom (B) vorgesehen sind.4. A device for performing the method according to claim 1, characterized in that means (8) for introducing the water into the marginal stream (B) are provided on the stator (3) of the axial compressor (1).
5. Vorrichtung nach Anspruch 4, dadurch gekennzeichnet, dass die Mittel zum Einbringen des Wassers mehrere Düsen (8) umfassen, welche am Umfang des Stators (3) verteilt angeordnet sind. 5. The device according to claim 4, characterized in that the means for introducing the water comprise a plurality of nozzles (8) which are arranged distributed on the circumference of the stator (3).
6. Vorrichtung nach Anspruch 5, dadurch gekennzeichnet, dass der Axialverdichter (1 ) eine Beschaufelung aufweist, welche in abwechselnder Anordnung Laufschaufeln (4) und Leitschaufeln (5) aufweist, und dass die Düsen (8) zwischen benachbarten Laufschaufeln (4) und Leitschaufeln (5) angeordnet sind.6. The device according to claim 5, characterized in that the axial compressor (1) has a blading, which has rotor blades (4) and guide vanes (5) in an alternating arrangement, and that the nozzles (8) between adjacent rotor blades (4) and guide vanes (5) are arranged.
7. Vorrichtung nach einem der Ansprüche 5 oder 6, dadurch gekennzeichnet, dass die Düsen (8) in Strömungsrichtung kurz hinter dem Eingang (11 ) des Axialverdichters (1 ) angeordnet sind. 7. Device according to one of claims 5 or 6, characterized in that the nozzles (8) are arranged in the flow direction just behind the input (11) of the axial compressor (1).
EP02765281A 2001-10-17 2002-10-02 Method for conditioning a compressor airflow and device therefor Withdrawn EP1436491A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
CH190901 2001-10-17
CH19092001 2001-10-17
PCT/IB2002/004068 WO2003033890A1 (en) 2001-10-17 2002-10-02 Method for conditioning a compressor airflow and device therefor

Publications (1)

Publication Number Publication Date
EP1436491A1 true EP1436491A1 (en) 2004-07-14

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ID=4566747

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02765281A Withdrawn EP1436491A1 (en) 2001-10-17 2002-10-02 Method for conditioning a compressor airflow and device therefor

Country Status (3)

Country Link
EP (1) EP1436491A1 (en)
CN (1) CN1701168A (en)
WO (1) WO2003033890A1 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP6010348B2 (en) 2012-06-01 2016-10-19 三菱日立パワーシステムズ株式会社 Axial flow compressor and gas turbine provided with the same
CN113266533A (en) * 2021-06-02 2021-08-17 安徽三联学院 Aerogenerator gear box with heat radiation structure

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Publication number Priority date Publication date Assignee Title
IT454098A (en) * 1948-02-27
DE4442936A1 (en) * 1994-12-02 1996-06-05 Abb Patent Gmbh Operating stationary gas turbine installation for silo combustion chamber
EP0903483A1 (en) * 1997-09-17 1999-03-24 Romabau AG Method and device for cooling a gas flow in a gas turbine
US6467252B1 (en) * 1998-07-24 2002-10-22 General Electric Company Nozzles for water injection in a turbine engine
DE19900026B4 (en) * 1999-01-02 2016-01-21 Alstom Technology Ltd. Gas turbine with steam injection
DE10027842A1 (en) * 2000-06-05 2001-12-20 Alstom Power Nv Gas turbine layout cooling system bleeds portion of film cooling air through turbine blade via inlet or outlet edge borings for direct blade wall service.

Non-Patent Citations (1)

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Title
See references of WO03033890A1 *

Also Published As

Publication number Publication date
CN1701168A (en) 2005-11-23
WO2003033890A1 (en) 2003-04-24

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