EP1013884B1 - Turbine blade with actively cooled head platform - Google Patents
Turbine blade with actively cooled head platform Download PDFInfo
- Publication number
- EP1013884B1 EP1013884B1 EP99811187A EP99811187A EP1013884B1 EP 1013884 B1 EP1013884 B1 EP 1013884B1 EP 99811187 A EP99811187 A EP 99811187A EP 99811187 A EP99811187 A EP 99811187A EP 1013884 B1 EP1013884 B1 EP 1013884B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- cooling
- turbine blade
- shroud
- shroud band
- blade according
- 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.)
- Expired - Lifetime
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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
-
- 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
- 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
-
- 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 concerns an air cooled turbine blade which is perpendicular to the blade tip Has to the blade longitudinal axis extending shroud element, wherein the shroud element for the purpose of cooling a plurality of cooling holes is traversed, which input side with at least one through the Turbine blade to the blade tip extending cooling air duct in conjunction stand and on the output side in the outer space surrounding the turbine blade lead.
- the basic idea of the invention consists in the side edges of the shroud elements To arrange recesses into which the cooling holes open.
- the recesses of opposite shroud elements form a Gap.
- the cooling air is divided into two partial flows. One Part flows to the top and feeds a cavity between the spaced ones Sealing ribs.
- the other part flows to the shroud bottom and mixes there with the hot gases under adjustment of a mixing temperature, which is the thermal Reduced load in this area. Due to the gap geometry, the ratio the up and down flowing subsets influenced.
- Cooling holes Means for improving the heat transfer between cooling air and shroud element are proposed.
- the means for improving the heat transfer at the bore walls can Roughnesses, ribs and / or turbulators include.
- the drilling can be done by means of the so-called “STEM drilling” process to be created.
- STEM drilling for example, in the US-A-5,306,401 in connection with the manufacture of cooling holes in turbine blades has been described, can be easily and reliably cooling holes produce with improved heat transfer properties.
- a preferred embodiment of a turbine blade according to the invention is shown in plan view.
- the turbine blade 10 comprises the actual blade profile 23 and a shroud element 11 arranged transversely thereto on the blade tip, which together with the shroud elements of the other blades (not shown) results in a continuous, mechanically stabilizing shroud.
- the blade profile 23 is partially hollow in the interior and traversed by one or more cooling air channels 18, which guide cooling air from the blade root to the blade tip.
- the shroud element 11 has on its upper side 22 two parallel running in the direction of movement of the blade tip sealing ribs 12 and 13, which together with the opposite housing wall 20 of the gas turbine form a connected by gaps with the environment cavity 21.
- cooling holes 17 Inside the shroud element 11 extend between and substantially parallel to the ribs 12, 13 a plurality of cooling holes 17, starting from the center to the outside.
- the cooling holes 17 are on the input side with the cooling air duct 18 in connection and are supplied by this with cooling air.
- the cooling holes 17 do not extend entirely to the lateral end or edge of the shroud element 11, but each open from the side into an elongated, recessed on the top 22 in the shroud element 11 recess 15th Es It is conceivable that the cooling bores 17 run slightly obliquely and deviate from one another by parallelism, if it is necessary to optimize the cooling over the entire surface of the shroud element 11.
- the cooling holes 17 in the cooling arrangement shown are preferably manufactured using the so-called "STEM drilling" method described in the US Pat 5,306,401 is described in detail. This is what it is (through change the feed), the surface of the cooling holes 17 with roughness, Equip ribs or turbulators. This leads to a significantly more efficient Cooling, because the shape of the cooling hole can be optimized. Farther it is advantageous, the cooling holes 17, preferably on the input side, i. in the area the cooling air supply to the profile 23, each with a throttle point 19 equip. This makes it possible to selectively limit the cooling air mass flow and to obtain a much more efficient cooling.
- the embodiment according to FIG. 2 differs from that according to FIG. 1 in that the cooling bores 17 are designed as diffuser 16a or diffuser-like from the throttle point 19, which is arranged respectively on the inlet side of each cooling bore.
- the cooling holes have an oval configuration. This increases, like the equipment with internal roughness or the diffuser-like extension, the effective surface area available for heat transfer.
- the cooling holes 17 may additionally or alternatively have other configurations than those described above. As such, for example, regularly or irregularly held depressions or corrugations are conceivable.
- the side edges 25 of the shroud elements 11 but designed so that adjacent elements 11 are only partially in contact, the area of the exiting cooling holes but is withdrawn in contrast in a depression. Between the adjacent elements, the opposite recesses 15 form gaps 26 into which the cooling air enters.
- This embodiment reliably prevents closure of the mouths by adjacent shroud elements. It ensures that the cooling air can always pass through the cooling holes 17, even if two adjacent shroud elements 11 are in mechanical contact. The cooling air entering from the two adjacent elements 11 into the gap 26 is divided into two partial flows.
- a partial flow flows upward and leads to an inflation of the cavity 21 above the shroud and thus contributes to a reduction of the penetrating mass flow of hot gas 24, while the other partial flow reaches the underside of the shroud and there mixes with the hot gases.
- the resulting mixing temperature reduces the thermal load in this area. Due to the structural design of the gap, the quantitative ratio of the two partial flows can be influenced. Thus, the upper and lower sides can have a different gap width or the boundary walls can be inclined or fluidically designed differently.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
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 concerns an air cooled turbine blade which is perpendicular to the blade tip Has to the blade longitudinal axis extending shroud element, wherein the shroud element for the purpose of cooling a plurality of cooling holes is traversed, which input side with at least one through the Turbine blade to the blade tip extending cooling air duct in conjunction stand and on the output side in the outer space surrounding the turbine blade lead.
Gattungsgemässe Turbinenschaufeln sind aus DE 198 13 173 oder aus US 5,785,496 bekannt.Generic turbine blades are known from DE 198 13 173 or from US 5,785,496 known.
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 der Deckbandelemente ist in der eingangs genannten Druckschrift DE 198 13 173 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 erstrekken und dort in den Aussenraum münden.Modern gas turbines operate at extremely high temperatures. This requires intensive cooling of the turbine blades. A special difficulty exists to reliably cool the exposed areas of the blades. one These areas are the shroud or the shroud elements of the blade. One way of cooling the shroud elements is in the aforementioned Document DE 198 13 173 has been described. There it is proposed (See Figures 3 and 4 there), the shroud elements by a series of parallel Cooling cooling holes extending from the (central) blade through the Deckbandelement extend therethrough to the outer edge of the shroud element and there open into the outside space.
Eine weitere Möglichkeit zur Deckbandkühlung offenbart GB 1605335. Eine Anzahl paralleler Kühlbohrungen erstreckt sich in Rotationsrichtung durch das Deckbandelement und mündet in einer seitlichen Vertiefung. Das jeweils benachbarte Deckbandelement speist mit seinen Kühlbohrungen ebenfalls den durch die Vertiefung gebildeten Hohlraum und schliesst diesen gleichzeitig ab. Über weitere Kühlbohrungen gelangt die Kühlluft aus dem Hohlraum in den Aussenraum am oberen Rand des Deckbandes.Another possibility for shroud cooling disclosed GB 1605335. A number parallel cooling holes extends in the direction of rotation through the shroud element and flows into a lateral depression. The adjacent one Shroud element fed with its cooling holes also through the recess formed cavity and closes this at the same time. About more Cooling holes, the cooling air passes from the cavity in the outer space on upper edge of the shroud.
Die veröffentlichte japanische Patentanmeldung JP 58047104 offenbart eine Deckbandkühlung, die sich dadurch auszeichnet, dass die aus einem zentralen Kühlluftkanal der Schaufel den Deckbandelementen zugeführte Kühlluft über unterschiedliche Kühlluftpfade aufgeteilt wird, welche an unterschiedlichen Stellen des Deckbandes in den Aussenraum münden.Published Japanese Patent Application JP 58047104 discloses a Shroud cooling, which is characterized by the fact that from a central Cooling air duct of the blade the shroud elements supplied cooling air over different Cooling air paths is divided, which at different points of the shroud open into the outer space.
Diese bekannten Lösungen haben allerdings die folgenden Nachteile:
- Stossen zwei Deckbandelemente benachbarter Schaufeln seitlich aneinander (wie dies z.B. aus Fig. 3 der US-A-5,482,435 zu ersehen ist), werden die Mündungen der Kühlbohrungen zumindest teilweise verschlossen und das Deckbandelement wird im Betrieb überhitzt.
- Die bekannte Deckbandkühlung ändert wegen der seitlich angeordneten Mündungen nicht die Ueberströmbedingungen 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-A-5,460,486 vorgeschlagen - gewisse Kühlbohrungen auf der Unterseite des Deckbandelementes münden.
- Die Kühlwirkung beruht hautpsächlich auf der durch Vermischung der austretenden Kühlluft mit dem Heissgas abgesenkten Mischtemperatur in der Deckbandumgebung. Es werden in den Kühlbohrungen keine Massnahmen getroffen, um den Wärmeübergang zwischen der Kühlluft und dem Deckbandelement zu intensivieren.
- If two shroud 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 orifices of the cooling bores are at least partially closed and the shroud element is overheated during operation.
- The known shroud cooling does not change the overflow conditions on the shroud because of the laterally arranged mouths, that is, pressure and temperature on the top of the shroud remain the same. This is not changed by the fact that - as proposed in US-A-5,460,486 - certain cooling holes open on the underside of the shroud element.
- The cooling effect is based mainly on the lowered by mixing the exiting cooling air with the hot gas mixing temperature in the shroud environment. 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, indem die Kühlluftbohrungen so in den Aussenraum münden, dass die exponierten Regionen des Deckbandes zuverlässig mit der Kühlluft beaufschlagt und zusätzlich gekühlt werden.It is therefore an object of the invention to provide a turbine blade with air-cooled To create shroud element, wherein said disadvantages to simple Be avoided by the cooling air holes so in the outside space conclude that the exposed regions of the shroud reliably with the Cooling air applied and additionally cooled.
Die Aufgabe wird durch die Gesamtheit der Merkmale des Anspruchs 1 gelöst. Vorteilhafte Ausführungsformen geben die abhängigen Ansprüche wieder.The object is solved by the entirety of the features of claim 1. Advantageous embodiments give the dependent claims again.
Der Grundgedanke der Erfindung besteht darin, in den Seitenkanten der Deckbandelemente Ausnehmungen anzuordnen, 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 eine Kavität zwischen den beabstandeten Dichtrippen. 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 wird das Verhältnis der nach oben und unten abströmenden Teilmengen beeinflusst.The basic idea of the invention consists in the side edges of the shroud elements To arrange recesses into which the cooling holes open. The recesses of opposite shroud elements form a Gap. When exiting into the gap, the cooling air is divided into two partial flows. One Part flows to the top and feeds a cavity between the spaced ones Sealing ribs. The other part flows to the shroud bottom and mixes there with the hot gases under adjustment of a mixing temperature, which is the thermal Reduced load in this area. Due to the gap geometry, the ratio the up and down flowing subsets influenced.
In einer zweckmässigen Ergänzung der Erfindung wird vorgeschlagen, in den Kühlbohrungen Mittel zur Verbesserung des Wärmeübergangs zwischen Kühlluft und Deckbandelement vorzusehen. In an expedient supplement of the invention is proposed in the Cooling holes Means for improving the heat transfer between cooling air and shroud element.
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-A-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.The means for improving the heat transfer at the bore walls can Roughnesses, ribs and / or turbulators include. In known per se The drilling can be done by means of the so-called "STEM drilling" process to be created. In particular, by the "STEM drilling", for example, in the US-A-5,306,401 in connection with the manufacture of cooling holes in turbine blades has been described, can be easily and reliably cooling holes produce with improved heat transfer properties.
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 continue to be achieved if according to another preferred embodiment of the invention in the cooling holes in each case a throttle point for limiting the cooling air mass flow is provided, and the throttle points respectively at 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 zweier Deckbandelemente mit zur Seitenkante hin austretenden Kühlbohrungen
- Fig. 2
- Teilschnittdarstellung eines Deckbandelementes gemäss Fig. 6 in einer Ausführungsform mit sich diffusorartig erweiternden Kühlbohrungen
- Fig. 3
- Seitenansicht eines Deckbandelementes gemäss Fig. 1 mit Kühlbohrungen von kreisförmigem Querschnitt
- Fig. 4
- Seitenansicht eines Deckbandelementes gemäss Fig. 1 mit Kühlbohrungen von ovalem Querschnitt
- Fig. 1
- Top view of two shroud elements with exiting to the side edge cooling holes
- Fig. 2
- Partial sectional view of a shroud element according to FIG. 6 in an embodiment with diffuser-like widening cooling holes
- Fig. 3
- Side view of a shroud element according to FIG. 1 with cooling holes of circular cross-section
- Fig. 4
- Side view of a shroud element according to FIG. 1 with cooling holes of oval cross-section
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 entnehmen kann, 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
eingelassen Vertiefung 15. Es ist 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.In Fig. 1, a preferred embodiment of a turbine blade according to the invention is shown in plan view. The
Inside 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.The cooling holes 17 in the cooling arrangement shown are preferably
manufactured using the so-called "STEM drilling" method described in the US Pat
5,306,401 is described in detail. This is what it is (through change
the feed), the surface of the cooling holes 17 with roughness,
Equip ribs or turbulators. This leads to a significantly more efficient
Cooling, because the shape of the cooling hole can be optimized. Farther
it is advantageous, the cooling holes 17, preferably on the input side, i. in the area
the cooling air supply to the
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 16a 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 embodiment according to FIG. 2 differs from that according to FIG. 1 in that the cooling bores 17 are designed as diffuser 16a or diffuser-like from the
According to a further embodiment - shown in Figure 4 - the cooling holes have an oval configuration. This increases, like the equipment with internal roughness or the diffuser-like extension, the effective surface area available for heat transfer.
The cooling holes 17 may additionally or alternatively have other configurations than those described above. As such, for example, regularly or irregularly held depressions or corrugations are conceivable.
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 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 und trägt damit zu einer Verkleinerung
des eindringenden Massenstromes an Heissgas 24 bei, 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. To avoid the disadvantages of the prior art, the side edges 25 of the
This embodiment reliably prevents closure of the mouths by adjacent shroud elements. It ensures that the cooling air can always pass through the cooling holes 17, even if two
The cooling air entering from the two
Due to the structural design of the gap, the quantitative ratio of the two partial flows can be influenced. Thus, the upper and lower sides can have a different gap width or the boundary walls can be inclined or fluidically designed differently.
- 1010
- Turbinenschaufelturbine blade
- 1111
- DeckbandelementShroud element
- 12,1312.13
- Dichtrippensealing ribs
- 1515
- Vertiefungdeepening
- 1717
- Kühlbohrungcooling hole
- 1818
- KühlluftkanalCooling air duct
- 1919
- Drosselstellerestriction
- 2020
- Gehäusewandhousing wall
- 2121
- Kavitätcavity
- 2222
- Oberseite (Deckbandelement)Top side (shroud element)
- 2323
- Schaufelprofilblade profile
- 2424
- Heissgashot gas
- 2525
- Seitenkante des DeckbandelementsSide edge of the shroud element
- 2626
- Spalt zwischen den DeckbandelementenGap between the shroud elements
Claims (9)
- Air-cooled turbine blade (10) which has a shroud band element (11), extending perpendicularly to the blade longitudinal axis, at the blade tip, a plurality of cooling bores (17) passing through the shroud band element (11) for cooling purposes and being connected on the inlet side to at least one cooling passage (18) which runs through the turbine blade (10) to the blade tip and opening on the outlet side into the exterior space surrounding the turbine blade (10), the cooling bores (17) running from inside to outside in the shroud band element (11) at least approximately parallel to the direction of movement of the blade (10) and opening in each case in front of the outer margin (25) of the shroud band element (11) into a surface recess (15) which is open towards the exterior space, the recess (15) open towards the exterior space being arranged on the side edge (25) of the shroud band element (11), at least two spaced-apart sealing ribs (12, 13) running parallel to the direction of movement of the blade being provided on the top side (22) of the shroud band element (11), these sealing ribs (12, 13) forming a cavity (21) in interaction with the opposite casing wall (20) of the gas turbine, the cooling bores (17) opening into a gap (26) formed by opposite recesses (15), and at least one partial flow of the cooling air which discharges there flowing into the cavity (21), characterized in that the quantitative proportion of the partial flows discharging from the gap (26) in the direction of the top side and underside of the shroud band is controlled by the gap geometry.
- Turbine blade according to Claim 1, characterized in that the top side and underside have different gap widths.
- Turbine blade according to Claim 1, characterized in that means for improving the heat transfer between cooling air and shroud band element (11) are provided in the cooling bores (17).
- Turbine blade according to Claim 3, characterized in that the means for improving the heat transfer at the bore walls (17) comprise surface irregularities, ribs and/or turbulators.
- Turbine blade according to Claim 4, characterized in that the cooling bores (17) are produced by means of the "STEM drilling" process.
- Turbine blade according to Claim 1, characterized in that a choke point (19) for limiting the cooling-air mass flow is provided in each case in the cooling bores (17).
- Turbine blade according to Claim 6, characterized in that the choke points (19) are arranged in each case at the inlet side of the cooling bores (17).
- Turbine blade according to Claim 1, characterized in that the cooling bores (17) have an oval cross section.
- Turbine blade according to Claim 1, characterized in that the cooling bores (17) form a diffuser or are of diffuser-like design in the flow direction.
Applications Claiming Priority (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19860245 | 1998-12-24 | ||
| DE19860244A DE19860244B4 (en) | 1998-12-24 | 1998-12-24 | Turbine blade with actively cooled shroud element |
| 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 |
| DE19860244 | 1998-12-24 |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| EP1013884A2 EP1013884A2 (en) | 2000-06-28 |
| EP1013884A3 EP1013884A3 (en) | 2003-11-05 |
| EP1013884B1 true 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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| US6761534B1 (en) | 1999-04-05 | 2004-07-13 | General Electric Company | Cooling circuit for a gas turbine bucket and tip shroud |
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| DE19963377A1 (en) * | 1999-12-28 | 2001-07-12 | Abb Alstom Power Ch Ag | Turbine blade with actively cooled cover band element |
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| JP2002371802A (en) * | 2001-06-14 | 2002-12-26 | Mitsubishi Heavy Ind Ltd | Shroud integrated type moving blade in gas turbine and split ring |
| US20040101410A1 (en) * | 2001-10-02 | 2004-05-27 | Oleg Naljotov | Axial flow fluid machine |
| US6632069B1 (en) * | 2001-10-02 | 2003-10-14 | Oleg Naljotov | Step of pressure of the steam and gas turbine with universal belt |
| US6491498B1 (en) | 2001-10-04 | 2002-12-10 | Power Systems Mfg, Llc. | Turbine blade pocket shroud |
| US7074006B1 (en) | 2002-10-08 | 2006-07-11 | The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration | Endwall treatment and method for gas turbine |
| JP4195882B2 (en) * | 2003-04-18 | 2008-12-17 | オレグ ナリオトフ | Axial flow fluid machine |
| US7066714B2 (en) * | 2004-03-26 | 2006-06-27 | United Technologies Corporation | High speed rotor assembly shroud |
| EP1591626A1 (en) | 2004-04-30 | 2005-11-02 | Alstom Technology Ltd | Blade for gas turbine |
| KR100758725B1 (en) | 2005-10-17 | 2007-09-14 | 올레지 날조토브 | Steam/gas turbine pressure stage with universal shroud |
| US7568882B2 (en) * | 2007-01-12 | 2009-08-04 | General Electric Company | Impingement cooled bucket shroud, turbine rotor incorporating the same, and cooling method |
| US7938951B2 (en) * | 2007-03-22 | 2011-05-10 | General Electric Company | Methods and systems for forming tapered cooling holes |
| US7964087B2 (en) * | 2007-03-22 | 2011-06-21 | General Electric Company | Methods and systems for forming cooling holes having circular inlets and non-circular outlets |
| US20080230396A1 (en) * | 2007-03-22 | 2008-09-25 | General Electric Company | Methods and systems for forming turbulated cooling holes |
| US8057177B2 (en) * | 2008-01-10 | 2011-11-15 | General Electric Company | Turbine blade tip shroud |
| US7946817B2 (en) * | 2008-01-10 | 2011-05-24 | General Electric Company | Turbine blade tip shroud |
| US20090180894A1 (en) * | 2008-01-10 | 2009-07-16 | General Electric Company | Turbine blade tip shroud |
| US7946816B2 (en) * | 2008-01-10 | 2011-05-24 | General Electric Company | Turbine blade tip shroud |
| US8317461B2 (en) * | 2008-08-27 | 2012-11-27 | United Technologies Corporation | Gas turbine engine component having dual flow passage cooling chamber formed by single core |
| GB0901129D0 (en) * | 2009-01-26 | 2009-03-11 | Rolls Royce Plc | Rotor blade |
| CH700686A1 (en) * | 2009-03-30 | 2010-09-30 | Alstom Technology Ltd | Blade for a gas turbine. |
| GB0910177D0 (en) * | 2009-06-15 | 2009-07-29 | Rolls Royce Plc | A cooled component for a gas turbine engine |
| US8353669B2 (en) * | 2009-08-18 | 2013-01-15 | United Technologies Corporation | Turbine vane platform leading edge cooling holes |
| DE102009049649A1 (en) * | 2009-10-15 | 2011-04-21 | Abb Turbo Systems Ag | turbine |
| JP5517910B2 (en) * | 2010-12-22 | 2014-06-11 | 三菱重工業株式会社 | Turbine and seal structure |
| US20140064984A1 (en) * | 2012-08-31 | 2014-03-06 | General Electric Company | Cooling arrangement for platform region of turbine rotor blade |
| JP5612136B2 (en) | 2013-01-09 | 2014-10-22 | ファナック株式会社 | Impeller forming method and impeller whose shape is defined by a plurality of straight lines |
| US9759070B2 (en) * | 2013-08-28 | 2017-09-12 | General Electric Company | Turbine bucket tip shroud |
| EP3049633A4 (en) * | 2013-09-26 | 2016-10-26 | Diffused platform cooling holes | |
| EP3060763B1 (en) * | 2013-10-21 | 2020-04-15 | United Technologies Corporation | Incident tolerant turbine vane gap flow discouragement |
| US10539026B2 (en) | 2017-09-21 | 2020-01-21 | United Technologies Corporation | Gas turbine engine component with cooling holes having variable roughness |
| US10641108B2 (en) * | 2018-04-06 | 2020-05-05 | United Technologies Corporation | Turbine blade shroud for gas turbine engine with power turbine and method of manufacturing same |
| JP7477284B2 (en) * | 2019-11-14 | 2024-05-01 | 三菱重工業株式会社 | Turbine blades and gas turbines |
| US11255198B1 (en) * | 2021-06-10 | 2022-02-22 | General Electric Company | Tip shroud with exit surface for cooling passages |
| CN115324657A (en) * | 2022-10-12 | 2022-11-11 | 中国航发四川燃气涡轮研究院 | Turbine working blade shroud cooling structure |
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-
1999
- 1999-12-21 EP EP99811187A patent/EP1013884B1/en not_active Expired - Lifetime
- 1999-12-21 DE DE59912323T patent/DE59912323D1/en not_active Expired - Lifetime
- 1999-12-23 US US09/471,410 patent/US6340284B1/en not_active Expired - Lifetime
- 1999-12-24 CN CN99124987A patent/CN1260442A/en active Pending
Also Published As
| Publication number | Publication date |
|---|---|
| US6340284B1 (en) | 2002-01-22 |
| DE59912323D1 (en) | 2005-09-01 |
| CN1260442A (en) | 2000-07-19 |
| EP1013884A3 (en) | 2003-11-05 |
| EP1013884A2 (en) | 2000-06-28 |
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