EP2300686B1 - Gas turbine comprising a guide vane - Google Patents
Gas turbine comprising a guide vane Download PDFInfo
- Publication number
- EP2300686B1 EP2300686B1 EP09765688.8A EP09765688A EP2300686B1 EP 2300686 B1 EP2300686 B1 EP 2300686B1 EP 09765688 A EP09765688 A EP 09765688A EP 2300686 B1 EP2300686 B1 EP 2300686B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- plenum
- gas turbine
- blade
- outer platform
- hot gas
- 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.)
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Links
- 239000002826 coolant Substances 0.000 claims description 21
- 238000001816 cooling Methods 0.000 claims description 19
- 238000007789 sealing Methods 0.000 claims description 17
- 230000000694 effects Effects 0.000 claims description 4
- 239000007789 gas Substances 0.000 description 37
- 238000002485 combustion reaction Methods 0.000 description 14
- 239000000446 fuel Substances 0.000 description 7
- 102100031118 Catenin delta-2 Human genes 0.000 description 2
- 101000922056 Homo sapiens Catenin delta-2 Proteins 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 241000251133 Sphyrna tiburo Species 0.000 description 1
- 206010053615 Thermal burn Diseases 0.000 description 1
- WYTGDNHDOZPMIW-RCBQFDQVSA-N alstonine Natural products C1=CC2=C3C=CC=CC3=NC2=C2N1C[C@H]1[C@H](C)OC=C(C(=O)OC)[C@H]1C2 WYTGDNHDOZPMIW-RCBQFDQVSA-N 0.000 description 1
- 239000011324 bead Substances 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
Images
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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
-
- 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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
-
- 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
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
-
- 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
- F05D2240/55—Seals
- F05D2240/57—Leaf seals
-
- 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
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
Definitions
- the present invention relates to the field of gas turbine technology. It relates to a gas turbine with a vane according to the preamble of claim 1.
- Gas turbines with sequential combustion are known and have proven themselves in industrial operation.
- Such a gas turbine which has become known in the art as GT24 / 26, for example, from an article of Joos, F. et al., "Field Experience of the Sequential Combustion System for the ABB GT24 / GT26 Gas Turbine Family", IGTI / ASME 98-GT-220, 1998 Sweden ,
- the local Fig. 1 shows the basic structure of such a gas turbine, where the local Fig. 1 in the present application as Fig. 1 is reproduced. Furthermore, such a gas turbine goes out EP-B1-0 620 362 out.
- 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 mixed with at least one fuel, at least via the fuel supply 12 brought up fuel becomes.
- premix burners go out in principle EP-A1-0 321 809 or EP-A2-0 704 657 out.
- 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 provided in this way is partially expanded in the subsequent high-pressure turbine 15 under working power 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 in the flow direction arranged one behind the other a plurality of rows of blades and vanes, which are arranged alternately.
- the guide vanes of the third row of guide vanes in the flow direction are in Fig. 1 provided with the reference numeral 20 '.
- a gaseous cooling medium eg compressed air from the compressor of the gas turbine or steam, if the gas turbine is part of a combined cycle power plant
- a gaseous cooling medium sent through arranged in the blade (often running in serpentine) cooling channels and / or at different points of the blade through corresponding openings (holes , Slits) to the outside, in particular on the outside of the blade to form a cooling film (film cooling).
- a cooled blade is in the document US-A-5,813,835 described and illustrated.
- the invention aims to remedy this situation. It is therefore an object of the invention to achieve an effective cooling of the cover plate with much simpler means and to ensure it at gas turbine vane.
- Essential for the invention is that first means for controlling the cooling medium pressure in the first plenum above the cover plate of the guide vane are provided, and that second means are provided which cause a cooling of the cover plate by specifically escaping from the first plenum cooling medium. As a result, specifically escaping leakage cooling medium can be used to cool the cover plate before it flows out into the hot gas channel.
- the first means are arranged in the region of the first plenum, wherein the first means comprise a throttle element, which throttles the flow of the cooling medium through the inlet in the cover plate, and the throttle element is formed as a plate which the inlet up on one or more provided in the plate, preferably circular, throttle openings covers.
- Another embodiment is characterized in that the access to the first plenum is designed as a throttle opening. Through the throttle devices the pressure in the first plenum and the leakage of the cooling medium from the plenum can be adjusted.
- two outwardly projecting, preferably hook-shaped, fastening elements for fastening the guide blade on the blade carrier are integrally formed on the upper side of the cover plate, wherein the first plenum is formed between the two fastening elements.
- the second means comprise a second plenum disposed on the side of the one fastener facing away from the first plenum, the second plenum being supplied from the first plenum with cooling medium escaping therefrom and the second plenum communicating with the hot gas channel via throttling means stands.
- the gaps between adjacent vanes of a row of vanes are sealed by sealing strips against the hot gas channel, which are inserted into corresponding sealing grooves in the side surfaces of the cover plates of the vanes, wherein the sealing strips are formed in the region of the second plenum as a throttle means and in the region of the second plenum for Achieving a throttle effect shorter and / or much thinner than the associated sealing grooves are formed.
- a further embodiment of the invention is characterized in that the second plenum is partially bounded by an adjacent in the flow direction of the hot gas flow to the cover plate of the guide blade heat shield segment, and that between the heat shield segment and the cover plate to the hot gas channel through a step gap is arranged, via which the second Plenum communicates with the hot gas channel.
- a vane can be seen, for example, in the low pressure turbine of a sequential combustion gas turbine Fig. 1 can be used, and is suitable for the realization of the invention.
- the guide vane 20 comprises a strongly curved airfoil 22 which extends in the longitudinal direction (in the radial direction of the gas turbine) between the vane head 23 and a cover plate 21 and extends in the direction of the hot gas stream 30 from a front edge 27 to a trailing edge 28. Between the two edges 27 and 28, the airfoil 22 is outwardly through a suction side 29 and an (opposite) pressure side (in Fig. 2 not to be seen) limited.
- the vane 20 is formed by means of the hook-shaped fastening elements 24 and 25 formed on the upper side of the cover plate 21 on the blade carrier (38 in FIG Fig. 5 ), while sealingly engages with the blade head 23 on the rotor.
- the space between the fasteners 24 and 25 forms in the installed state of the vane ( Fig. 5 ) a first plenum (41) for the cooling air, while a pronounced groove 31 on the other side of the fastening element 25 in the installed state of the guide vane ( Fig. 5 ) is available as a second plenum (42).
- Sealing grooves are provided in the side surfaces of the cover plate 21, which receive strip seals for sealing the gaps between adjacent vanes of a blade ring.
- An originating in the cover plate 21 from the casting process core output 32 is flush and thus streamlined closed by a stopper not shown in detail.
- cooling means (cooling channels, cooling fins, impingement cooling elements, etc.) are provided (not shown in the figures), according to Fig. 4 be supplied via an inlet 36 in the cover plate 21 with cooling medium (cooling air).
- the cooling medium flowing into the blade originates from the first plenum 41 above the cover plate (FIG. Fig. 6 ), in which it passes through a throttle opening 43 in the blade carrier 38.
- the comparatively large cross-section of the inlet 36 is closed by a flush inserted, plate-shaped throttle element 34, which (see Fig. 4 , Pos. 35) or several throttle openings of smaller diameter (see Fig. 5 , Pos. 35a).
- the pressure of the cooling medium 51 in the first plenum is effectively controlled and adjusted.
- the set pressure causes a targeted (controlled) leakage of the cooling medium 51 c from the first plenum 41 in the adjacent second plenum 42 and the wall of the hot gas channel 44 forming part of the cover plate 21.
- This allows the cover plate 21 without further constructive measures to simple , safe and easily adjustable way with leakage cooling medium 51 a-51 d are cooled from the cooling of the airfoil (curved arrows in Fig. 6 ).
- the use of the cooling medium which has flowed into the second plenum 42 for the cooling of the cover plate 21 is preferably influenced by two measures which are more clearly defined in FIG FIGS. 7 and 8
- a special sealing strip 46 is used which is shorter and / or substantially thinner than the associated sealing groove 26 in order to achieve a throttling effect ( Fig. 8 ).
- targeted cooling medium from the second plenum 42 through the throttled sealed gap between adjacent cover plates 21 escape into the hot gas channel and cool the cover plates.
- the weather strip especially thin can be distributed in the base portion 48 of the provided with an additional angle section 47 strip beads 49, 50 are provided to fix the position of the sealing strip 46 in the sealing groove 26 ( Fig. 8 ).
- step gap 45 is characterized by two gap widths s1 and s2 and a distance x ( Fig. 7 ), where s1 is preferably in the range between 0.1 and 2 mm, s2 is between s1 and 0.1 to 1 mm, and x is in the range between 0.2 mm and 7 mm.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Die vorliegende Erfindung bezieht sich auf das Gebiet der Gasturbinentechnik. Sie betrifft eine Gasturbine mit einer Leitschaufel gemäss dem Oberbegriff des Anspruchs 1.The present invention relates to the field of gas turbine technology. It relates to a gas turbine with a vane according to the preamble of
Gasturbinen mit sequentieller Verbrennung sind bekannt und haben sich im industriellen Betrieb bewährt.
Eine solche Gasturbine, welche in Fachkreisen als GT24/26 bekannt geworden ist, geht beispielsweise aus einem Aufsatz von
Such a gas turbine, which has become known in the art as GT24 / 26, for example, from an article of
Die verdichtete Luft strömt in die Vormischbrenner, wo die Vermischung, wie oben ausgeführt, mit mindestens einem Brennstoff stattfindet. Dieses Brennstoff/LuftGemisch strömt dann in die erste Brennkammer 14 ein, in welche dieses Gemisch unter Bildung einer stabilen Flammenfront zur Verbrennung gelangt. Das so bereit gestellte 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.
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
Die Niederdruckturbine 18 umfasst in Strömungsrichtung hintereinander angeordnet mehrere Reihen von Lauf- und Leitschaufeln, die alternierend angeordnet sind. Beispielsweise die Leitschaufeln der in Strömungsrichtung dritten Leitschaufelreihe sind in
Bei den hohen Heissgastemperaturen von Gasturbinen der letzten Generation ist es notwendig, die Leit- und Laufschaufeln der Turbine zu kühlen. Dazu wird ein gasförmiges Kühlmedium (z.B. verdichtete Luft vom Verdichter der Gasturbine oder Dampf, wenn die Gasturbine Teil eines Kombikraftwerks ist) durch in der Schaufel angeordnete (häufig in Serpentinen verlaufende) Kühlkanäle geschickt und/oder an verschiedenen Stellen der Schaufel durch entsprechende Öffnungen (Bohrungen, Schlitze) nach aussen abgegeben, um insbesondere auf der Aussenseite der Schaufel einen kühlenden Film auszubilden (Filmkühlung). Ein Beispiel für eine derartige gekühlte Schaufel ist in der Druckschrift
Besonders wichtig ist auch die Kühlung der Plattformen, insbesondere der Deckplatten. Aus der Druckschrift
Dokument
Hier will die Erfindung Abhilfe schaffen. Es ist daher Aufgabe der Erfindung, bei er Gasturbinen-Leitschaufel eine wirkungsvolle Kühlung der Deckplatte mit wesentlich einfacheren Mitteln zu erreichen und sicher zu stellen.The invention aims to remedy this situation. It is therefore an object of the invention to achieve an effective cooling of the cover plate with much simpler means and to ensure it at gas turbine vane.
Die Aufgabe wird durch eine Gesamtheit der Merkmale des Anspruchs 1 gelöst. Vorteilhafte Ausgestaltungen der erfindungsgemässen Lösung sind in den abhängigen Ansprüchen definiert.The object is achieved by an entirety of the features of
Wesentlich für die Erfindung ist, dass erste Mittel zur Steuerung des Kühlmediumdrucks in dem ersten Plenum oberhalb der Deckplatte der Leitschaufel vorgesehen sind, und dass zweite Mittel vorhanden sind, welche eine Kühlung der Deckplatte durch gezielt aus dem ersten Plenum entweichendes Kühlmedium bewirken. Hierdurch kann gezielt entweichendes Leckage-Kühlmedium zur Kühlung der Deckplatte herangezogen werden, bevor es in den Heissgaskanal abströmt.Essential for the invention is that first means for controlling the cooling medium pressure in the first plenum above the cover plate of the guide vane are provided, and that second means are provided which cause a cooling of the cover plate by specifically escaping from the first plenum cooling medium. As a result, specifically escaping leakage cooling medium can be used to cool the cover plate before it flows out into the hot gas channel.
Gemäss einer Ausgestaltung der Erfindung sind die ersten Mittel im Bereich des ersten Plenums angeordnet, wobei die ersten Mittel ein Drosselelement umfassen, welches den Strom des Kühlmediums durch den Einlass in der Deckplatte drosselt, und das Drosselelement als Platte ausgebildet ist, welche den Einlass bis auf eine oder mehrere in der Platte vorgesehene, vorzugsweise kreisrunde, Drosselöffnungen abdeckt.According to one embodiment of the invention, the first means are arranged in the region of the first plenum, wherein the first means comprise a throttle element, which throttles the flow of the cooling medium through the inlet in the cover plate, and the throttle element is formed as a plate which the inlet up on one or more provided in the plate, preferably circular, throttle openings covers.
Eine andere Ausgestaltung zeichnet sich dadurch aus, dass der Zugang zum ersten Plenum als Drosselöffnung ausgebildet ist. Durch die Drosselvorrichtungen kann der Druck im ersten Plenum und die Leckage des Kühlmediums aus dem Plenum eingestellt werden.Another embodiment is characterized in that the access to the first plenum is designed as a throttle opening. Through the throttle devices the pressure in the first plenum and the leakage of the cooling medium from the plenum can be adjusted.
Vorzugsweise sind auf der Oberseite der Deckplatte voneinander beabstandet zwei nach aussen abstehende, vorzugsweise hakenförmige, Befestigungselemente zum Befestigen der Leitschaufel an dem Schaufelträger angeformt, wobei das erste Plenum zwischen den beiden Befestigungselementen ausgebildet ist.Preferably, two outwardly projecting, preferably hook-shaped, fastening elements for fastening the guide blade on the blade carrier are integrally formed on the upper side of the cover plate, wherein the first plenum is formed between the two fastening elements.
Insbesondere umfassen die zweiten Mittel ein zweites Plenum, welches auf der dem ersten Plenum abgewandten Seite des einen Befestigungselements angeordnet ist, wobei das zweite Plenum aus dem ersten Plenum mit von dort entweichendem Kühlmedium versorgt wird, und das zweite Plenum über Drosselmittel mit dem Heissgaskanal in Verbindung steht.In particular, the second means comprise a second plenum disposed on the side of the one fastener facing away from the first plenum, the second plenum being supplied from the first plenum with cooling medium escaping therefrom and the second plenum communicating with the hot gas channel via throttling means stands.
Weiterhin sind die zwischen benachbarten Leitschaufeln einer Leitschaufelreihe bestehenden Spalte durch Dichtungsstreifen gegen den Heissgaskanal abgedichtet, die in entsprechende Dichtungsnuten in den Seitenflächen der Deckplatten der Leitschaufeln eingeschoben sind, wobei die Dichtungsstreifen im Bereich des zweiten Plenums als Drosselmittel ausgebildet sind und im Bereich des zweiten Plenums zur Erzielung einer Drosselwirkung kürzer und/oder wesentlich dünner als die zugehörigen Dichtungsnuten ausgebildet sind.Furthermore, the gaps between adjacent vanes of a row of vanes are sealed by sealing strips against the hot gas channel, which are inserted into corresponding sealing grooves in the side surfaces of the cover plates of the vanes, wherein the sealing strips are formed in the region of the second plenum as a throttle means and in the region of the second plenum for Achieving a throttle effect shorter and / or much thinner than the associated sealing grooves are formed.
Eine weitere Ausgestaltung der Erfindung ist dadurch gekennzeichnet, dass das zweite Plenum teilweise von einem in Strömungsrichtung des Heissgasstromes an die Deckplatte der Leitschaufel angrenzenden Wärmestausegment begrenzt wird, und dass zwischen dem Wärmestausegment und der Deckplatte zum Heissgaskanal hin ein Stufenspalt angeordnet ist, über welchen das zweite Plenum mit dem Heissgaskanal in Verbindung steht.A further embodiment of the invention is characterized in that the second plenum is partially bounded by an adjacent in the flow direction of the hot gas flow to the cover plate of the guide blade heat shield segment, and that between the heat shield segment and the cover plate to the hot gas channel through a step gap is arranged, via which the second Plenum communicates with the hot gas channel.
Die Erfindung soll nachfolgend anhand von Ausführungsbeispielen im Zusammenhang mit der Zeichnung näher erläutert werden. Alle für das unmittelbare Verständnis der Erfindung nicht wesentlichen Elemente sind weggelassen 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 sequentieller Verbrennung nach dem Stand der Technik,
- Fig. 2
- in einer perspektivischen Seitenansicht eine Leitschaufel für eine bevorzugtes Ausführungsbeispiel der Erfindung,
- Fig. 3
- in der Draufsicht von oben die Deckplatte der Leitschaufel aus
Fig. 2 mit dem am Ausgang des ersten Plenums angeordneten Drosselelement, - Fig. 4
- den Schnitt in der Ebene IV-IV in
Fig. 3 durch das Drosselelement, - Fig. 5
- den Schnitt durch das Drosselelement im Einklang mit
Fig. 4 , wobei das Drosselelement mehrere Drosselöffnungen aufweist, - Fig. 6
- in einer Seitenansicht die Befestigung der Leitschaufel aus
Fig. 2 in der Gasturbine, - Fig. 7
- die Ausbildung des Stufenspaltes zwischen zweitem Plenum und Heissgaskanal gemäss einem Ausführungsbeispiel der Erfindung und
- Fig. 8
- die als Drosselmittel ausgebildete Streifendichtung zwischen benachbarten Deckplatten gemäss einem anderen Ausführungsbeispiel der Erfindung.
- Fig. 1
- the basic structure of a gas turbine with sequential combustion according to the prior art,
- Fig. 2
- in a perspective side view of a guide vane for a preferred embodiment of the invention,
- Fig. 3
- in the plan view from above the cover plate of the vane
Fig. 2 with the throttle element arranged at the exit of the first plenum, - Fig. 4
- the section in the plane IV-IV in
Fig. 3 through the throttle element, - Fig. 5
- the section through the throttle element in accordance with
Fig. 4 wherein the throttle element has a plurality of throttle openings, - Fig. 6
- in a side view of the attachment of the vane
Fig. 2 in the gas turbine, - Fig. 7
- the formation of the step gap between the second plenum and hot gas duct according to an embodiment of the invention and
- Fig. 8
- formed as a throttle means strip seal between adjacent cover plates according to another embodiment of the invention.
Aus
Der Einsatz des erfindungsgemässen Gegenstandes ist aber weder auf die genannte Gasturbinenart noch auf eine spezielle Leit- oder Laufschaufel beschränkt.
Die Leitschaufel 20 umfasst ein im Raum stark gekrümmtes Schaufelblatt 22, dass sich in Längsrichtung (in radialer Richtung der Gasturbine) zwischen Schaufelkopf 23 und einer Deckplatte 21 erstreckt und in Richtung des Heissgasstromes 30 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 Saugseite 29 und eine (gegenüberliegende) Druckseite (in
However, the use of the article according to the invention is not limited to the named type of gas turbine or to a special guide or moving blade.
The
Die Leitschaufel 20 ist mittels der auf der Oberseite der Deckplatte 21 ausgebildeten hakenförmigen Befestigungselemente 24 und 25 am Schaufelträger (38 in
Im Inneren des Schaufelblattes 22 sind (in den Figuren nicht gezeigte) Kühleinrichtungen (Kühlkanäle, Kühlrippen, Prallkühlelemente etc.) vorgesehen, die gemäss
Wie aus
Der Einsatz des in das zweite Plenum 42 eingeströmten Kühlmediums für die Kühlung der Deckplatte 21 wird vorzugsweise durch zwei Massnahmen beeinflusst, die deutlicher in
Zum anderen ist zwischen einem an die Deckplatte 21 der Leitschaufel 20 angrenzenden Wärmestausegment 39, das einer Laufschaufel 40 gegenüberliegt und teilweise das zweite Plenum 42 begrenzt, und der Deckplatte 21 zum Heissgaskanal 44 hin ein Stufenspalt 45 angeordnet, über welchen das zweite Plenum 42 mit dem Heissgaskanal 44 auf gezielte Weise in Verbindung steht. Die Geometrie des Stufenspaltes 45 ist dabei durch zwei Spaltbreiten s1 und s2 und einen Abstand x charakterisiert (
- 1010
- Gasturbinegas turbine
- 1111
- Verdichtercompressor
- 12,1612.16
- Brennstoffzufuhrfuel supply
- 1313
- EV-BrennerEV burner
- 14,1714.17
- Brennkammercombustion chamber
- 1515
- HochdruckturbineHigh-pressure turbine
- 1818
- NiederdruckturbineLow-pressure turbine
- 1919
- Achseaxis
- 20,20'20.20 '
- Leitschaufelvane
- 2121
- Deckplattecover plate
- 2222
- Schaufelblattairfoil
- 2323
- Schaufelkopfshovel head
- 24,2524.25
- Befestigungselement (hakenförmig)Fastening element (hook-shaped)
- 2626
- Dichtungsnutseal groove
- 2727
- Vorderkanteleading edge
- 2828
- Hinterkantetrailing edge
- 2929
- Saugseitesuction
- 3030
- HeissgasstromHot gas flow
- 3131
- Hohlkehlefillet
- 3232
- Kernausgangcore output
- 3434
- Drosselelementthrottle element
- 35, 35a, 4335, 35a, 43
- Drosselöffnungenthrottle openings
- 3636
- Einlassinlet
- 3737
- Anschlussflächeterminal area
- 3838
- Schaufelträger (Gehäuse)Blade carrier (housing)
- 3939
- WärmestausegmentHeat shield
- 4040
- Laufschaufelblade
- 41,4241.42
- Plenumplenum
- 4444
- HeissgaskanalHot-gas duct
- 4545
- Stufenspaltstep gap
- 4646
- Dichtungsstreifen (L-förmig)Sealing strips (L-shaped)
- 4747
- Winkelabschnittangle section
- 4848
- Basisabschnittbase section
- 49,5049,50
- SickeBeading
- 51, 51a-51d51, 51a-51d
- Kühlmediumcooling medium
- s1,s2s1, s2
- Spaltbreitegap width
- xx
- Abstanddistance
Claims (8)
- Gas turbine (10) with a stator blade (20), which stator blade (20) is fastened on a blade carrier (38) and comprises a blade airfoil (22) which extends inwards in the radial direction from an outer platform (21) into a hot gas passage (44), wherein a cooling medium (51) flows through the interior of the stator blade (20), which cooling medium, through an access (43) in the blade carrier (38), flows into a first plenum (41) which is arranged above the outer platform (21), and from there, via an inlet (36) which is provided in the outer platform (21), flows into the interior of the stator blade (20), wherein provision is made for first means (34, 35; 35a, 43) for controlling the cooling-medium pressure in the first plenum (41), and in that provision is made for second means (42, 45, 46) which effect cooling of the outer platform (21) by means of cooling medium which escapes in a directed manner from the first plenum (41), characterized in that the first means (34, 35; 35a, 43) are arranged in the region of the first plenum (41), and in that the first means comprise a throttling element (34) which throttles the flow of cooling medium through the inlet (36) in the outer platform (21).
- Gas turbine according to Claim 1, characterized in that the throttling element (34) is formed as a plate which covers the inlet (36) except for at least one, preferably circular, throttling opening (35, 35a) which is provided in the plate.
- Gas turbine according to one of Claims 1 to 2, characterized in that the access to the first plenum (41) is formed as at least one throttling opening (43).
- Gas turbine according to one of Claims 1 to 3, characterized in that outwardly projecting, preferably hook-like fastening elements (24, 25), for fastening the stator blade (20) on the blade carrier (38), are formed on the upper side of the outer platform (21) at a distance from each other, and in that the first plenum (41) is formed between the two fastening elements (24, 25).
- Gas turbine according to Claim 4, characterized in that the second means comprise a second plenum (42) which is arranged on the side of the one fastening element (25) facing away from the first plenum (41), in that the second plenum (42) is supplied from the first plenum (41) with cooling medium which escapes from there, and in that the second plenum (42) is in communication with the hot gas passage (44) via throttling means (45, 46).
- Gas turbine according to Claim 5, characterized in that the gaps which exist between adjacent stator blades (20) of a stator blade row are sealed against the hot gas passage (44) by means of sealing strips (46) which are inserted in corresponding sealing grooves (26) in the lateral surfaces of the outer platforms (21) of the stator blades (20), and in that the sealing strips (46) are formed as throttling means in the region of the second plenum (42).
- Gas turbine according to Claim 6, characterized in that the sealing strips (46) in the region of the second plenum (42) are formed shorter and/or considerably thinner than the associated sealing grooves (26) for achieving a throttling effect.
- Gas turbine according to Claim 6 or 7, characterized in that the second plenum (42) is partially delimited by a heat shield segment (39) which is adjacent to the outer platform (21) of the stator blade (20) in the flow direction of the hot gas flow (30), and in that a stepped gap (45), via which the second plenum (42) is in communication with the hot gas passage (44), is arranged between the heat shield segment (39) and the outer platform (21) towards the hot gas passage (44).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH7902008 | 2008-05-26 | ||
PCT/EP2009/055768 WO2009153108A2 (en) | 2008-05-26 | 2009-05-13 | Gas turbine comprising a guide vane |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2300686A2 EP2300686A2 (en) | 2011-03-30 |
EP2300686B1 true EP2300686B1 (en) | 2013-08-07 |
Family
ID=39832517
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP09765688.8A Active EP2300686B1 (en) | 2008-05-26 | 2009-05-13 | Gas turbine comprising a guide vane |
Country Status (4)
Country | Link |
---|---|
US (1) | US8210797B2 (en) |
EP (1) | EP2300686B1 (en) |
ES (1) | ES2432622T3 (en) |
WO (1) | WO2009153108A2 (en) |
Families Citing this family (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP4841678B2 (en) * | 2010-04-15 | 2011-12-21 | 川崎重工業株式会社 | Turbine vane of gas turbine |
RU2547542C2 (en) * | 2010-11-29 | 2015-04-10 | Альстом Текнолоджи Лтд | Axial gas turbine |
EP2518278A1 (en) * | 2011-04-28 | 2012-10-31 | Siemens Aktiengesellschaft | Turbine casing cooling channel with cooling fluid flowing upstream |
EP2644833A1 (en) * | 2012-03-26 | 2013-10-02 | Alstom Technology Ltd | Holder ring |
US8961108B2 (en) * | 2012-04-04 | 2015-02-24 | United Technologies Corporation | Cooling system for a turbine vane |
EP2811118B1 (en) * | 2013-06-06 | 2018-03-14 | MTU Aero Engines GmbH | Guide blade segment of a turboengine and turbine |
EP3199759A1 (en) | 2016-01-29 | 2017-08-02 | Siemens Aktiengesellschaft | Turbine blade for a thermal turbo engine |
EP3199760A1 (en) | 2016-01-29 | 2017-08-02 | Siemens Aktiengesellschaft | Turbine blade with a throttle element |
US10641174B2 (en) | 2017-01-18 | 2020-05-05 | General Electric Company | Rotor shaft cooling |
FR3070718B1 (en) * | 2017-09-06 | 2019-08-23 | Safran Aircraft Engines | RING SECTOR TURBINE ASSEMBLY |
FR3070716B1 (en) * | 2017-09-06 | 2020-10-02 | Safran Aircraft Engines | STATOR RINGS SEALING TAB |
US10655489B2 (en) * | 2018-01-04 | 2020-05-19 | General Electric Company | Systems and methods for assembling flow path components |
US11035251B2 (en) * | 2019-09-26 | 2021-06-15 | General Electric Company | Stator temperature control system for a gas turbine engine |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
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US3427000A (en) * | 1966-11-14 | 1969-02-11 | Westinghouse Electric Corp | Axial flow turbine structure |
DE2065334C3 (en) * | 1969-12-01 | 1982-11-25 | General Electric Co., Schenectady, N.Y. | Cooling system for the inner and outer massive platforms of a hollow guide vane |
US3781125A (en) * | 1972-04-07 | 1973-12-25 | Westinghouse Electric Corp | Gas turbine nozzle vane structure |
US4187054A (en) * | 1978-04-20 | 1980-02-05 | General Electric Company | Turbine band cooling system |
CH674561A5 (en) | 1987-12-21 | 1990-06-15 | Bbc Brown Boveri & Cie | |
US5098257A (en) * | 1990-09-10 | 1992-03-24 | Westinghouse Electric Corp. | Apparatus and method for minimizing differential thermal expansion of gas turbine vane structures |
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 |
DE4435266A1 (en) | 1994-10-01 | 1996-04-04 | Abb Management Ag | burner |
US5816835A (en) * | 1996-10-21 | 1998-10-06 | Alden Products Company | Multi-sleeve high-voltage cable plug with vented seal |
US6227798B1 (en) * | 1999-11-30 | 2001-05-08 | General Electric Company | Turbine nozzle segment band cooling |
US6431820B1 (en) * | 2001-02-28 | 2002-08-13 | General Electric Company | Methods and apparatus for cooling gas turbine engine blade tips |
DE10306915A1 (en) * | 2003-02-19 | 2004-09-02 | Alstom Technology Ltd | Seal for use between segments of gas turbine shrouds comprises strip with apertures for passage of gas in pattern designed so that when strip shifts sideways their free cross-section remains constant |
DE102005013795A1 (en) | 2005-03-24 | 2006-09-28 | Alstom Technology Ltd. | Guide vane for e.g. gas turbine, has open connection channel for inner hole provided in area of side wall section facing platform section, and platform with side edge having recess, where stripped seal is provided in recess |
US7625174B2 (en) * | 2005-12-16 | 2009-12-01 | General Electric Company | Methods and apparatus for assembling gas turbine engine stator assemblies |
-
2009
- 2009-05-13 EP EP09765688.8A patent/EP2300686B1/en active Active
- 2009-05-13 ES ES09765688T patent/ES2432622T3/en active Active
- 2009-05-13 WO PCT/EP2009/055768 patent/WO2009153108A2/en active Application Filing
-
2010
- 2010-11-24 US US12/954,205 patent/US8210797B2/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
WO2009153108A2 (en) | 2009-12-23 |
EP2300686A2 (en) | 2011-03-30 |
ES2432622T3 (en) | 2013-12-04 |
US20110085894A1 (en) | 2011-04-14 |
US8210797B2 (en) | 2012-07-03 |
WO2009153108A3 (en) | 2010-07-15 |
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