EP1013884A2 - Turbine blade with actively cooled head platform - Google Patents
Turbine blade with actively cooled head platform Download PDFInfo
- Publication number
- EP1013884A2 EP1013884A2 EP99811187A EP99811187A EP1013884A2 EP 1013884 A2 EP1013884 A2 EP 1013884A2 EP 99811187 A EP99811187 A EP 99811187A EP 99811187 A EP99811187 A EP 99811187A EP 1013884 A2 EP1013884 A2 EP 1013884A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- turbine blade
- cooling
- blade according
- shroud
- open
- 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
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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
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2240/00—Components
- F05B2240/80—Platforms for stationary or moving blades
- F05B2240/801—Platforms for stationary or moving blades cooled platforms
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- 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 turbines. It affects an air-cooled turbine blade, which is vertical at the tip of the blade to the blade longitudinal axis extending shroud element, wherein the shroud element for the purpose of cooling a plurality of cooling holes is crossed, which on the input side with at least one through the Turbine blade in connection with the cooling air duct running at the tip of the blade stand and on the output side in the outside space surrounding the turbine blade flow out.
- Generic turbine blades are from DE 198 13 173 A1 or from US 5,785,496.
- the basic idea of the invention is, on the one hand, to guide the cooling bores through the shroud element in such a way that a high heat transfer between the shroud element and cooling air is ensured and, on the other hand, to allow these bores to open into the outside space in such a way that the exposed regions of the shroud reliably depend on Cooling air is applied and additionally cooled. This is achieved by proceeding from the cooling channel of the blade in the area of the shroud element, the cooling holes running essentially parallel to the direction of movement of the shovel tip from the inside to the outside and each opening in front of the outer edge of the shroud element in a recess in the surface open to the outside.
- recesses are made in the cover band element near the outer edge from the top, into which the cooling holes open laterally.
- the outlet of the cooling air on the top of the shroud element is particularly effective if, according to a preferred development, mutually spaced sealing ribs are provided on the top of the shroud element, which form a cavity in cooperation with the opposite housing wall of the gas turbine, and the cooling holes in open this cavity.
- the escaping cooling air leads to a pressure build-up in the cavity, as a result of which the penetration of hot gases is reduced.
- the side edges of the Shroud elements recesses into which the cooling holes open.
- the recesses Opposing shroud elements form a gap.
- the cooling air is divided into two partial flows. A part flows to the top and feeds the cavity mentioned between the spaced Sealing ribs with the above-mentioned effect.
- the other part flows to Underside of the cover tape and mixes there with the hot gases under setting a mixing temperature that reduces the thermal load in this area. Due to the gap geometry, the ratio of those flowing up and down can Partial quantities are influenced.
- the holes can be created using the so-called "STEM drilling” process.
- STEM drilling which has been described, for example, in US Pat. No. 5,306,401 in connection with the production of cooling holes in turbine blades, can be used to produce cooling bores with improved heat transfer properties simply and reliably.
- the turbine blade 10 comprises the actual one Blade profile 23 and one arranged transversely thereto at the tip of the blade Shroud element 11, which together with the shroud elements of the other Buckets (not shown) a continuous, mechanically stabilizing Cover band results.
- the blade profile 23 is partially hollow inside and of one or several cooling air channels 18, the cooling air from the blade root to the tip of the blade.
- the shroud element 11 has on its top 22 two sealing ribs running parallel in the direction of movement of the blade tip 12 and 13, which together with the opposite housing wall 20 of the gas turbine form a cavity 21 connected to the surroundings by gaps.
- cooling bores 17 are on the input side with the cooling air duct 18 in connection and are supplied by this with cooling air.
- the cooling bores 17 do not extend all the way to the side End or edge of the shroud element 11, but each open from the side into an elongated, on the top 22 in the shroud element 11 recessed recess 14.
- each of the cooling holes 17 taken for themselves can be connected to a separate depression.
- the cooling holes 17 slightly oblique and parallel to each other to be different if it is to optimize cooling over the entire area of the shroud element 11 is necessary.
- the cooling bores 17 in the cooling arrangement shown are preferably produced using the so-called "STEM drilling" method, which is described in detail in US Pat. No. 5,306,401. This makes it possible (by changing the feed) to equip the surface of the cooling bores 17 with roughness, ribs or turbulators. This leads to significantly more efficient cooling because the shape of the cooling hole can be optimized. Furthermore, it is advantageous to provide the cooling bores 17, preferably on the inlet side, ie in the area of the cooling air supply on the profile 23, with a throttle point 19. This makes it possible to limit the cooling air mass flow in a targeted manner and to obtain significantly more efficient cooling.
- the embodiment according to FIG. 2 differs from that according to FIG.
- cooling bores 17 are designed as a diffuser or similar to a diffuser from the throttle point 19, which is arranged on the input side of each cooling bore.
- the cooling holes have an oval configuration. This, like the provision of internal roughness or the diffuser-like enlargement, increases the effective surface available for heat transfer.
- the cooling bores 17 can have different configurations than those described above. As such, regular or irregular depressions or corrugations are conceivable.
- the cooling bores 17 emerge on the side edge 25 of the shroud element 11.
- the side edges 25 of the shroud elements 11 are, however, designed such that adjacent elements 11 are only in contact in some areas, but the area of the emerging cooling bores is in contrast recessed in a recess 15. Between the adjacent elements, the opposite depressions 15 form gaps 26 into which the cooling air enters.
- This design reliably prevents the mouths from being closed by adjacent shroud elements. It ensures that the cooling air can always pass through the cooling bores 17, even if two adjacent cover band elements 11 are in mechanical contact.
- the cooling air entering the gap 26 from the two adjacent elements 11 is divided into two partial flows.
- the ratio of the two partial flows can be influenced by the design of the gap.
- the top and bottom sides can have a different gap width or the boundary walls can be inclined or differently designed in terms of flow technology.
- FIG 8 shows an embodiment with a coolant outlet on the underside of the Shroud element.
- the cooling bores 17 open laterally into the recess 16. According to this variant, the mixing temperature in the area of the bottom of the Cover band lowered and thus the thermal load is reduced.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Die vorliegende Erfindung bezieht sich auf das Gebiet der Gasturbinen. Sie betrifft eine luftgekühlte Turbinenschaufel, welche an der Schaufelspitze ein sich senkrecht zur Schaufellängsachse erstreckendes Deckbandelement aufweist, wobei das Deckbandelement zum Zwecke der Kühlung von einer Mehrzahl von Kühlbohrungen durchzogen ist, welche eingangsseitig mit wenigstens einem durch die Turbinenschaufel zur Schaufelspitze verlaufenden Kühlluftkanal in Verbindung stehen und ausgangsseitig in den die Turbinenschaufel umgebenden Aussenraum münden.The present invention relates to the field of gas turbines. It affects an air-cooled turbine blade, which is vertical at the tip of the blade to the blade longitudinal axis extending shroud element, wherein the shroud element for the purpose of cooling a plurality of cooling holes is crossed, which on the input side with at least one through the Turbine blade in connection with the cooling air duct running at the tip of the blade stand and on the output side in the outside space surrounding the turbine blade flow out.
Gattungsgemässe Turbinenschaufeln sind aus DE 198 13 173 A1 oder aus US 5,785,496 bekannt.Generic turbine blades are from DE 198 13 173 A1 or from US 5,785,496.
Moderne Gasturbinen arbeiten bei extrem hohen Temperaturen. Dies erfordert eine intensive Kühlung der Turbinenschaufeln. Eine besondere Schwierigkeit besteht darin, die exponierten Bereiche der Schaufeln zuverlässig zu kühlen. Einer dieser Bereiche sind das Deckband bzw. die Deckbandelemente der Schaufel. Eine Möglichkeit der Kühlung von Deckbandelementen ist in der eingangs genannten Druckschrift DE 198 13 173 A1 beschrieben worden. Dort wird vorgeschlagen (siehe die dortigen Fig. 3 und 4), die Deckbandelemente durch eine Reihe paralleler Kühlbohrungen zu kühlen, die sich von der (zentralen) Laufschaufel durch das Deckbandelement hindurch zur äusseren Kante des Deckbandelementes hin erstrecken und dort in den Aussenraum münden.Modern gas turbines operate at extremely high temperatures. This requires intensive cooling of the turbine blades. There is a particular difficulty in reliably cooling the exposed areas of the blades. One these areas are the shroud or shroud elements of the blade. One possibility for cooling shroud elements is in the above Document DE 198 13 173 A1 has been described. It is suggested there (see FIGS. 3 and 4 there), the shroud elements by a row parallel cooling bores to cool off from the (central) blade through the shroud element to the outer edge of the shroud element stretch out and open into the outside space.
Diese bekannte Lösung hat allerdings die folgenden Nachteile:
- Stossen zwei Deckbandelemente benachbarter Schaufeln seitlich aneinander (wie dies z.B. aus Fig. 3 der US 5,482,435 zu ersehen ist), werden die Mündungen der Kühlbohrungen zumindest teilweise verschlossen. Dies behindert Kühlluftaustritt und -verteilung. Das Deckbandelement wird im Betrieb überhitzt.
- Die bekannte Deckbandkühlung ändert wegen der seitlich angeordneten Mündungen nicht die Überströmbedingungen über das Deckband, das heisst, Druck und Temperatur auf der Oberseite des Deckbandes bleiben gleich. Dies wird auch nicht dadurch geändert, dass- wie in der US 5,460,486 vorgeschlagen - gewisse Kühlbohrungen auf der Unterseite des Deckbandelementes münden.
- Die Kühlwirkung beruht hauptsächlich auf der durch Vermischung der austretenden Kühlluft mit dem Heissgas abgesenkten Mischtemperatur in der Deckband umgebung. Es werden in den Kühlbohrungen keine Massnahmen getroffen, um den Wärmeübergang zwischen der Kühlluft und dem Deckbandelement zu intensivieren.
- If two cover band elements of adjacent blades abut one another laterally (as can be seen, for example, from FIG. 3 of US Pat. No. 5,482,435), the mouths of the cooling bores are at least partially closed. This prevents cooling air from escaping and distributing. The shroud element is overheated during operation.
- The known shroud cooling does not change the overflow conditions over the shroud because of the laterally arranged mouths, that is, pressure and temperature on the top of the shroud remain the same. This is also not changed by the fact that, as proposed in US Pat. No. 5,460,486, certain cooling bores open on the underside of the shroud element.
- The cooling effect is mainly due to the reduced mixing temperature in the shroud environment due to the mixing of the emerging cooling air with the hot gas. No measures are taken in the cooling holes to intensify the heat transfer between the cooling air and the shroud element.
Es ist daher Aufgabe der Erfindung, eine Turbinenschaufel mit luftgekühltem Deckbandelement zu schaffen, bei welcher die genannten Nachteile auf einfache Weise vermieden werden, und die sich durch eine wirksame Kühlung des Deckbandelementes, insbesondere auch auf der exponierten Oberseite des Deckbandelementes, auszeichnet.It is therefore an object of the invention to provide a turbine blade with air-cooled To create shroud element in which the disadvantages mentioned in a simple Be avoided, and which are due to effective cooling of the shroud element, especially on the exposed top of the shroud element, distinguished.
Die Aufgabe wird durch die Gesamtheit der Merkmale des Anspruchs 1 gelöst. Vorteilhafte Ausführungsformen geben die Unteransprüche wieder.The object is achieved by the entirety of the features of claim 1. Advantageous embodiments reflect the subclaims.
Der Grundgedanke der Erfindung besteht darin, die Kühlbohrungen zum einen so
durch das Deckbandelement zu führen, dass ein hoher Wärmeübergang zwischen
Deckbandelement und Kühlluft gewährleistet ist und zum anderen diese Bohrungen
so in den Aussenraum münden zu lassen, dass die exponierten Regionen des
Deckbandes zuverlässig mit der Kühlluft beaufschlagt und zusätzlich gekühlt werden.
Dies wird erreicht, indem vom Kühlkanal der Schaufel ausgehend im Bereich des
Deckbandelements die Kühlbohrungen im wesentlichen parallel zur Bewegungsrichtung
der Schaufelspitze von innen nach aussen verlaufen und jeweils vor dem
äusseren Rand des Deckbandelementes in eine zum Aussenraum hin offene Vertiefung
der Oberfläche münden.The basic idea of the invention is, on the one hand, to guide the cooling bores through the shroud element in such a way that a high heat transfer between the shroud element and cooling air is ensured and, on the other hand, to allow these bores to open into the outside space in such a way that the exposed regions of the shroud reliably depend on Cooling air is applied and additionally cooled.
This is achieved by proceeding from the cooling channel of the blade in the area of the shroud element, the cooling holes running essentially parallel to the direction of movement of the shovel tip from the inside to the outside and each opening in front of the outer edge of the shroud element in a recess in the surface open to the outside.
In einer ersten bevorzugten Ausführungsform der Erfindung sind dabei in das
Deckbandelement nahe dem Aussenrand von der Oberseite her Vertiefungen eingelassen,
in die die Kühlbohrungen seitlich münden.
Durch Vermischen der austretenden Kühlluft mit den heissen Verbrennungsgasen,
welche über die Oberseite des Deckbandelementes strömen, wird die Temperatur
in diesem Bereich wirksam herabgesetzt und so eine Überhitzung des Deckbandes
vermieden. Hierdurch wird eine gleichmässige Kühlung des Deckbandelements
über die gesamte Fläche erreicht.
Neben einer wirkungsvollen Kühlung der Deckbandoberseite hat diese Konfiguration
auch den Vorteil einer sehr einfachen Herstellung.
Besonders wirksam ist der Auslass der Kühlluft auf der Oberseite des Deckbandelementes,
wenn gemäss einer bevorzugten Weiterbildung auf der Oberseite des
Deckbandelementes parallel zueinander verlaufende, voneinander beabstandete
Dichtrippen vorgesehen sind, welche im Zusammenwirken mit der gegenüberliegenden
Gehäusewand der Gasturbine eine Kavität bilden, und die Kühlbohrungen
in diese Kavität münden. Die austretende Kühlluft führt zu einem Druckaufbau in
der Kavität, in dessen Folge das Eindringen von Heissgasen vermindert wird.In a first preferred embodiment of the invention, recesses are made in the cover band element near the outer edge from the top, into which the cooling holes open laterally.
By mixing the emerging cooling air with the hot combustion gases that flow over the top of the shroud element, the temperature in this area is effectively reduced and overheating of the shroud is avoided. As a result, uniform cooling of the shroud element is achieved over the entire area.
In addition to effective cooling of the top of the shroud, this configuration also has the advantage of very simple manufacture.
The outlet of the cooling air on the top of the shroud element is particularly effective if, according to a preferred development, mutually spaced sealing ribs are provided on the top of the shroud element, which form a cavity in cooperation with the opposite housing wall of the gas turbine, and the cooling holes in open this cavity. The escaping cooling air leads to a pressure build-up in the cavity, as a result of which the penetration of hot gases is reduced.
Nach einer anderen Ausführungsform der Erfindung besitzen die Seitenkanten der Deckbandelemente Ausnehmungen, in die die Kühlbohrungen münden. Die Ausnehmungen gegenüberliegender Deckbandelemente bilden dabei einen Spalt. Beim Austritt in den Spalt teilt sich die Kühlluft in zwei Teilströme auf. Ein Teil strömt zur Oberseite hin und speist die erwähnte Kavität zwischen den beabstandeten Dichtrippen mit der oben erwähnten Wirkung. Der andere Teil strömt zur Deckbandunterseite und mischt sich dort mit den Heissgasen unter Einstellung einer Mischtemperatur, die die thermische Belastung in diesem Bereich verringert. Durch die Spaltgeometrie kann das Verhältnis der nach oben und unten abströmenden Teilmengen beeinflusst werden.According to another embodiment of the invention, the side edges of the Shroud elements recesses into which the cooling holes open. The recesses Opposing shroud elements form a gap. When exiting into the gap, the cooling air is divided into two partial flows. A part flows to the top and feeds the cavity mentioned between the spaced Sealing ribs with the above-mentioned effect. The other part flows to Underside of the cover tape and mixes there with the hot gases under setting a mixing temperature that reduces the thermal load in this area. Due to the gap geometry, the ratio of those flowing up and down can Partial quantities are influenced.
In einer zweckmässigen Ergänzung der Erfindung wird ferner vorgeschlagen, in
den Kühlbohrungen Mittel zur Verbesserung des Wärmeübergangs zwischen
Kühlluft und Deckbandelement vorzusehen.
Die Mittel zur Verbesserung des Wärmeübergangs an den Bohrungswänden können
Rauhigkeiten, Rippen und/oder Turbulatoren umfassen. In an sich bekannter
Weise können die Bohrungen mittels des sogenannten "STEM drilling"-Prozesses
erstellt werden. Insbesondere durch das "STEM drilling", das beispielsweise in der
US 5,306,401 im Zusammenhang mit der Herstellung von Kühllöchern in Turbinenschaufeln
beschrieben worden ist, lassen sich einfach und zuverlässig Kühlbohrungen
mit verbesserten Wärmeübergangseigenschaften erzeugen.In an expedient addition to the invention, it is further proposed to provide means for improving the heat transfer between the cooling air and the shroud element in the cooling bores.
The means for improving the heat transfer on the bore walls can include roughness, ribs and / or turbulators. In a manner known per se, the holes can be created using the so-called "STEM drilling" process. In particular, "STEM drilling", which has been described, for example, in US Pat. No. 5,306,401 in connection with the production of cooling holes in turbine blades, can be used to produce cooling bores with improved heat transfer properties simply and reliably.
Eine bessere Ausnutzung der Kühlluft kann weiterhin erreicht werden, wenn gemäss einer anderen bevorzugten Ausführungsform der Erfindung in den Kühlbohrungen jeweils eine Drosselstelle zur Begrenzung des Kühlluftmassenstromes vorgesehen ist, und die Drosselstellen jeweils an der Eingangsseite der Kühlbohrungen angeordnet sind. Better utilization of the cooling air can still be achieved if according to another preferred embodiment of the invention in the cooling bores one throttle point each to limit the cooling air mass flow is provided, and the throttle points on the input side of the cooling holes are arranged.
Die Erfindung soll nachfolgend anhand von Ausführungsbeispielen im Zusammenhang mit der Zeichnung näher erläutert werden. Es zeigen
- Fig.1
- Draufsicht einer bevorzugten Ausführungsform der Turbinenschaufel mit zur Deckbandoberseite hin austretenden Kühlbohrungen
- Fig.2
- eine weitere Ausführungsform gemäss Fig.1 mit diffusorartigen Kühlbohrungen
- Fig.3
- Seitenansicht eines Deckbandelements gemäss Fig.1 mit Kühlbohrungen von kreisförmigem Querschnitt
- Fig.4
- Seitenansicht eines Deckbandelements gemäss Fig.1 mit Kühlbohrungen von ovalem Querschnitt
- Fig.5
- Teilschnittdarstellung eines Deckbandelements gemäss Fig.1
- Fig.6
- Draufsicht zweier Deckbandelemente in einer Ausführungsform mit zur Seitenkante hin austretenden Kühlbohrungen
- Fig.7
- Teilschnittdarstellung eines Deckbandelements gemäss Fig.6
- Fig.8
- Teilschnittdarstellung eines Deckbandelements mit Kühlluftaustritt zur Unterseite des Deckbandelements hin
- Fig. 1
- Top view of a preferred embodiment of the turbine blade with cooling bores emerging toward the top of the shroud
- Fig. 2
- a further embodiment according to Figure 1 with diffuser-like cooling bores
- Fig. 3
- Side view of a shroud element according to Figure 1 with cooling holes of circular cross-section
- Fig. 4
- Side view of a shroud element according to Figure 1 with cooling holes of oval cross-section
- Fig. 5
- Partial sectional view of a shroud element according to Fig.1
- Fig. 6
- Top view of two cover band elements in one embodiment with cooling bores emerging towards the side edge
- Fig. 7
- Partial sectional view of a shroud element according to FIG. 6
- Fig. 8
- Partial sectional view of a shroud element with cooling air outlet towards the underside of the shroud element
In Fig. 1 ist in der Draufsicht eine bevorzugte Ausführungsform einer Turbinenschaufel
nach der Erfindung dargestellt. Die Turbinenschaufel 10 umfasst das eigentliche
Schaufelprofil 23 und ein quer dazu an der Schaufelspitze angeordnetes
Deckbandelement 11, welches zusammen mit den Deckbandelementen der anderen
(nicht gezeigten) Schaufeln ein durchgehendes, mechanisch stabilisierendes
Deckband ergibt. Das Schaufelprofil 23 ist im Inneren teilweise hohl und von einem
oder mehreren Kühlluftkanälen 18 durchzogen, die Kühlluft vom Schaufelfuss
bis in die Schaufelspitze leiten. Das Deckbandelement 11 hat auf seiner Oberseite
22 zwei parallel in Bewegungsrichtung der Schaufelspitze verlaufende Dichtrippen
12 und 13, die zusammen mit der gegenüberliegenden Gehäusewand 20 der Gasturbine
eine durch Spalte mit der Umgebung verbundene Kavität 21 bilden.
Im Inneren des Deckbandelementes 11 verlaufen zwischen und im wesentlichen
parallel zu den Rippen 12, 13 mehrere Kühlbohrungen 17 von der Mitte ausgehend
nach aussen. Die Kühlbohrungen 17 stehen eingangsseitig mit dem Kühlluftkanal
18 in Verbindung und werden von diesem mit Kühlluft versorgt. Wie aus Fig.
1 zu entnehmen ist, erstrecken sich die Kühlbohrungen 17 nicht ganz bis zum seitlichen
Ende bzw. Rand des Deckbandelementes 11, sondern münden jeweils von
der Seite her in eine längliche, auf der Oberseite 22 in das Deckbandelement 11
eingelassene Vertiefung 14. Es versteht sich von selbst, dass anstelle einer
durchgehenden Vertiefung 14 auch jede der Kühlbohrungen 17 für sich genommen
mit einer separaten Vertiefung in Verbindung stehen kann. Weiterhin ist es
auch denkbar, die Kühlbohrungen 17 leicht schräg und von einer Parallelität untereinander
abweichend verlaufen zu lassen, wenn es zur Optimierung der Kühlung
über die gesamte Fläche des Deckbandelementes 11 nötig ist.1 shows a top view of a preferred embodiment of a turbine blade
shown according to the invention. The
Weiterhin führt ein Ausblasen der Kühlluft nach oben zu einem "Aufblasen" der
Kavität 21 zwischen Deckband und Gehäuse 20. Dies führt zu einer Erhöhung des
Druckes in der Kavität und trägt damit zu einer Verkleinerung des eindringenden
Massenstromes an Heissgas 24 bei. Weiterhin wird natürlich auch die Mischtemperatur
in diesem Bereich abgesenkt, wodurch die thermische Belastung des
Deckbandelementes 11 von der Oberseite 22 her verringert wird.Furthermore, blowing the cooling air upwards leads to an "inflation" of the
Die Kühlbohrungen 17 in der gezeigten Kühlungsanordnung werden vorzugsweise
mit dem sogenannten "STEM drilling"-Verfahren hergestellt, das in der US
5,306,401 in allen Einzelheiten beschrieben ist. Dadurch ist es (durch Veränderung
des Vorschubs) möglich, die Oberfläche der Kühlbohrungen 17 mit Rauhigkeiten,
Rippen oder Turbulatoren auszurüsten. Dies führt zu einer deutlich effizienteren
Kühlung, weil die Form der Kühlbohrung optimiert werden kann. Weiterhin
ist es vorteilhaft, die Kühlbohrungen 17, vorzugsweise eingangsseitig, d.h. im Bereich
der Kühlluftversorgung am Profil 23, jeweils mit einer Drosselstelle 19 auszustatten.
Dadurch wird es möglich, den Kühlluftmassenstrom gezielt zu begrenzen
und eine deutlich effizientere Kühlung zu erhalten.
Die Ausführungsform gemäss Fig.2 unterscheidet sich von jener gemäss Fig.1
darin, dass die Kühlbohrungen 17 ab der Drosselstelle 19, welche jeweils an der
Eingangsseite jeder Kühlbohrung angeordnet ist, als Diffusor oder diffusorähnlich
ausgebildet sind.
Nach einer weiteren Ausführungsform - dargestellt in Fig.4 - weisen die Kühlbohrungen
eine ovale Konfiguration auf. Dies erhöht, wie die Ausrüstung mit inneren
Rauhigkeiten oder die diffusorartige Erweiterung, die zur Wärmeübertragung zur
Verfügung stehende wirksame Oberfläche.
Die Kühlbohrungen 17 können darüber hinaus oder alternativ andere Konfigurationen
aufweisen als die oben beschriebenen. Als solche sind beispielsweise regelmässig
oder unregelmässig gehaltene Vertiefungen oder Wellungen denkbar.The cooling bores 17 in the cooling arrangement shown are preferably produced using the so-called "STEM drilling" method, which is described in detail in US Pat. No. 5,306,401. This makes it possible (by changing the feed) to equip the surface of the cooling bores 17 with roughness, ribs or turbulators. This leads to significantly more efficient cooling because the shape of the cooling hole can be optimized. Furthermore, it is advantageous to provide the cooling bores 17, preferably on the inlet side, ie in the area of the cooling air supply on the
The embodiment according to FIG. 2 differs from that according to FIG. 1 in that the cooling bores 17 are designed as a diffuser or similar to a diffuser from the
According to a further embodiment - shown in Figure 4 - the cooling holes have an oval configuration. This, like the provision of internal roughness or the diffuser-like enlargement, increases the effective surface available for heat transfer.
In addition, or alternatively, the cooling bores 17 can have different configurations than those described above. As such, regular or irregular depressions or corrugations are conceivable.
In einer weiteren günstigen Ausgestaltung der Erfindung nach Fig. 6 und 7 treten
die Kühlbohrungen 17 an der Seitenkante 25 des Deckbandelements 11 aus.
Zur Vermeidung der Nachteile des Standes der Technik sind die Seitenkanten 25
der Deckbandelemente 11 aber so ausgeführt, dass benachbarte Elemente 11 nur
bereichsweise in Kontakt stehen, der Bereich der austretenden Kühlbohrungen
aber demgegenüber in einer Vertiefung 15 zurückgenommen ist. Zwischen den
benachbarten Elementen bilden die gegenüberliegenden Vertiefungen 15 Spalte
26, in die die Kühlluft eintritt .
Diese Ausführung verhindert zuverlässig ein Verschliessen der Mündungen durch
benachbarte Deckbandelemente. Sie gewährleistet, dass die Kühlluft immer durch
die Kühlbohrungen 17 hindurchtreten kann, auch wenn zwei benachbarte Deckbandelemente
11 in mechanischem Kontakt stehen.
Die aus beiden benachbarten Elementen 11 in den Spalt 26 eintretende Kühlluft
teilt sich in zwei Teilströme auf. Ein Teilstrom strömt nach oben und führt zu einem
Aufblasen der Kavität 21 oberhalb des Deckbandes, während der andere Teilstrom
auf die Unterseite des Deckbandes gelangt und sich dort mit den Heissgasen
mischt. Die sich einstellende Mischtemperatur verringert die thermische Belastung
in diesem Bereich.
Durch die konstruktive Gestaltung des Spaltes kann das Mengenverhältnis der
beiden Teilströme beeinflusst werden. So können Ober- und Unterseite eine unterschiedliche
Spaltweite aufweisen oder die Begrenzungswände geneigt oder
strömungstechnisch unterschiedlich ausgebildet sein.In a further advantageous embodiment of the invention according to FIGS. 6 and 7, the cooling bores 17 emerge on the
This design reliably prevents the mouths from being closed by adjacent shroud elements. It ensures that the cooling air can always pass through the cooling bores 17, even if two adjacent
The cooling air entering the
The ratio of the two partial flows can be influenced by the design of the gap. For example, the top and bottom sides can have a different gap width or the boundary walls can be inclined or differently designed in terms of flow technology.
Fig.8 zeigt eine Ausführungsform mit Kühlmittelaustritt auf der Unterseite des
Deckbandelements. Die Kühlbohrungen 17 münden seitlich in die Vertiefung 16.
Nach dieser Variante wird die Mischtemperatur im Bereich der Unterseite des
Deckbandes abgesenkt und damit die thermische Belastung verringert. 8 shows an embodiment with a coolant outlet on the underside of the
Shroud element. The cooling bores 17 open laterally into the
- 1010th
- TurbinenschaufelTurbine blade
- 1111
- DeckbandelementShroud element
- 12,1312.13
- DichtrippenSealing ribs
- 14,15,1614,15,16
- Vertiefungdeepening
- 1717th
- KühlbohrunqCooling drilling
- 1818th
- KühlluftkanalCooling air duct
- 1919th
- DrosselstelleThrottling point
- 2020th
- GehäusewandHousing wall
- 2121
- Kavitätcavity
- 2222
- Oberseite (Deckbandelement)Top (cover band element)
- 2323
- SchaufelprofilBucket profile
- 2424th
- HeissgasHot gas
- 2525th
- Aussenkante des DeckbandelementsOuter edge of the shroud element
- 2626
- Spalt zwischen den DeckbandelementenGap between the cover band elements
Claims (14)
dadurch gekennzeichnet, dass
die Kühlbohrungen (17) in dem Deckbandelement (11) zumindest annähernd parallel zur Bewegungsrichtung der Schaufel (10) von innen nach aussen verlaufen und jeweils vor dem äusseren Rand (25) des Deckbandelements (11) in eine zum Aussenraum hin offene Oberflächenvertiefung (14) und/oder (15) münden.Air-cooled turbine blade (10), which has at the blade tip a cover band element (11) extending perpendicular to the longitudinal axis of the blade, the cover band element (11) being passed through for cooling purposes a plurality of cooling bores (17) which are connected on the input side with at least one through the turbine blade ( 10) are connected to the cooling air duct (18) which extends to the blade tip, and open on the outlet side into the outer space surrounding the turbine blade (10),
characterized in that
the cooling bores (17) in the shroud element (11) run at least approximately parallel to the direction of movement of the blade (10) from the inside out and in each case in front of the outer edge (25) of the shroud element (11) into a surface recess (14) which is open to the outside space and / or (15) open.
dadurch gekennzeichnet, dass
die zum Aussenraum hin offene Vertiefung (14) auf der Oberseite (22) des Deckbandelements (11) angeordnet ist und die Kühlbohrungen (17) seitlich in diese Vertiefung (14) münden.Turbine blade according to claim 1,
characterized in that
the recess (14) open to the outside is arranged on the top (22) of the shroud element (11) and the cooling bores (17) open laterally into this recess (14).
dadurch gekennzeichnet, dass
die zum Aussenraum hin offene Vertiefung (15) an der Seitenkante (25) des Deckbandelements (11) angeordnet ist.Turbine blade according to claim 1,
characterized in that
the recess (15) open to the outside is arranged on the side edge (25) of the shroud element (11).
dadurch gekennzeichnet, dass
auf der Oberseite (22) des Deckbandelementes (11) mindestens zwei parallel zur Bewegungsrichtung der Schaufel verlaufende, voneinander beabstandete Dichtrippen (12, 13) vorgesehen sind, welche im Zusammenwirken mit der gegenüberliegenden Gehäusewand (20) der Gasturbine eine Kavität (21) bilden.Turbine blade according to one of claims 1 to 3,
characterized in that
On the top (22) of the shroud element (11) there are at least two spaced apart sealing ribs (12, 13) which run parallel to the direction of movement of the blade and which, in cooperation with the opposite housing wall (20) of the gas turbine, form a cavity (21).
dadurch gekennzeichnet, dass
die Kühlbohrungen (17) über die Vertiefungen (14) in die Kavität (21) münden.Turbine blade according to claim 4,
characterized in that
the cooling bores (17) open into the cavity (21) via the depressions (14).
dadurch gekennzeichnet, dass
die Kühlbohrungen (17) in einen von den Vertiefungen (15) gebildeten Spalt (26) münden, und zumindest ein Teilstrom der dort austretenden Kühlluft in die Kavität (21) einströmt.Turbine blade according to claim 4,
characterized in that
the cooling bores (17) open into a gap (26) formed by the depressions (15), and at least a partial flow of the cooling air emerging there flows into the cavity (21).
dadurch gekennzeichnet, dass
das Mengenverhältnis der aus dem Spalt (26) in Richtung Deckbandoberseite und -unterseite austretenden Teilströme durch die Spaltgeometrie gesteuert wird.Turbine blade according to claim 6,
characterized in that
the quantity ratio of the partial flows emerging from the gap (26) in the direction of the top and bottom of the shroud is controlled by the gap geometry.
dadurch gekennzeichnet, dass
in den Kühlbohrungen (17) Mittel zur Verbesserung des Wärmeübergangs zwischen Kühlluft und Deckbandelement (11) vorgesehen sind.Turbine blade according to one of claims 1 to 7,
characterized in that
means for improving the heat transfer between cooling air and shroud element (11) are provided in the cooling bores (17).
dadurch gekennzeichnet, dass
die Mittel zur Verbesserung des Wärmeübergangs an den Bohrungswänden (17) Rauhigkeiten, Rippen und/oder Turbulatoren, umfassen. Turbine blade according to claim 8,
characterized in that
the means for improving the heat transfer on the bore walls (17) include roughness, ribs and / or turbulators.
dadurch gekennzeichnet, dass
die Kühlbohrungen (17) mittels des sogenannten "STEM drilling"-Prozesses hergestellt sind.Turbine blade according to claim 9,
characterized in that
the cooling bores (17) are produced by means of the so-called "STEM drilling" process.
dadurch gekennzeichnet, dass
in den Kühlbohrungen (17) jeweils eine Drosselstelle (19) zur Begrenzung des Kühlluftmassenstromes vorgesehen ist.Turbine blade according to claim 1,
characterized in that
A throttle point (19) for limiting the cooling air mass flow is provided in each of the cooling bores (17).
dadurch gekennzeichnet, dass
die Drosselstellen (19) jeweils an der Eingangsseite der Kühlbohrungen (17) angeordnet sind.Turbine blade according to claim 11,
characterized in that
the throttling points (19) are each arranged on the input side of the cooling bores (17).
dadurch gekennzeichnet, dass
die Kühlbohrungen (17) einen ovalen Querschnitt besitzen.Turbine blade according to claim 1,
characterized in that
the cooling holes (17) have an oval cross section.
dadurch gekennzeichnet, dass
die Kühlbohrungen (17) in Strömungsrichtung einen Diffusor bilden oder diffusorähnlich ausgebildet sind.Turbine blade according to claim 1,
characterized in that
the cooling bores (17) form a diffuser in the flow direction or are designed like a diffuser.
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19860244 | 1998-12-24 | ||
DE19860244A DE19860244B4 (en) | 1998-12-24 | 1998-12-24 | Turbine blade with actively cooled shroud element |
DE19860245 | 1998-12-24 | ||
DE19860245A DE19860245A1 (en) | 1998-12-24 | 1998-12-24 | Air cooled blade for gas turbine has cooling holes in shroud element running from inside outwards and parallel to direction of blade's movement, with each cooling hole opening out into surface recess before outer edge of shroud element |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1013884A2 true EP1013884A2 (en) | 2000-06-28 |
EP1013884A3 EP1013884A3 (en) | 2003-11-05 |
EP1013884B1 EP1013884B1 (en) | 2005-07-27 |
Family
ID=26051058
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP99811187A Expired - Lifetime EP1013884B1 (en) | 1998-12-24 | 1999-12-21 | Turbine blade with actively cooled head platform |
Country Status (4)
Country | Link |
---|---|
US (1) | US6340284B1 (en) |
EP (1) | EP1013884B1 (en) |
CN (1) | CN1260442A (en) |
DE (1) | DE59912323D1 (en) |
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EP1126136A2 (en) * | 1999-12-28 | 2001-08-22 | ALSTOM (Schweiz) AG | Turbine blade with air cooled tip shroud |
EP1267042A2 (en) * | 2001-06-14 | 2002-12-18 | Mitsubishi Heavy Industries, Ltd. | Shrouded gas turbine blade |
US7273347B2 (en) | 2004-04-30 | 2007-09-25 | Alstom Technology Ltd. | Blade for a gas turbine |
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EP2657452A1 (en) * | 2010-12-22 | 2013-10-30 | Mitsubishi Heavy Industries, Ltd. | Turbine |
EP2290193A3 (en) * | 2009-08-18 | 2014-07-16 | United Technologies Corporation | Turbine vane platform leading edge cooling holes |
EP3550111A1 (en) * | 2018-04-06 | 2019-10-09 | United Technologies Corporation | Turbine blade shroud for gas turbine engine with power turbine and method of manufacturing same |
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EP1126136A2 (en) * | 1999-12-28 | 2001-08-22 | ALSTOM (Schweiz) AG | Turbine blade with air cooled tip shroud |
EP1126136A3 (en) * | 1999-12-28 | 2004-05-19 | ALSTOM Technology Ltd | Turbine blade with air cooled tip shroud |
EP1267042A2 (en) * | 2001-06-14 | 2002-12-18 | Mitsubishi Heavy Industries, Ltd. | Shrouded gas turbine blade |
EP1267042A3 (en) * | 2001-06-14 | 2009-06-17 | Mitsubishi Heavy Industries, Ltd. | Shrouded gas turbine blade |
US7273347B2 (en) | 2004-04-30 | 2007-09-25 | Alstom Technology Ltd. | Blade for a gas turbine |
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EP2290193A3 (en) * | 2009-08-18 | 2014-07-16 | United Technologies Corporation | Turbine vane platform leading edge cooling holes |
WO2011045346A1 (en) * | 2009-10-15 | 2011-04-21 | Abb Turbo Systems Ag | Turbine wheel |
EP2657452A1 (en) * | 2010-12-22 | 2013-10-30 | Mitsubishi Heavy Industries, Ltd. | Turbine |
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Also Published As
Publication number | Publication date |
---|---|
US6340284B1 (en) | 2002-01-22 |
DE59912323D1 (en) | 2005-09-01 |
EP1013884B1 (en) | 2005-07-27 |
CN1260442A (en) | 2000-07-19 |
EP1013884A3 (en) | 2003-11-05 |
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