EP2260180A2 - Guide vane for a gas turbine - Google Patents

Guide vane for a gas turbine

Info

Publication number
EP2260180A2
EP2260180A2 EP09726037A EP09726037A EP2260180A2 EP 2260180 A2 EP2260180 A2 EP 2260180A2 EP 09726037 A EP09726037 A EP 09726037A EP 09726037 A EP09726037 A EP 09726037A EP 2260180 A2 EP2260180 A2 EP 2260180A2
Authority
EP
European Patent Office
Prior art keywords
gas turbine
airfoil
guide vane
vane
cooling
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
EP09726037A
Other languages
German (de)
French (fr)
Other versions
EP2260180B1 (en
Inventor
Willy Heinz Hofmann
Roland DÜCKERSHOFF
Brian Kenneth Wardle
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.)
Ansaldo Energia IP UK Ltd
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 EP2260180A2 publication Critical patent/EP2260180A2/en
Application granted granted Critical
Publication of EP2260180B1 publication Critical patent/EP2260180B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F01D5/187—Convection cooling
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3215—Application in turbines in gas turbines for a special turbine stage the last stage of the turbine
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/301—Cross-sectional characteristics
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/185—Two-dimensional patterned serpentine-like
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • the present invention relates to the field of gas turbine technology. It relates to a guide vane for a gas turbine according to the preamble of claim 1. It also relates to a gas turbine equipped with such a vane.
  • Such a gas turbine which has become known in the art as GT24 / 26, for example, from an article by Joos, F. et al., "Field Experience of the Sequential Combustion System for the ABB GT24 / GT26 Gasturbine Famil /, IGTI / ASME 98-GT-220, 1998 Sweden.
  • the local Fig. 1 shows the basic structure of such a gas turbine, the local Fig. 1 in the present application as Fig. 1 is reproduced. Furthermore, such a gas turbine is known from EP-B1 -0 620 362.
  • FIG. 1 shows a gas turbine 10 with sequential combustion, in which along an axis 19 a compressor 11, a first combustion chamber 14, a high-pressure turbine (HDT) 15, a second combustion chamber 17 and a low-pressure turbine (NDT) 18 are arranged.
  • the compressor 11 and the two turbines 15, 18 are part of a rotor which rotates about the axis 19.
  • the compressor 11 sucks in air and compresses it.
  • the compressed air flows into a plenum, and from there into premix burners, where this air is mixed with at least one fuel, fuel supplied at least via the fuel feed 12.
  • premix burners are fundamentally apparent from EP-A1-0 321 809 or EP-A2-0 704 657.
  • the compressed air flows into the premix burners, where the mixing, as stated above, takes place with at least one fuel.
  • This fuel / air mixture then flows into the first combustion chamber 14, into which this mixture passes to form a stable flame front for combustion.
  • the hot gas thus provided is partially expanded in the subsequent high-pressure turbine 15 under working performance and then flows into the second combustion chamber 17, where a further fuel supply 16 takes place. Due to the high temperatures, which still has the hot gas partially released in the high-pressure turbine 15, combustion takes place in the second combustion chamber 17, which combustion is based on autoignition.
  • the hot gas reheated in the second combustion chamber 17 is then expanded in a multistage low-pressure turbine 18.
  • the low-pressure turbine 18 comprises a plurality of rows of blades and vanes arranged alternately in the flow direction, which are arranged alternately.
  • the guide vanes of the third row of guide vanes in the direction of flow are designated by the reference numeral 20 in FIG.
  • a gaseous cooling medium eg compressed air from the compressor of the gas turbine is shown or supplied with steam.
  • the cooling medium is sent through cooling channels formed in the blade (often in serpentines) and / or at different points of the blade through holes (holes, Slits) to form a cooling film on the outside of the blade (film cooling)
  • An example of such a cooled blade is described and illustrated in US-A-5,813,835.
  • the invention aims to remedy this situation.
  • the invention wants to suggest an improvement here. It is an object of the invention to provide a guide vane, which is able to maximize the service life and cooling, taking into account the casting conditions.
  • the object is solved by the entirety of the features of claim 1. It is essential for the invention that the airfoil has in the radial direction a cross-sectional area of the blade material which varies over the height of the airfoil. In this way, with regard to the used
  • the cross-sectional area of the blade material is understood to be the difference between the total cross-sectional area of the blade leaf and the cross-sectional area of the cooling passages.
  • the cross-sectional area of the blade material is a minimum, depending on the height of the blade.
  • the minimum cross-sectional area of the blade material is in the range between 20% and 40% of the total height of the airfoil.
  • Another embodiment of the guide vane according to the invention is characterized in that it has a curved shape in space, that arranged in the interior of the airfoil a number extending in the radial direction of cooling channels in the direction of the hot gas flow one behind the other and respectively at the ends of the airfoil.
  • the cooling channels arranged deflection are connected to each other, that the cooling medium flows through the cooling channels successively in alternating directions, and that the cooling channels in the radial direction of the curvature of the airfoil follow in space.
  • the gas turbine is a sequential combustion gas turbine having a first combustion chamber with a high pressure turbine downstream and a second combustion chamber with a downstream low pressure turbine with the nozzle disposed in the low pressure turbine. (See the above-mentioned Fig. 1).
  • the low-pressure turbine preferably has a plurality of rows of guide vanes one behind the other in the flow direction, wherein the guide vane according to the invention is arranged in a middle row of guide vanes.
  • Fig. 2 in a side view on the suction side a vane in the
  • FIG. 3 shows the longitudinal section through the vane according to FIG. 2.
  • Fig. 2 is a side outer view of a vane in the
  • the vane 20 includes a highly curved in air space blade 22 extending in the longitudinal direction (in the radial direction of the gas turbine) between a blade head 23 and a cover plate 21 and in the direction of
  • Hot gas stream 29 from a leading edge 27 to a trailing edge 28 extends. Between the two edges 27 and 28, the airfoil 22 is limited to the outside by a pressure side (in Fig. 2 on the side facing away from the viewer) and a suction side 26.
  • the vane 20 is secured by means of the formed on the top of the cover plate 21 hook-shaped fastening elements 24 and 25 on the turbine housing, while it rests sealingly with the blade head 23 on the rotor.
  • the inner structure of the vane 20 is shown in Fig. 3:
  • the airfoil is traversed in the longitudinal direction of three cooling channels 30, 31 and 32, which follow the curvature of the airfoil in space and arranged in the direction of the hot gas stream 29 in series and through at the ends of Airfoil arranged deflecting areas are interconnected so that the cooling medium flows through the cooling channels 30, 31, 32 successively in alternating directions.
  • the airfoil 22 with its inner cooling channels 30, 31, 32 is bounded outwardly by walls 33, 36, while the cooling channels 30, 31, 32 are delimited from each other by walls 34 and 35.
  • the total cross-sectional area of the walls 33, .., 36 in the radial direction, i. in the direction of the height h of the airfoil 22, results as a difference of the airfoil cross section and the cross section of the cooling channels 30, 31, 32. This area difference is the integral cross-sectional area of the blade material.
  • the cross-sectional area of the blade material over the height h varies, in particular, this cross-sectional area passes through a minimum.
  • the minimum of the cross-sectional area is preferably in the range between 20% and 40% of the height h of the airfoil 22 or in the range of 0.2h to 0.4h, as indicated in FIG. 3 by the dashed lines.
  • the shape of the blade profus is influenced in terms of cross-sectional area, wall thickness, chord length and cooling channel cross-section. With an appropriate distribution of these parameters over the blade height, the underlying requirements with respect to the life of the blade, the achievable cooling and the cooling air consumption are achieved.
  • the guide vanes according to the invention can be used in gas turbines with sequential combustion, in particular in the middle rows of guide vanes of the low-pressure turbine, which is connected downstream of the second combustion chamber.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention relates to a guide vane (20) for a gas turbine (10), in particular for a low-pressure turbine (18) of a gas turbine (10) with sequential combustion, comprising a vane (22) that extends in the radial direction between an inner platform (23) and an outer platform (21), extending in the inner cooling channel thereof (30, 31, 32), through which a cooling medium, in particular cooling air, for cooling the guide vane (20) can flow. In said type of guide vane, the desired service life and cooling, in relation to the used casting process is achieved such that the vane (22) comprises a transversal surface of the blade material in the radial direction, that varies about the height (h) of the vane (22).

Description

LEITSCHAUFEL FÜR EINE GASTURBINE GUIDE BUCKET FOR A GAS TURBINE
Technisches GebietTechnical area
Die vorliegende Erfindung bezieht sich auf das Gebiet der Gasturbinentechnik. Sie betrifft eine Leitschaufel für eine Gasturbine gemäss Oberbegriff des Anspruchs 1. Sie betrifft auch eine mit einer solchen Leitschaufel ausgestattete Gasturbine.The present invention relates to the field of gas turbine technology. It relates to a guide vane for a gas turbine according to the preamble of claim 1. It also relates to a gas turbine equipped with such a vane.
Stand der TechnikState of the art
Gasturbinen mit sequentieller Verbrennung sind bekannt und haben sich im industriellen Betrieb bewährt.Gas turbines with sequential combustion are known and have proven themselves in industrial operation.
Eine solche Gasturbine, welche in Fachkreisen als GT24/26 bekannt geworden ist, geht beispielsweise aus einem Aufsatz von Joos, F. et al.,„Field Experience of the Sequential Combustion System for the ABB GT24/GT26 Gasturbine Famil/, IGTI/ASME 98-GT-220, 1998 Stockholm. Die dortige Fig. 1 zeigt den grundsätzlichen Aufbau einer solchen Gasturbine, wobei die dortige Fig. 1 in der vorliegenden Anmeldung als Fig. 1 wiedergegeben ist. Des Weiteren geht eine solche Gasturbine aus EP-B1 -0 620 362 hervor.Such a gas turbine, which has become known in the art as GT24 / 26, for example, from an article by Joos, F. et al., "Field Experience of the Sequential Combustion System for the ABB GT24 / GT26 Gasturbine Famil /, IGTI / ASME 98-GT-220, 1998 Stockholm. The local Fig. 1 shows the basic structure of such a gas turbine, the local Fig. 1 in the present application as Fig. 1 is reproduced. Furthermore, such a gas turbine is known from EP-B1 -0 620 362.
Fig. 1 zeigt eine Gasturbine 10 mit sequentieller Verbrennung, bei der entlang einer Achse 19 ein Verdichter 11 , eine erste Brennkammer 14, eine Hochdruckturbine (HDT) 15, eine zweite Brennkammer 17 und eine Niederdruckturbine (NDT) 18 angeordnet sind. Der Verdichter 11 und die beiden Turbinen 15, 18 sind Teil eines Rotors, der um die Achse 19 dreht. Der Verdichter 11 saugt Luft an und verdichtet sie. Die verdichtete Luft strömt in ein Plenum ein, und von dort in Vormischbrenner, wo diese Luft mit mindestens einem Brennstoff, mindestens über die Brennstoffzufuhr 12 herangeführten Brennstoff vermischt wird. Solche Vormischbrenner gehen grundsätzlich aus EP-A1 -0 321 809 oder EP-A2-0 704 657 hervor. Die verdichtete Luft strömt in die Vormischbrenner, wo die Vermischung, wie oben ausgeführt, mit mindestens einem Brennstoff stattfindet. Dieses Brennstoff/Luft- Gemisch strömt dann in die erste Brennkammer 14 ein, in welche dieses Gemisch unter Bildung einer stabilen Flammenfront zur Verbrennung gelangt. Das so bereitgestellte Heissgas wird in der anschliessenden Hochdruckturbine 15 unter Arbeitsleistung teilweise entspannt und strömt sodann in die zweite Brennkammer 17 ein, wo eine weitere Brennstoffzufuhr 16 stattfindet. Durch die hohen Temperaturen, welche das in der Hochdruckturbine 15 teilentspannte Heissgas immer noch aufweist, findet in der zweiten Brennkammer 17 eine Verbrennung statt, welche auf Selbstzündung beruht. Das in der zweiten Brennkammer 17 nacherhitzte Heissgas wird dann in einer mehrstufigen Niederdruckturbine 18 entspannt.1 shows a gas turbine 10 with sequential combustion, in which along an axis 19 a compressor 11, a first combustion chamber 14, a high-pressure turbine (HDT) 15, a second combustion chamber 17 and a low-pressure turbine (NDT) 18 are arranged. The compressor 11 and the two turbines 15, 18 are part of a rotor which rotates about the axis 19. The compressor 11 sucks in air and compresses it. The compressed air flows into a plenum, and from there into premix burners, where this air is mixed with at least one fuel, fuel supplied at least via the fuel feed 12. Such premix burners are fundamentally apparent from EP-A1-0 321 809 or EP-A2-0 704 657. The compressed air flows into the premix burners, where the mixing, as stated above, takes place with at least one fuel. This fuel / air mixture then flows into the first combustion chamber 14, into which this mixture passes to form a stable flame front for combustion. The hot gas thus provided is partially expanded in the subsequent high-pressure turbine 15 under working performance and then flows into the second combustion chamber 17, where a further fuel supply 16 takes place. Due to the high temperatures, which still has the hot gas partially released in the high-pressure turbine 15, combustion takes place in the second combustion chamber 17, which combustion is based on autoignition. The hot gas reheated in the second combustion chamber 17 is then expanded in a multistage low-pressure turbine 18.
Die Niederdruckturbine 18 umfasst in Strömungsrichtung hintereinander angeordnet mehrere Reihen von Laufschaufeln und Leitschaufeln, die alternierend angeordnet sind. Die Leitschaufeln der in Strömungsrichtung dritten Leitschaufelreihe sind in Fig. 1 mit dem Bezugszeichen 20 versehen.The low-pressure turbine 18 comprises a plurality of rows of blades and vanes arranged alternately in the flow direction, which are arranged alternately. The guide vanes of the third row of guide vanes in the direction of flow are designated by the reference numeral 20 in FIG.
Bei den hohen vorherrschenden Heissgastemperaturen in Gasturbinen der neueren Generationen ist es unabdingbar geworden, die Leit- und Laufschaufeln der Turbine nachhaltig zu kühlen. Dazu wird ein gasförmiges Kühlmedium (z.B. verdichtete Luft vom Verdichter der Gasturbine abgezeigt oder Dampf zugeführt. Bei allen Fällen wird das Kühlmedium durch in der Schaufelgebildete (häufig in Serpentinen verlaufende) Kühlkanäle geschickt und/oder an verschiedenen Stellen der Schaufel durch entsprechende Öffnungen (Bohrungen, Schlitze) nach aussen geleitet, um insbesondere auf der Aussenseite der Schaufel einen kühlenden Film auszubilden (Filmkühlung). Ein Beispiel für eine derartige gekühlte Schaufel ist in der Druckschrift US-A-5, 813,835 beschrieben und dargestellt.With the high prevailing hot gas temperatures in gas turbines of the newer generations, it has become indispensable to sustainably cool the guide vanes and rotor blades of the turbine. For this purpose, a gaseous cooling medium (eg compressed air from the compressor of the gas turbine is shown or supplied with steam.) In all cases, the cooling medium is sent through cooling channels formed in the blade (often in serpentines) and / or at different points of the blade through holes (holes, Slits) to form a cooling film on the outside of the blade (film cooling) An example of such a cooled blade is described and illustrated in US-A-5,813,835.
Die Leitschaufeln 20 in der bekannten Gasturbine aus Fig. 1 sind als gekühlteThe vanes 20 in the known gas turbine of Fig. 1 are cooled
Schaufeln ausgebildet, die im Inneren in radialer Richtung verlaufende Kühlkanäle aufweisen, wie sie beispielsweise aus der Druckschrift WO-A1 -2006029983 bekannt geworden sind. Solche Leitschaufeln werden anhand eines hochtechnologischen Gussverfahrens hergestellt, wobei das Gussmaterial von beiden Seiten (Schaufelkopf und Deckplatte) der Gussform zugeführt wird. Wegen der vergleichsweise dünnen Wände des Schaufelblattes und der im Gussverfahren hergestellten Kanäle und Öffnungen für die Kühlluft hängt die Lebensdauer, der Kühlluftverbrauch sowie die erzielte Kühlwirkung stark von der beim Gussverfahren erzielbaren Präzision ab. Dies ist insbesondere dann der Fall, wenn solche Schaufeln noch eine ausgeprägte Krümmung im Raum aufweisen.Shovels formed, which have in the interior in the radial direction extending cooling channels, as they have become known for example from the publication WO-A1 -2006029983. Such vanes are based on a manufactured high-tech casting process, wherein the casting material from both sides (blade head and cover plate) is fed to the mold. Because of the comparatively thin walls of the airfoil and the channels and openings for the cooling air produced by the casting process, the service life, the cooling air consumption and the cooling effect achieved depend strongly on the precision achievable in the casting process. This is especially the case when such blades still have a pronounced curvature in space.
Darstellung der ErfindungPresentation of the invention
Hier will die Erfindung Abhilfe schaffen. Die Erfindung will hier eine Verbesserung vorschlagen. Es ist Aufgabe der Erfindung, eine Leitschaufel zu schaffen, die unter Berücksichtigung der gusstechnischen Gegebenheiten die Lebensdauer und Kühlung zu maximieren vermag.The invention aims to remedy this situation. The invention wants to suggest an improvement here. It is an object of the invention to provide a guide vane, which is able to maximize the service life and cooling, taking into account the casting conditions.
Die Aufgabe wird durch die Gesamtheit der Merkmale des Anspruchs 1 gelöst. Wesentlich für die Erfindung ist, dass das Schaufelblatt in radialer Richtung eine Querschnittsfläche des Schaufelmaterials aufweist, die über der Höhe des Schaufelblattes variiert. Hierdurch kann im Hinblick auf die eingesetzteThe object is solved by the entirety of the features of claim 1. It is essential for the invention that the airfoil has in the radial direction a cross-sectional area of the blade material which varies over the height of the airfoil. In this way, with regard to the used
Gusstechnik das Kühlverhalten und die Lebensdauer der Schaufel in gewünschter Weise beeinflusst werden. Unter der Querschnittsfläche des Schaufelmaterials wird dabei die Differenz aus der gesamten Querschnittsfläche des Schaufelblattes und der Querschnittsfläche der Kühlkanäle verstanden.Casting the cooling behavior and the life of the blade can be influenced in the desired manner. The cross-sectional area of the blade material is understood to be the difference between the total cross-sectional area of the blade leaf and the cross-sectional area of the cooling passages.
Gemäss einer Ausgestaltung der Erfindung geht die Querschnittsfläche des Schaufelmaterials in Abhängigkeit von der Höhe des Schaufelblattes durch ein Minimum.According to one embodiment of the invention, the cross-sectional area of the blade material is a minimum, depending on the height of the blade.
Insbesondere liegt die minimale Querschnittsfläche des Schaufelmaterials im Bereich zwischen 20% und 40% der gesamten Höhe des Schaufelblattes. Eine andere Ausgestaltung der Leitschaufel nach der Erfindung zeichnet sich dadurch aus, dass sie eine im Raum gekrümmte Form aufweist, dass im Inneren des Schaufelblatts eine Anzahl in radialer Richtung verlaufende Kühlkanäle in Richtung des Heissgasstromes hintereinander angeordnet und durch an den Enden des Schaufelblattes resp. der Kühlkanäle angeordnete Umlenkbereiche miteinander verbunden sind, dass das Kühlmedium die Kühlkanäle nacheinander in wechselnder Richtung durchströmt, und dass die Kühlkanäle in radialer Richtung der Krümmung des Schaufelblattes im Raum folgen.In particular, the minimum cross-sectional area of the blade material is in the range between 20% and 40% of the total height of the airfoil. Another embodiment of the guide vane according to the invention is characterized in that it has a curved shape in space, that arranged in the interior of the airfoil a number extending in the radial direction of cooling channels in the direction of the hot gas flow one behind the other and respectively at the ends of the airfoil. The cooling channels arranged deflection are connected to each other, that the cooling medium flows through the cooling channels successively in alternating directions, and that the cooling channels in the radial direction of the curvature of the airfoil follow in space.
Bevorzugt wird eine Gasturbine mit einer solchen erfindungsgemässenPreference is given to a gas turbine with such an inventive
Leitschaufel ausgestattet, wobei die Leitschaufel in einer Turbine der Gasturbine angeordnet ist.Fitted with guide vane, wherein the guide vane is arranged in a turbine of the gas turbine.
Insbesondere handelt es sich bei der Gasturbine um eine Gasturbine mit sequentieller Verbrennung, die eine erste Brennkammer mit einer nachgeschalteten Hochdruckturbine und eine zweite Brennkammer mit einer nachgeschalteten Niederdruckturbine aufweist, wobei die Leitschaufel in der Niederdruckturbine angeordnet ist. (Siehe hierzu die bereits oben angesprochene Fig. 1 ).In particular, the gas turbine is a sequential combustion gas turbine having a first combustion chamber with a high pressure turbine downstream and a second combustion chamber with a downstream low pressure turbine with the nozzle disposed in the low pressure turbine. (See the above-mentioned Fig. 1).
Bevorzugt weist die Niederdruckturbine in Strömungsrichtung hintereinander mehrere Reihen von Leitschaufeln auf, wobei die erfindungsgemässe Leitschaufel in einer mittleren Leitschaufelreihe angeordnet ist.The low-pressure turbine preferably has a plurality of rows of guide vanes one behind the other in the flow direction, wherein the guide vane according to the invention is arranged in a middle row of guide vanes.
Kurze Erläuterung der FigurenBrief explanation of the figures
Die Erfindung soll nachfolgend anhand von Ausführungsbeispielen im Zusammenhang mit der Zeichnung näher erläutert werden. Alle für das unmittelbare Verständnis der Erfindung nicht wesentlichen Merkmale sind fortgelassen worden. Gleiche Elemente sind in den verschiedenen Figuren mit den gleichen Bezugszeichen versehen. Die Strömungsrichtung der Medien ist mit Pfeilen angegeben. Es zeigen Fig. 1 den prinzipiellen Aufbau einer Gasturbine mit sequentiellerThe invention will be explained in more detail with reference to embodiments in conjunction with the drawings. All features not essential to the instant understanding of the invention have been omitted. The same elements are provided in the various figures with the same reference numerals. The flow direction of the media is indicated by arrows. Show it Fig. 1 shows the basic structure of a gas turbine with sequential
Verbrennung nach dem Stand der Technik,Combustion according to the prior art,
Fig. 2 in einer Seitenansicht auf der Saugseite eine Leitschaufel in derFig. 2 in a side view on the suction side a vane in the
Niederdruckturbine einer Gasturbine mit sequentieller Verbrennung nach Fig. 1 gemäss einem bevorzugten Ausführungsbeispiel der Erfindung undLow-pressure turbine of a gas turbine with sequential combustion of FIG. 1 according to a preferred embodiment of the invention and
Fig. 3 den Längsschnitt durch die Leitschaufel gemäss Fig. 2.3 shows the longitudinal section through the vane according to FIG. 2.
Wege zur Ausführung der ErfindungWays to carry out the invention
In Fig. 2 ist in einer seitlichen Aussenansicht eine Leitschaufel in derIn Fig. 2 is a side outer view of a vane in the
Niederdruckturbine einer Gasturbine mit sequentieller Verbrennung nach Fig. 1 gemäss einem bevorzugten Ausführungsbeispiel der Erfindung dargestellt. Die Leitschaufel 20 umfasst eine im Raum stark gekrümmtes Schaufelblatt 22, dass sich in Längsrichtung (in radialer Richtung der Gasturbine) zwischen einem Schaufelkopf 23 und einer Deckplatte 21 erstreckt und in Richtung desLow-pressure turbine of a gas turbine with sequential combustion of FIG. 1 according to a preferred embodiment of the invention shown. The vane 20 includes a highly curved in air space blade 22 extending in the longitudinal direction (in the radial direction of the gas turbine) between a blade head 23 and a cover plate 21 and in the direction of
Heissgasstromes 29 von einer Vorderkante 27 bis zu einer Hinterkante 28 reicht. Zwischen den beiden Kanten 27 und 28 ist das Schaufelblatt 22 nach aussen durch eine Druckseite (in Fig. 2 auf der dem Betrachter abgewandten Seite) und eine Saugseite 26 begrenzt. Die Leitschaufel 20 ist mittels der auf der Oberseite der Deckplatte 21 ausgebildeten hakenförmigen Befestigungselemente 24 und 25 am Turbinengehäuse befestigt, während sie mit dem Schaufelkopf 23 dichtend am Rotor anliegt.Hot gas stream 29 from a leading edge 27 to a trailing edge 28 extends. Between the two edges 27 and 28, the airfoil 22 is limited to the outside by a pressure side (in Fig. 2 on the side facing away from the viewer) and a suction side 26. The vane 20 is secured by means of the formed on the top of the cover plate 21 hook-shaped fastening elements 24 and 25 on the turbine housing, while it rests sealingly with the blade head 23 on the rotor.
Der innere Aufbau der Leitschaufel 20 ist in Fig. 3 dargestellt: Das Schaufelblatt wird in Längsrichtung von drei Kühlkanälen 30, 31 und 32 durchzogen, die der Krümmung des Schaufelblattes im Raum folgen und in Richtung des Heissgasstromes 29 hintereinander angeordnet und durch an den Enden des Schaufelblattes angeordnete Umlenkbereiche so miteinander verbunden sind, dass das Kühlmedium die Kühlkanäle 30, 31 , 32 nacheinander in wechselnder Richtung durchströmt.The inner structure of the vane 20 is shown in Fig. 3: The airfoil is traversed in the longitudinal direction of three cooling channels 30, 31 and 32, which follow the curvature of the airfoil in space and arranged in the direction of the hot gas stream 29 in series and through at the ends of Airfoil arranged deflecting areas are interconnected so that the cooling medium flows through the cooling channels 30, 31, 32 successively in alternating directions.
Das Schaufelblatt 22 mit seinen innen liegenden Kühlkanälen 30, 31 , 32 ist nach aussen durch Wände 33, 36 begrenzt, während die Kühlkanäle 30, 31 , 32 untereinander durch Wände 34 und 35 abgegrenzt sind. Die Gesamt- Querschnittsfläche der Wände 33, ..,36 in radialer Richtung, d.h. in Richtung der Höhe h des Schaufelblattes 22, ergibt sich als Differenz des Schaufelblatt- Querschnitts und des Querschnitts der Kühlkanäle 30, 31 , 32. Diese Flächendifferenz ist die integrale Querschnittsfläche des Schaufelmaterials. Da beim Giessen der Leitschaufel 20 das Gussmaterial von zwei Seiten, nämlich von dem Schaufel köpf und der Deckplatte 23 bzw. 21 her, in die Gussform einfliesst, ist es für den Erfolg und die Präzision des Gusses von Vorteil, wenn bei der Auslegung der Schaufel die Querschnittsfläche des Schaufelmaterials über der Höhe h variiert, indem insbesondere diese Querschnittsfläche ein Minimum durchläuft. Das Minimum der Querschnittsfläche befindet sich vorzugsweise im Bereich zwischen 20% und 40% der Höhe h des Schaufelblattes 22 bzw. im Bereich von 0,2h bis 0,4h, wie dies in Fig. 3 durch die gestrichelten Grenzen angedeutet ist.The airfoil 22 with its inner cooling channels 30, 31, 32 is bounded outwardly by walls 33, 36, while the cooling channels 30, 31, 32 are delimited from each other by walls 34 and 35. The total cross-sectional area of the walls 33, .., 36 in the radial direction, i. in the direction of the height h of the airfoil 22, results as a difference of the airfoil cross section and the cross section of the cooling channels 30, 31, 32. This area difference is the integral cross-sectional area of the blade material. As the casting material flows into the mold from two sides, namely from the blade head and the cover plate 23 or 21, when the guide blade 20 is cast, it is advantageous for the success and the precision of the casting when designing the blade the cross-sectional area of the blade material over the height h varies, in particular, this cross-sectional area passes through a minimum. The minimum of the cross-sectional area is preferably in the range between 20% and 40% of the height h of the airfoil 22 or in the range of 0.2h to 0.4h, as indicated in FIG. 3 by the dashed lines.
Durch diese Auslegung wird die Form des Schaufel profus im Hinblick auf Querschnittsfläche, Wandstärke, Sehnenlänge und Kühlkanalquerschnitt beeinflusst. Mit einer entsprechenden Verteilung dieser Parameter über die Schaufelblatthöhe werden die zugrundegelegten Anforderungen hinsichtlich der Lebensdauer der Schaufel, der erzielbaren Kühlung und des Kühlluft-Verbrauchs erzielt.By this design, the shape of the blade profus is influenced in terms of cross-sectional area, wall thickness, chord length and cooling channel cross-section. With an appropriate distribution of these parameters over the blade height, the underlying requirements with respect to the life of the blade, the achievable cooling and the cooling air consumption are achieved.
Mit der optimierten Verteilung des Schaufelmaterials entlang des Schaufelblattes wird beim Giessen der Schaufel das Auftreten von Porositäten minimiert. Hierdurch erhöht sich die Qualität der gegossenen Schaufelblätter, was zu einer verbesserten Effizienz, insbesondere was die Kühlung betrifft, zu einer erhöhten Lebensdauer und zu reduzierten Kosten bei der Herstellung führt. Mit Vorteil können die erfindungsgemässen Leitschaufeln in Gasturbinen mit sequentieller Verbrennung eingesetzt werden, und zwar insbesondere in den mittleren Leitschaufelreihen der Niederdruckturbine, die der zweiten Brennkammer nachgeschaltet ist. With the optimized distribution of the blade material along the airfoil, the occurrence of porosity is minimized when casting the blade. This increases the quality of the cast airfoils, which leads to improved efficiency, in particular as regards the cooling, to an increased service life and to reduced costs in the production. Advantageously, the guide vanes according to the invention can be used in gas turbines with sequential combustion, in particular in the middle rows of guide vanes of the low-pressure turbine, which is connected downstream of the second combustion chamber.
BezugszeichenlisteLIST OF REFERENCE NUMBERS
10 Gasturbine10 gas turbine
11 Verdichter11 compressors
12,16 Brennstoffzufuhr12,16 fuel supply
13 EV-Brenner, Vormischbrenner13 EV burners, premix burners
14,17 Brennkammer14,17 combustion chamber
15 Hochdruckturbine15 high-pressure turbine
18 Niederdruckturbine18 low-pressure turbine
19 Achse19 axis
20,20 Leitschaufel20.20 vane
21 Deckplatte (Deckband)21 cover plate (shroud)
22 Schaufelblatt22 airfoil
23 Schaufel köpf23 scoop head
24,25 Befestigungselement (hakenförmig)24,25 fastener (hook-shaped)
26 Saugseite26 suction side
27 Vorderkante27 leading edge
28 Hinterkante28 trailing edge
29 Heissgasstrom29 hot gas stream
30,31 ,32 Kühlkanal30,31, 32 cooling channel
33,..,36 Wand (Schaufelblatt) h Höhe (Schaufelblatt) 33, .., 36 wall (airfoil) h height (airfoil)

Claims

Patentansprüche claims
1. Leitschaufel (20) für eine Gasturbine (10), welche Leitschaufel (20) ein sich in radialer Richtung zwischen einem Schaufelkopf (23) und einer DeckplatteA guide vane (20) for a gas turbine (10), said vane (20) extending in a radial direction between a blade head (23) and a cover plate
(21 ) erstreckendes Schaufelblatt (22) aufweist, in dessen Innerem Kühlkanäle (30, 31 , 32) verlaufen, durch die ein Kühlmedium zum Kühlen der Leitschaufel (20) strömen, dadurch gekennzeichnet, dass das Schaufelblatt (22) in radialer Richtung eine Querschnittsfläche des Schaufelmaterials aufweist, und dass die Querschnittsfläche des(21) extending airfoil (22) inside which run cooling channels (30, 31, 32) through which a cooling medium for cooling the vane (20) to flow, characterized in that the airfoil (22) in the radial direction has a cross-sectional area of the blade material, and that the cross-sectional area of the
Schaufelmaterials über der Höhe (h) des Schaufelblattes (22) variiert.Blade material over the height (h) of the airfoil (22) varies.
2. Leitschaufel nach Anspruch 1 , dadurch gekennzeichnet, dass die Querschnittsfläche des Schaufelmaterials in Abhängigkeit von der Höhe (h) des Schaufelblattes (22) durch ein Minimum geht.2. Guide vane according to claim 1, characterized in that the cross-sectional area of the blade material in dependence on the height (h) of the airfoil (22) passes through a minimum.
3. Leitschaufel nach Anspruch 2, dadurch gekennzeichnet, dass die minimale Querschnittsfläche des Schaufelmaterials im Bereich zwischen 20% und 40% der gesamten Höhe (h) des Schaufelblattes (22) liegt.3. Guide vane according to claim 2, characterized in that the minimum cross-sectional area of the blade material is in the range between 20% and 40% of the total height (h) of the airfoil (22).
4. Leitschaufel nach Anspruch 1 , dadurch gekennzeichnet, dass das Kühlmedium Luft und/oder Dampf ist.4. Guide vane according to claim 1, characterized in that the cooling medium is air and / or steam.
5. Leitschaufel nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass sie eine im Raum gekrümmte Form aufweist, dass im Inneren des5. Guide vane according to one of claims 1 to 4, characterized in that it has a curved in space form that inside the
Schaufelblatts (22) drei in radialer Richtung verlaufende Kühlkanäle (30, 31 , 32) in Richtung des Heissgasstromes (29) hintereinander angeordnet und durch an den Enden des Schaufelblattes (22) angeordnete Umlenkbereiche miteinander verbunden sind, dass das Kühlmedium die Kühlkanäle (30, 31 , 32) nacheinander in wechselnder Richtung durchströmt, und dass dieBlade (22) three extending in the radial direction of the cooling channels (30, 31, 32) in the direction of the hot gas flow (29) arranged one behind the other and are connected by arranged at the ends of the airfoil (22) deflection regions, that the cooling medium, the cooling channels (30, 31, 32) successively flows in alternating directions, and that the
Kühlkanäle (30, 31 , 32) in radialer Richtung der Krümmung des Schaufelblattes (22) im Raum folgen. Cooling channels (30, 31, 32) in the radial direction of the curvature of the airfoil (22) in the room follow.
6. Gasturbine (10) mit einer Leitschaufel nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass die Leitschaufel (20) in einer Turbine (15, 18) der Gasturbine (10) angeordnet ist.6. Gas turbine (10) with a guide vane according to one of claims 1 to 5, characterized in that the guide vane (20) in a turbine (15, 18) of the gas turbine (10) is arranged.
7. Gasturbine nach Anspruch 6, dadurch gekennzeichnet, dass die Gasturbine (10) eine Gasturbine mit sequentieller Verbrennung ist, die eine erste Brennkammer (14) mit einer nachgeschalteten Hochdruckturbine (15) und eine zweite Brennkammer (17) mit einer nachgeschalteten Niederdruckturbine (18) aufweist, und dass die Leitschaufel (20) in der Niederdruckturbine (18) angeordnet ist.7. Gas turbine according to claim 6, characterized in that the gas turbine (10) is a gas turbine with sequential combustion, a first combustion chamber (14) with a downstream high-pressure turbine (15) and a second combustion chamber (17) with a downstream low-pressure turbine (18 ), and that the vane (20) is disposed in the low-pressure turbine (18).
8. Gasturbine nach Anspruch 7, dadurch gekennzeichnet, dass die8. Gas turbine according to claim 7, characterized in that the
Niederdruckturbine in Strömungsrichtung hintereinander mehrere Reihen von Leitschaufeln aufweist, und dass die Leitschaufel (20) in einer mittleren Leitschaufelreihe angeordnet ist. Low-pressure turbine in the flow direction behind a plurality of rows of vanes, and that the vane (20) is arranged in a middle row of guide vanes.
EP09726037.6A 2008-03-28 2009-03-05 Guide vane for a gas turbine Active EP2260180B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH4682008 2008-03-28
PCT/EP2009/052570 WO2009118235A2 (en) 2008-03-28 2009-03-05 Guide vane for a gas turbine

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Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8757961B1 (en) * 2011-05-21 2014-06-24 Florida Turbine Technologies, Inc. Industrial turbine stator vane
US8720526B1 (en) * 2012-11-13 2014-05-13 Siemens Energy, Inc. Process for forming a long gas turbine engine blade having a main wall with a thin portion near a tip
ITCO20120059A1 (en) * 2012-12-13 2014-06-14 Nuovo Pignone Srl METHODS FOR MANUFACTURING SHAPED SHAPED LOAFERS IN 3D OF TURBOMACCHINE BY ADDITIVE PRODUCTION, TURBOMACCHINA CAVE BLOCK AND TURBOMACCHINE
EP3034798B1 (en) * 2014-12-18 2018-03-07 Ansaldo Energia Switzerland AG Gas turbine vane
EP3081751B1 (en) * 2015-04-14 2020-10-21 Ansaldo Energia Switzerland AG Cooled airfoil and method for manufacturing said airfoil
EP3112589A1 (en) 2015-07-03 2017-01-04 Siemens Aktiengesellschaft Turbine blade
US10174622B2 (en) * 2016-04-12 2019-01-08 Solar Turbines Incorporated Wrapped serpentine passages for turbine blade cooling
US10641174B2 (en) 2017-01-18 2020-05-05 General Electric Company Rotor shaft cooling
US10533454B2 (en) 2017-12-13 2020-01-14 Pratt & Whitney Canada Corp. Turbine shroud cooling
US10570773B2 (en) 2017-12-13 2020-02-25 Pratt & Whitney Canada Corp. Turbine shroud cooling
US11274569B2 (en) 2017-12-13 2022-03-15 Pratt & Whitney Canada Corp. Turbine shroud cooling
US10502093B2 (en) * 2017-12-13 2019-12-10 Pratt & Whitney Canada Corp. Turbine shroud cooling
US11365645B2 (en) 2020-10-07 2022-06-21 Pratt & Whitney Canada Corp. Turbine shroud cooling

Family Cites Families (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2823893A (en) * 1952-06-09 1958-02-18 Gen Motors Corp Laminated turbine buckets
GB811921A (en) * 1955-03-10 1959-04-15 Rolls Royce Improvements relating to manufacture of blading for axial-flow fluid machines
GB811586A (en) * 1956-07-25 1959-04-08 Havilland Engine Co Ltd Turbine or compressor blades
US3066910A (en) * 1958-07-09 1962-12-04 Thompson Ramo Wooldridge Inc Cooled turbine blade
US4136516A (en) * 1977-06-03 1979-01-30 General Electric Company Gas turbine with secondary cooling means
CH674561A5 (en) 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
US4930980A (en) * 1989-02-15 1990-06-05 Westinghouse Electric Corp. Cooled turbine vane
US5813835A (en) 1991-08-19 1998-09-29 The United States Of America As Represented By The Secretary Of The Air Force Air-cooled turbine blade
US5207556A (en) * 1992-04-27 1993-05-04 General Electric Company Airfoil having multi-passage baffle
JP2684936B2 (en) * 1992-09-18 1997-12-03 株式会社日立製作所 Gas turbine and gas turbine blade
CH687347A5 (en) * 1993-04-08 1996-11-15 Abb Management Ag Heat generator.
CH687269A5 (en) 1993-04-08 1996-10-31 Abb Management Ag Gas turbine group.
US5688104A (en) * 1993-11-24 1997-11-18 United Technologies Corporation Airfoil having expanded wall portions to accommodate film cooling holes
DE4435266A1 (en) 1994-10-01 1996-04-04 Abb Management Ag burner
US5488825A (en) * 1994-10-31 1996-02-06 Westinghouse Electric Corporation Gas turbine vane with enhanced cooling
DE19514991A1 (en) * 1995-04-24 1996-10-31 Abb Management Ag Method for operating a sequentially fired gas turbine group
JPH1077802A (en) * 1996-09-04 1998-03-24 Hitachi Ltd Axial flow turbine blade
GB2345942B (en) * 1998-12-24 2002-08-07 Rolls Royce Plc Gas turbine engine internal air system
JP3782637B2 (en) * 2000-03-08 2006-06-07 三菱重工業株式会社 Gas turbine cooling vane
CN2711391Y (en) * 2004-06-09 2005-07-20 哈尔滨汽轮机厂有限责任公司 Final stage blade for large air cooling turbine
US7104756B2 (en) * 2004-08-11 2006-09-12 United Technologies Corporation Temperature tolerant vane assembly
EP1789654B1 (en) 2004-09-16 2017-08-23 General Electric Technology GmbH Turbine engine vane with fluid cooled shroud
US7510371B2 (en) * 2005-06-06 2009-03-31 General Electric Company Forward tilted turbine nozzle
US20100310367A1 (en) * 2006-09-28 2010-12-09 United Technologies Corporation Impingement cooling of a turbine airfoil with large platform to airfoil fillet radius

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2009118235A3 *

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EP2260180B1 (en) 2017-10-04
JP5490091B2 (en) 2014-05-14
US20110076155A1 (en) 2011-03-31
WO2009118235A3 (en) 2010-11-25
CN102016234A (en) 2011-04-13
CN102016234B (en) 2015-05-20
JP2011517480A (en) 2011-06-09
WO2009118235A2 (en) 2009-10-01
US8459934B2 (en) 2013-06-11

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