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EP2384392B2 - Cooled component for a gas turbine - Google Patents
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EP2384392B2 - Cooled component for a gas turbine - Google Patents

Cooled component for a gas turbine Download PDF

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Publication number
EP2384392B2
EP2384392B2 EP10701375.7A EP10701375A EP2384392B2 EP 2384392 B2 EP2384392 B2 EP 2384392B2 EP 10701375 A EP10701375 A EP 10701375A EP 2384392 B2 EP2384392 B2 EP 2384392B2
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EP
European Patent Office
Prior art keywords
pins
wall
impingement cooling
density
cooling
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EP10701375.7A
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German (de)
French (fr)
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EP2384392B1 (en
EP2384392A1 (en
Inventor
Jörg KRÜCKELS
Milan Pathak
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Ansaldo Energia IP UK Ltd
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Ansaldo Energia IP UK Ltd
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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
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid

Definitions

  • the present invention relates to the field of gas turbines. It relates to a cooled component for a gas turbine according to the preamble of claim 1. It also relates to a method for operating such a component.
  • Gas turbines are designed for ever higher operating temperatures to increase efficiency.
  • the components and elements in the combustion chamber area and the rotor and guide blades of the downstream turbine, including the other elements that border the hot gas channel, are particularly exposed to thermal stress.
  • thermal stress In order to effectively counteract the thermal stress that occurs, particularly resistant materials such as nickel-based alloys can be used.
  • additional measures must be taken to cool the components, with different cooling methods being used, such as film cooling or impingement cooling.
  • Cooling the guide vanes in the first stages of the turbine is particularly important because this is the area where the highest temperatures in the gas turbine occur.
  • US-B2-7,097,418 It has already been described how the outer platform of a guide vane can be cooled in a particularly simple manner by means of a two-stage impingement cooling system, whereby in a first stage the area at the trailing edge of the vane is cooled and then the cooling air flowing out from there cools the platform at the leading edge in a second stage. In both stages, differently positioned and spaced impingement cooling holes (30, 38 in Fig.3 ) are used. Pins on the back of the platform floor are not used.
  • the invention aims to remedy this situation. It is therefore an object of the invention to create a cooled component of a gas turbine, in particular in the case of a guide vane provided with a platform, the cooling of which is optimally adapted to the locally varying thermal load without causing unnecessary additional consumption of cooling air, i.e. the cooling air used is minimized with the same cooling intensity.
  • the thermally loaded wall to be cooled has a large number of pins protruding from the wall on its rear side in a flat distribution, and that the distribution of the pins within the thermally critical zones of the component has a higher density than in the other areas.
  • the heat transfer between the wall and the cooling air can be changed locally and adapted to the thermal load without necessarily having to use a larger amount of cooling air.
  • An embodiment of the invention is characterized in that the means for generating the jets directed onto the rear side of the wall comprise an impact cooling plate provided with distributed impact cooling holes.
  • the cooling is particularly effective if, according to another embodiment of the invention, the impingement cooling plate is arranged at a distance substantially parallel to the rear side of the wall, and the distribution of the impingement cooling holes is coordinated with the distribution of the pins in such a way that, viewed in a direction perpendicular to the impingement cooling plate, the impingement cooling holes lie between the pins.
  • the variation of the cooling can be intensified by correlating the density of the impingement cooling holes with the density of the pins.
  • the density of the impingement cooling holes and the density of the pins can be locally equal.
  • the component is a guide vane of a gas turbine, which comprises an airfoil extending in a longitudinal direction and a platform adjoining the airfoil and extending transversely to the longitudinal direction, the base of which is the thermally loaded wall cooled by impingement cooling and forms a groove at the transition to the airfoil, wherein the distribution of the pins towards the groove has a higher density than in the remaining areas remote from the groove.
  • Fig.1 is a longitudinal section of the upper part of a gas turbine guide vane with platform and locally varying impingement cooling according to an embodiment of the invention.
  • the guide vane 10 has an overall similar configuration to that shown in the initially mentioned US-B2-7,097,418 It comprises a blade 11 extending in the longitudinal direction of the blade, at the upper end of which a platform 12 is formed, which extends essentially transversely to the longitudinal direction of the blade.
  • the platform 12 has a base or a wall 12a, the underside of which is exposed to the hot gas flowing through the turbine, and which is cooled on the upper side by impingement cooling.
  • a cavity 13 is formed on the top of the platform 12, which is covered by an impact cooling plate 14 arranged parallel to the wall 12a.
  • Impact cooling holes 16 are provided in a predetermined distribution in the impact cooling plate 14, through which compressed cooling air in the form of individual cooling air jets (see the arrows in Fig.1 ) enters the cavity 13 and impacts on the opposite rear side of the wall 12a. During the impact and the subsequent turbulent contact with the rear side of the wall 12a, the cooling air absorbs heat from the wall 12a and is then discharged from the cavity 13 (in Fig.1 not shown).
  • the surface distribution of the impact cooling holes 16 is shown in Fig.2 to see.
  • Fig.4 To improve the heat transfer between wall 12a and the cooling air, vertically projecting, conical or pyramid-shaped pins 15 are arranged on the back of wall 12a (see also Fig.3 , in which the pins 15 are shown in perspective), which increase the contact area between the wall and the cooling air flow and intensify the turbulence.
  • Fig.4 As can be seen, the density of the impingement cooling holes 16 and the density of the pins 15 are locally different, but at the same time correlated with each other, i.e. in the areas where the density of the pins 15 is increased (compression area 18), the density of the impingement cooling holes 16 is also increased, and vice versa. In particular, the densities of the two are locally the same.
  • the impingement cooling holes 16 are preferably arranged "on a gap", i.e. in spaces between the pins 15: Between two parallel rows of pins 15, a row of impingement cooling holes 16 with the same periodicity is placed offset.
  • Fig.1 there is a guide vane in Fig.1 reproduced type on the platform 12 critical zones A c in which precautions against thermal stress are particularly important.
  • One such critical zone is the groove between the wall 12a of the platform 12 and the blade.
  • the density of the pins 15 is significantly increased compared to the rest of the area.
  • the density of the impact cooling holes 16 in this area 18 is also increased, analogous to the density of the pins 15.
  • the transition between the areas of different hole and pin density can be continuous.

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

Description

Technisches GebietTechnical area

Die vorliegende Erfindung bezieht sich auf das Gebiet der Gasturbinen. Sie betrifft ein gekühltes Bauelement für eine Gasturbine gemäss dem Oberbegriff des Anspruchs 1. Sie betrifft auch ein Verfahren zum Betrieb eines solchen Bauelements.The present invention relates to the field of gas turbines. It relates to a cooled component for a gas turbine according to the preamble of claim 1. It also relates to a method for operating such a component.

Stand der TechnikState of the art

Gasturbinen werden zur Steigerung des Wirkungsgrades für immer höhere Betriebstemperaturen ausgelegt. Besonderen thermischen Belastungen ausgesetzt sind dabei vor allem die Bauteile bzw. Bauelemente im Bereich der Brennkammer sowie die Lauf- und Leitschaufeln der nachfolgenden Turbine einschliesslich der übrigen, den Heissgaskanal begrenzenden Elemente. Um die auftretenden thermischen Belastungen wirkungsvoll zu begegnen, können einerseits besonders widerstandfähige Werkstoffe, wie z. B. Nickelbasislegierungen, eingesetzt werden. Andererseits müssen zusätzliche Massnahmen zur Kühlung der Bauelemente ergriffen werden, wobei unterschiedliche Kühlungsmethoden, wie z.B. die Filmkühlung oder die Prallkühlung, Anwendung finden.Gas turbines are designed for ever higher operating temperatures to increase efficiency. The components and elements in the combustion chamber area and the rotor and guide blades of the downstream turbine, including the other elements that border the hot gas channel, are particularly exposed to thermal stress. In order to effectively counteract the thermal stress that occurs, particularly resistant materials such as nickel-based alloys can be used. On the other hand, additional measures must be taken to cool the components, with different cooling methods being used, such as film cooling or impingement cooling.

Es ist bereits aus der US-B2-6,779,597 bekannt geworden, bei Bauelementen von Gasturbinen mehrstufige Prallkühlungsstrukturen vorzusehen, bei denen eine Wand, deren Vorderseite dem Heissgaskanal zugewandt ist, auf der Rückseite durch senkrecht auftreffenden Kühlluftstrahlen, die durch entsprechende Prallkühlungslöcher erzeugt werden, entsprechend prallgekühlt wird. Die Kühlwirkung wird dabei durch auf der Rückseite verteilt angeordnete, abstehende Pfosten oder Pins verstärkt, welche die Wärme abgebende Oberfläche vergrössern und Turbulenzen in der Kühlluftströmung verstärken. Die Verteilungen der Prallkühlungslöcher und Pins in der Fläche sind dabei konstant. Die Durchmesser der Prallkühlungslöcher entsprechen dabei dem Durchmesser der Pins an der Basis. Die Dichte der Löcher ist wesentlich geringer als die Dichte der Pins. Es ist auch aus der EP0889201 bekannt geworden, bei Bauelementen von Gasturbinen Prallkühlungsstrukturen vorzusehen. Es ist weiterhin aus der USA-4,719,748 bekannt geworden, beim Übergangsrohr zwischen den einzelnen Brennern und dem Eingang der nachfolgenden Turbine eine Prallkühlung vorzusehen, bei welcher mittels Prallkühlungslöchern erzeugte Kühlluftstrahlen auf die Rückseite der Rohrwände gerichtet werden. Durch Variation der Lochgrösse und/oder der Abstände zwischen den Löchern und/oder der Abstände von den Löchern zur Rohrwand wird die Kühlungsintensität variiert und der jeweiligen thermischen Belastung angepasst. Pins zur Verbesserung des Wärmeübergangs sind nicht vorgesehen.It is already out of the US-B2-6,779,597 It has become known to provide multi-stage impingement cooling structures for gas turbine components, in which a wall, the front of which faces the hot gas channel, is impingement cooled on the back by vertically impinging cooling air jets generated by corresponding impingement cooling holes. The cooling effect is increased by protruding posts or pins distributed on the back, which increase the heat-emitting surface and increase turbulence in the cooling air flow. The distribution of the impingement cooling holes and pins in the area is constant. The diameters of the impingement cooling holes correspond to the diameter of the pins at the base. The density of the holes is significantly lower than the density of the pins. It is also clear from the EP0889201 It has become known to provide impingement cooling structures for components of gas turbines. It is also known from the USA-4,719,748 It has become known to provide impingement cooling in the transition pipe between the individual burners and the inlet of the subsequent turbine, in which cooling air jets generated by means of impingement cooling holes are directed onto the back of the pipe walls. By varying the hole size and/or the distances between the holes and/or the distances from the holes to the pipe wall, the cooling intensity is varied and adapted to the respective thermal load. Pins to improve heat transfer are not provided.

Besondere Bedeutung kommt der Kühlung den Leitschaufeln in den ersten Stufen der Turbine zu, weil in diesem Bereich die höchsten Temperaturen in der Gasturbine auftreten. In der US-B2-7,097,418 ist bereits beschrieben worden, wie die äussere Plattform einer Leitschaufel auf besonders einfache Weise mittels einer zweistufigen Prallkühlung gekühlt werden kann, wobei in einer ersten Stufe der Bereich an der Hinterkante der Schaufel gekühlt wird, und dann die von dort abströmende Kühlluft in einer zweiten Stufe die Plattform an der Vorderkante kühlt. In beiden Stufen werden unterschiedlich positionierte und beabstandete Prallkühlungslöcher (30, 38 in Fig. 3) eingesetzt. Pins auf der Rückseite des Plattformbodens kommen nicht zum Einsatz.Cooling the guide vanes in the first stages of the turbine is particularly important because this is the area where the highest temperatures in the gas turbine occur. US-B2-7,097,418 It has already been described how the outer platform of a guide vane can be cooled in a particularly simple manner by means of a two-stage impingement cooling system, whereby in a first stage the area at the trailing edge of the vane is cooled and then the cooling air flowing out from there cools the platform at the leading edge in a second stage. In both stages, differently positioned and spaced impingement cooling holes (30, 38 in Fig.3 ) are used. Pins on the back of the platform floor are not used.

Die Variation der Prallkühlungslöcher zur Anpassung an sich verändernde thermische Belastungen hat zur Folge, dass sich in der Regel auch die benötigte Kühlluftmenge verändert. Werden - bei gleich bleibenden Lochdurchmesser - mehr Löcher pro Flächeneinheit eingesetzt, erhöht sich auch die verbrauchte Kühlluftmenge, was zu einer Minderung des Wirkungsgrades der Maschine führt.The variation of the impingement cooling holes to adapt to changing thermal loads usually results in the required amount of cooling air also changing. If more holes are used per unit area - with the hole diameter remaining the same - the amount of cooling air used also increases, which leads to a reduction in the efficiency of the machine.

Darstellung der ErfindungDescription of the invention

Hier will die Erfindung Abhilfe schaffen. Es ist daher eine Aufgabe der Erfindung, ein gekühltes Bauelement einer Gasturbine, insbesondere bei einer mit einer Plattform versehenen Leitschaufel, zu schaffen, deren Kühlung an die lokal variierende thermische Belastung optimal angepasst ist, ohne einen unnötigen Mehrverbrauch an Kühlluft zu verursachen, d.h. es wird bei gleicher Kühlungsintensität eine Minimierung der eingesetzten Kühlluft erzielt.The invention aims to remedy this situation. It is therefore an object of the invention to create a cooled component of a gas turbine, in particular in the case of a guide vane provided with a platform, the cooling of which is optimally adapted to the locally varying thermal load without causing unnecessary additional consumption of cooling air, i.e. the cooling air used is minimized with the same cooling intensity.

Die Aufgabe wird durch die Gesamtheit der Merkmale des Anspruchs 1 gelöst. Es ist eine wesentliche Komponente der Erfindung, dass die thermisch belastete und zu kühlende Wand auf ihrer Rückseite in flächiger Verteilung eine Vielzahl von aus der Wand hervorstehenden Pins aufweist, und dass die Verteilung der Pins innerhalb der thermischen kritischen Zonen des Bauelements eine höhere Dichte aufweist als in den übrigen Bereichen. Hierdurch kann lokal der Wärmeübergang zwischen Wand und Kühlluft verändert und der thermischen Belastung angepasst werden, ohne dass zwingend eine grössere Kühlluftmenge eingesetzt werden muss.The object is achieved by the totality of the features of claim 1. It is an essential component of the invention that the thermally loaded wall to be cooled has a large number of pins protruding from the wall on its rear side in a flat distribution, and that the distribution of the pins within the thermally critical zones of the component has a higher density than in the other areas. As a result, the heat transfer between the wall and the cooling air can be changed locally and adapted to the thermal load without necessarily having to use a larger amount of cooling air.

Eine Ausgestaltung der Erfindung ist dadurch gekennzeichnet, dass die Mittel zur Erzeugung der auf die Rückseite der Wand gerichteten Strahlen ein mit verteilt angeordneten Prallkühlungslöchern versehenes Prallkühlungsblech umfassen.An embodiment of the invention is characterized in that the means for generating the jets directed onto the rear side of the wall comprise an impact cooling plate provided with distributed impact cooling holes.

Besonders effektiv ist die Kühlung, wenn gemäss einer anderen Ausgestaltung der Erfindung das Prallkühlungsblech mit Abstand im wesentlichen parallel zur Rückseite der Wand angeordnet ist, und die Verteilung der Prallkühlungslöcher auf die Verteilung der Pins derart abgestimmt ist, dass in einer Richtung senkrecht zum Prallkühlungsblech gesehen die Prallkühlungslöcher jeweils zwischen den Pins liegen.The cooling is particularly effective if, according to another embodiment of the invention, the impingement cooling plate is arranged at a distance substantially parallel to the rear side of the wall, and the distribution of the impingement cooling holes is coordinated with the distribution of the pins in such a way that, viewed in a direction perpendicular to the impingement cooling plate, the impingement cooling holes lie between the pins.

Die Variation der Kühlung kann dadurch intensiviert werden, dass die Dichte der Prallkühlungslöcher mit der Dichte der Pins korreliert ist. Insbesondere kann die Dichte der Prallkühlungslöcher und die Dichte der Pins örtlich gleich sein.The variation of the cooling can be intensified by correlating the density of the impingement cooling holes with the density of the pins. In particular, the density of the impingement cooling holes and the density of the pins can be locally equal.

Das Bauelement ist eine Leitschaufel einer Gasturbine, welche ein sich in einer Längsrichtung erstreckendes Schaufelblatt und eine an das Schaufelblatt anschliessende, sich quer zur Längsrichtung erstreckende Plattform umfasst, deren Boden die thermisch belastete, durch Prallkühlung gekühlte Wand ist und am Übergang zum Schaufelblatt eine Hohlkehle ausbildet, wobei die Verteilung der Pins zur Hohlkehle hin eine höhere Dichte aufweist als in den von der Hohlkehle entfernten übrigen Bereichen.The component is a guide vane of a gas turbine, which comprises an airfoil extending in a longitudinal direction and a platform adjoining the airfoil and extending transversely to the longitudinal direction, the base of which is the thermally loaded wall cooled by impingement cooling and forms a groove at the transition to the airfoil, wherein the distribution of the pins towards the groove has a higher density than in the remaining areas remote from the groove.

Kurze Erläuterung der FigurenBrief explanation of the figures

Die Erfindung soll nachfolgend anhand von Ausführungsbeispielen im Zusammenhang mit der Zeichnung näher erläutert werden. Alle für das unmittelbare Verständnis der Erfindung nicht erforderlichen Elemente sind weggelassen worden. Gleiche Elemente sind in den verschiedenen Figuren mit den gleichen Bezugszeichen versehen. Es zeigt:

Fig. 1
einen Längsschnitt durch den oberen Teil einer Gasturbinen-Leitschaufel mit Plattform, mit örtlich variierender Prallkühlung, gemäss einem Ausführungsbeispiel der Erfindung;
Fig. 2
das bei der Leitschaufel aus Fig. 1 eingesetzte Prallkühlungsblech in der Draufsicht von oben;
Fig. 3
die bei der Leitschaufel aus Fig. 1 eingesetzte Verteilung von Pins in der Draufsicht von oben (die Pins sind perspektivisch gezeichnet) und
Fig. 4
von oben gesehen, die korrelierten Verteilungen von Prallkühlungslöchern und Pins gemäss Fig. 1-3.
The invention will be explained in more detail below using exemplary embodiments in conjunction with the drawing. All elements not required for the immediate understanding of the invention have been omitted. Identical elements are provided with the same reference numerals in the various figures. It shows:
Fig.1
a longitudinal section through the upper part of a gas turbine guide vane with platform, with locally varying impingement cooling, according to an embodiment of the invention;
Fig. 2
that of the guide vane Fig.1 inserted impact cooling plate in top view;
Fig.3
which in the guide vane is made of Fig.1 used distribution of pins in the top view (the pins are drawn in perspective) and
Fig.4
seen from above, the correlated distributions of impingement cooling holes and pins according to Fig. 1-3 .

Wege zur Ausführung der ErfindungWays to implement the invention

In Fig. 1 ist im Längsschnitt der obere Teil einer Gasturbinen- Leitschaufel mit Plattform und örtlich variierender Prallkühlung gemäss einem Ausführungsbeispiel der Erfindung wiedergegeben. Die Leitschaufel 10 hat insgesamt eine ähnliche Konfiguration, wie sie in der eingangs erwähnten US-B2-7,097,418 beschrieben wird. Sie umfasst ein sich in der Schaufellängsrichtung erstreckendes Schaufelblatt 11, an dessen oberem Ende eine Plattform 12 angeformt ist, die sich im wesentlichen quer zur Längsrichtung der Schaufel erstreckt. Die Plattform 12 hat einen Boden bzw. eine Wand 12a, deren Unterseite vom durch die Turbine strömenden Heissgas beaufschlagt ist, und die auf der Oberseite durch eine Prallkühlung gekühlt wird.In Fig.1 is a longitudinal section of the upper part of a gas turbine guide vane with platform and locally varying impingement cooling according to an embodiment of the invention. The guide vane 10 has an overall similar configuration to that shown in the initially mentioned US-B2-7,097,418 It comprises a blade 11 extending in the longitudinal direction of the blade, at the upper end of which a platform 12 is formed, which extends essentially transversely to the longitudinal direction of the blade. The platform 12 has a base or a wall 12a, the underside of which is exposed to the hot gas flowing through the turbine, and which is cooled on the upper side by impingement cooling.

Dazu ist auf der Oberseite der Plattform 12 ein Hohlraum 13 ausgebildet, der von einem zur Wand 12a parallel angeordneten Prallkühlungsblech 14 abgedeckt wird. Im Prallkühlungsblech 14 sind in einer vorgegebenen Verteilung Prallkühlungslöcher 16 vorgesehen, durch die komprimierte Kühlluft in Form von einzelnen Kühlluftstrahlen (siehe die Pfeile in Fig. 1) in den Hohlraum 13 eintritt und auf die gegenüberliegende Rückseite der Wand 12a aufprallt. Beim Aufprall und dem danach folgenden turbulenten Kontakt mit der Rückseite der Wand 12a nimmt die Kühlluft Wärme von der Wand 12a auf und wird anschliessend aus dem Hohlraum 13 (auf in Fig. 1 nicht dargestelltem Wege) abgeleitet. Die flächige Verteilung der Prallkühlungslöcher 16 ist in Fig. 2 zu sehen.For this purpose, a cavity 13 is formed on the top of the platform 12, which is covered by an impact cooling plate 14 arranged parallel to the wall 12a. Impact cooling holes 16 are provided in a predetermined distribution in the impact cooling plate 14, through which compressed cooling air in the form of individual cooling air jets (see the arrows in Fig.1 ) enters the cavity 13 and impacts on the opposite rear side of the wall 12a. During the impact and the subsequent turbulent contact with the rear side of the wall 12a, the cooling air absorbs heat from the wall 12a and is then discharged from the cavity 13 (in Fig.1 not shown). The surface distribution of the impact cooling holes 16 is shown in Fig.2 to see.

Zur Verbesserung des Wärmeübergangs zwischen Wand 12a und der Kühlluft sind auf der Rückseite der Wand 12a senkrecht abstehende, kegel- oder pyramidenförmige Pins 15 angeordnet (siehe auch Fig. 3, in der die Pins 15 perspektivisch eingezeichnet sind), welche die Kontaktfläche zwischen Wand und Kühlluftstrom vergrössern und die Turbulenzen intensivieren. Wie aus Fig. 4 zu erkennen ist, ist die Dichte der Prallkühlungslöcher 16 und die Dichte der Pins 15 örtlich unterschiedlich, aber gleichzeitig miteinander korreliert, d.h. in den Bereichen, wo die Dichte der Pins 15 erhöht ist (Verdichtungsbereich 18), ist auch die Dichte der Prallkühlungslöcher 16 erhöht, und umgekehrt. Insbesondere sind lokal die Dichten der beiden gleich. Die Prallkühlungslöcher 16 sind vorzugsweise "auf Lücke", also auf Zwischenräume, mit den Pins 15 angeordnet: Zwischen zwei parallelen Reihen von Pins 15 ist jeweils versetzt eine Reihe von Prallkühlungslöchern 16 mit derselben Periodizität platziert.To improve the heat transfer between wall 12a and the cooling air, vertically projecting, conical or pyramid-shaped pins 15 are arranged on the back of wall 12a (see also Fig.3 , in which the pins 15 are shown in perspective), which increase the contact area between the wall and the cooling air flow and intensify the turbulence. As can be seen from Fig.4 As can be seen, the density of the impingement cooling holes 16 and the density of the pins 15 are locally different, but at the same time correlated with each other, i.e. in the areas where the density of the pins 15 is increased (compression area 18), the density of the impingement cooling holes 16 is also increased, and vice versa. In particular, the densities of the two are locally the same. The impingement cooling holes 16 are preferably arranged "on a gap", i.e. in spaces between the pins 15: Between two parallel rows of pins 15, a row of impingement cooling holes 16 with the same periodicity is placed offset.

Erfahrungsgemäss gibt es bei einer Leitschaufel der in Fig. 1 wiedergegebenen Art an der Plattform 12 kritische Zonen Ac, in denen Vorkehrungen gegen die thermische Belastung besonders wichtig sind. Eine solche kritische Zone ist die Hohlkehle zwischen der Wand 12a der Plattform 12 und dem Schaufelblatt. Um an dieser Stelle der Plattform 12, d.h. am Übergang zum Schaufelblatt die Kühlwirkung lokal zu erhöhen, ist in einem an die Hohlkehle unmittelbar angrenzenden Verdichtungsbereich 18 (in Fig. 4 grau unterlegt) die Dichte der Pins 15 gegenüber dem übrigen Bereich deutlich erhöht. Zusätzlich ist auch die Dichte der Prallkühlungslöcher 16 in diesem Bereich 18 erhöht, und zwar analog zur Dichte der Pins 15. Der Übergang zwischen den Bereichen unterschiedlicher Loch- und Pindichte kann dabei stetig ausgebildet sein.Experience has shown that there is a guide vane in Fig.1 reproduced type on the platform 12 critical zones A c in which precautions against thermal stress are particularly important. One such critical zone is the groove between the wall 12a of the platform 12 and the blade. In order to locally increase the cooling effect at this point on the platform 12, ie at the transition to the blade, in a compression area 18 immediately adjacent to the groove (in Fig.4 (highlighted in grey) the density of the pins 15 is significantly increased compared to the rest of the area. In addition, the density of the impact cooling holes 16 in this area 18 is also increased, analogous to the density of the pins 15. The transition between the areas of different hole and pin density can be continuous.

Hierdurch wird die Wärmeabfuhr im Bereich der Hohlkehle deutlich verbessert, wodurch die Auswirkungen der thermischen Belastung begrenzt werden können.This significantly improves heat dissipation in the area of the cove, which can limit the effects of thermal stress.

Es versteht sich von selbst, dass im Rahmen der Erfindung und durch die erfindungsgemässen Vorkehrungen nicht nur kritische Bereiche der Leitschaufeln, sondern auch anderer thermisch belasteter Bauelemente der Gasturbine kühlungstechnisch "entschärft" werden können.It goes without saying that within the scope of the invention and through the provisions according to the invention, not only critical areas of the guide vanes, but also other thermally stressed components of the gas turbine can be "defused" by cooling technology.

BezugszeichenlisteList of reference symbols

1010
Leitschaufel (Gasturbine)Guide vane (gas turbine)
1111
SchaufelblattShovel blade
1212
Plattformplatform
12a12a
Wand (Plattform)Wall (platform)
1313
Hohlraumcavity
1414
PrallkühlungsblechImpact cooling plate
1515
PinPin
1616
PrallkühlungslochImpact cooling hole
1717
PrallkühlungsmusterImpingement cooling pattern
1818
VerdichtungsbereichCompaction area
AcAc
kritische Zone (Hohlkehle)critical zone (cove)

Claims (4)

  1. Cooled component (10) for a gas turbine which, in order to cool a wall (12a) thermally loaded on the front side, comprises a plurality of pins (15) protruding from the wall and distributed (17) superficially on the back of the wall (12a), and means (14, 16) for creating jets of a cooling medium which are directed onto the back of the wall (12a) in the region of the pins (15) and serve for impingement cooling, wherein the means for generating the jets onto the back of the wall comprises an impingement cooling plate (14) with impingement cooling holes (16) arranged in distributed fashion, and the density of the impingement cooling holes (16) correlates with the density of the pins (15), wherein the distribution of the pins (15) within critical zones (Ac) of the component (10) has a higher density than in the other regions of the component, characterised in that in the regions in which the density of the pins is higher, the density of the impingement cooling holes (16) is also higher and vice versa;
    wherein the component is a guide vane (10) of the gas turbine which comprises a blade (11) extending in a longitudinal direction and a platform (12) adjoining the blade (11) and extending transversely to the longitudinal direction, the base of which is the thermally loaded wall (12a) cooled by the impingement cooling, and a hollow groove (Ac) is formed at the transition to the blade (11), and that the distribution of the pins (15) has a higher density towards the hollow groove (Ac) than in the other regions remote from the hollow groove (Ac).
  2. Cooled component according to claim 1, characterised in that the impingement cooling plate (14) is arranged spaced from and substantially parallel to the back of the wall (12a), and that the distribution of the impingement cooling holes (16) is matched to the distribution of the pins (15) such that, viewed in a direction perpendicular to the impingement cooling plate (14), the impingement cooling holes (16) each lie between the pins (15).
  3. Cooled component according to claim 1, characterised in that the density of the impingement cooling holes (16) and the density of the pins (15) are locally the same.
  4. Method for operating a cooled component of a gas turbine according to any of claims 1 to 3, characterised in that to improve the heat transfer between the wall (12a) and the cooling air, which is used in the form of individual cooling air jets flowing through impingement cooling air holes (16), these cooling air jets flow onto the back of this wall which is fitted with perpendicularly protruding conical of pyramidal pins (15), that the cooling air jets impact between the spaces formed by the pins such that on this impact, a turbulent flow is generated which acts on the wall and causes an additional cooling.
EP10701375.7A 2009-01-30 2010-01-28 Cooled component for a gas turbine Active EP2384392B2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH00140/09A CH700319A1 (en) 2009-01-30 2009-01-30 Chilled component for a gas turbine.
PCT/EP2010/051018 WO2010086381A1 (en) 2009-01-30 2010-01-28 Cooled component for a gas turbine

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EP2384392A1 EP2384392A1 (en) 2011-11-09
EP2384392B1 EP2384392B1 (en) 2017-05-31
EP2384392B2 true EP2384392B2 (en) 2024-09-04

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CH (1) CH700319A1 (en)
RU (1) RU2539950C2 (en)
WO (1) WO2010086381A1 (en)

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Publication number Publication date
EP2384392B1 (en) 2017-05-31
RU2011135942A (en) 2013-03-10
CH700319A1 (en) 2010-07-30
US8444376B2 (en) 2013-05-21
WO2010086381A1 (en) 2010-08-05
RU2539950C2 (en) 2015-01-27
US20120020768A1 (en) 2012-01-26
EP2384392A1 (en) 2011-11-09

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