EP1869291B1 - Convectively cooled gas turbine blade - Google Patents

Convectively cooled gas turbine blade Download PDF

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Publication number
EP1869291B1
EP1869291B1 EP06725419.3A EP06725419A EP1869291B1 EP 1869291 B1 EP1869291 B1 EP 1869291B1 EP 06725419 A EP06725419 A EP 06725419A EP 1869291 B1 EP1869291 B1 EP 1869291B1
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EP
European Patent Office
Prior art keywords
blade
gas turbine
airfoil
cooling air
outlet opening
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.)
Not-in-force
Application number
EP06725419.3A
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German (de)
French (fr)
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EP1869291A1 (en
Inventor
Arkadi Fokine
Alexander Trishkin
Vladimir Vassiliev
Dmitry Vinogradov
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
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Publication date
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Publication of EP1869291A1 publication Critical patent/EP1869291A1/en
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Publication of EP1869291B1 publication Critical patent/EP1869291B1/en
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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
    • F01D5/14—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
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • 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 application relates to a gas turbine blade according to the preamble of claim 1.
  • the cross sections of these outlet openings are dimensioned smaller than that of the cooling air channels. They thus serve as throttling points and limit the mass flow of the blown cooling fluid, such as in the US 5,993,156 disclosed.
  • the outlet openings usually have circular or elliptical cross-sections, and do not coincide with the cross-sectional shape of the cooling channel, which leads the cooling air to the outlet opening.
  • the sudden abrupt change in cross section resulting in unfavorable flow patterns which among other things lead to increased pressure losses and locally increased material temperatures.
  • a gas turbine blade of the type mentioned is to be specified so that the disadvantages of the prior art are avoided. More specifically, the gas turbine blade is to be specified such that the heat transfer is uniformed on the cooling side and in this way uneven Temperaturvorannonen be avoided with life-shortening thermoelectric voltages.
  • the contour of the outlet opening of the along the leading edge extending cooling air duct is designed geometrically similar to the cross section of the cooling air duct. As a result, the cross-sectional transitions are minimized when flowing through the cooling air from the cooling air duct into the outlet opening. Dead water zones of the cooling air and deviations of the flow direction of the blown cooling air with its negative effects are thus avoided.
  • the cross-sectional area of the outlet opening is smaller than the cross-sectional area of the cooling air channel.
  • the outlet opening act as a throttle point and thus serve to limit the mass flow. That is, in the region of the outlet opening a web is arranged.
  • the distance of the contour line of the outlet opening from the blade outer contour in the area of the blade leaf leading edge assumes values between 138% and 162% of the local wall thickness of the blade leaf wall. This means; the height of the web is 38% to 62% of the local wall thickness in the area of the blade leading edge.
  • the distance between the contour line of the outlet opening and the airfoil outer contour assumes values of 113% to 138% of the local wall thickness of the airfoil wall.
  • the height of the web is therefore 13% to 38% of the local wall thickness in this area.
  • the height of the web is in one embodiment in the range of 0% to 225% of the wall thickness of the airfoil wall.
  • the wall thickness of the airfoil wall can vary in the direction of flow of the airfoil; In one embodiment of the invention, the wall thickness of the blade flap wall in the region of the outlet opening is constant.
  • the cooling air duct has an inlet opening arranged on the blade root.
  • fresh cooling air is supplied to the blade root, which flows along the blade leading edge in the blade inner side to the blade head, where it flows out through the outlet opening.
  • the blade is designed to be purely convectionally cooled in the region of the cooling channel. This means that there are no openings through which cooling air, for example as film cooling air, can reach the outside of the airfoil. The entire cooling air mass flow flowing into the cooling air duct therefore flows again through the outlet opening.
  • Blades of the type described above are preferably used in gas turbines, as components of a rotor and / or a stator.
  • FIG. 1 is exemplified a gas turbine group. This includes a known manner, a compressor 1, a combustion chamber 2, and the turbine 3.
  • the turbine 3 is shown in section.
  • a turbine stator comprises a housing 4 and vanes 61, 62, 63 and 64.
  • a turbine rotor comprises a shaft 5 and rotor blades 65, 66, 67 and 68.
  • FIG. 2 shows a side view of an exemplary turbine blade in a sectional view, which reveals the internal cooling configuration of the blade.
  • the blade 6 comprises a blade root 601, an airfoil 602, and a blade head 603.
  • a cross-section of the airfoil that reveals the airfoil profile is shown in FIG. 2b shown.
  • the profile of the airfoil has a front edge 604, a trailing edge 605, a pressure side 606 and a suction side 607.
  • cooling air channel 609 Within the airfoil, along the airfoil leading edge 604, there is a cooling air channel 609. As shown in FIG. 2b can be seen, this channel is bounded on the one hand by the wall of the airfoil in the region of the front edge 604, in the region of the pressure side 606, in the region of the suction side 607, and by a partition wall 614 extending from the suction-side airfoil wall to the pressure-side airfoil wall.
  • the cooling air channel 609 has in the fus researchen area of the Airfoil on an inlet opening 610 for cooling air, and has in the region of the blade head on an outlet opening 611 for cooling air.
  • a further serpentine running cooling air passage 608 is arranged, wherein the cooling air flowing through this is blown out in the region of the blade air trailing edge.
  • the blade is cooled in the region of the trailing edge by the blown cooling air; in the other areas of the airfoil, the airfoil is cooled purely convective.
  • ribs 613 are arranged inside the cooling air ducts, which there intensify the heat transfer from the airfoil wall to the cooling air.
  • the cooling air of the leading edge cooling air channel 609 is supplied to the inlet opening 610 and blown out again in the blade head area at the outlet opening 611, where it serves to cool the blade head and the seals, not shown.
  • a web 612 is arranged, which avoids that the cooling air is prematurely mixed with hot gas.
  • the region of the outlet opening 611 is in the FIGS. 3a and 3b shown enlarged.
  • the contour of the outlet opening 611 has a cross-section of the cooling air channel 609 substantially geometrically similar shape, but compared to this reduced in cross-section.
  • the front edge side extending cooling air channel is indicated by dashed lines.
  • the distance of the contour of the outlet opening from the airfoil outer contour is dimension A.
  • the distance between the contour of the outlet opening and the airfoil outer contour is dimension B
  • the distance of the contour of the outlet opening from the dividing wall is the dimension C.
  • the thickness of the airfoil outer wall is denoted by ⁇ .
  • C is 0 ⁇ C ⁇ ⁇ (2 ⁇ 0.25).

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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 Anmeldung bezieht sich auf eine Gasturbinenschaufel gemäss dem Oberbegriff des Anspruchs 1.The present application relates to a gas turbine blade according to the preamble of claim 1.

Stand der TechnikState of the art

Es ist bekannt, bei gekühlten Schaufeln von Gasturbinen Kühlluft am Schaufelkopf auszublasen, was beispielsweise zu einer verbesserten Kühlung der dort angeordneten Dichtungen beiträgt. Aus US 2003/156943 ist eine Turbinenschaufel bekannt geworden, welche mit einem in der Schaufelblatt-Vorderkante verlaufenden Kühlkanal mit Austrittsöffnungen im Bereich des Schaufelkopf versehen ist. Die Wanddicke der Schaufel ändert sich im Austrittsbereich nicht und damit ist die Kontur im Austrittsbereich ähnlich der Kanalkontur.It is known to blow cooling air at the blade head with cooled blades of gas turbines, which contributes, for example, to improved cooling of the seals arranged there. Out US 2003/156943 is a turbine blade has become known, which is provided with a running in the blade edge leading edge cooling channel with outlet openings in the region of the blade head. The wall thickness of the blade does not change in the exit area and thus the contour in the exit area is similar to the channel contour.

Im allgemeinen werden die Querschnitte dieser Austrittsöffnungen kleiner dimensioniert als die der Kühlluftkanäle. Sie dienen damit als Drosselstellen und begrenzen den Massenstrom des ausgeblasenen Kühlfluids, wie z.B. in der US 5 993156 offenbart.In general, the cross sections of these outlet openings are dimensioned smaller than that of the cooling air channels. They thus serve as throttling points and limit the mass flow of the blown cooling fluid, such as in the US 5,993,156 disclosed.

Die Austrittsöffnungen weisen üblicherweise kreisförmige oder elliptische Querschnitte auf, und stimmen nicht mit der Querschnittsform des Kühlkanals überein, welcher die Kühlluft zu der Austrittsöffnung führt. Der damit vorliegende abrupte Querschnittswechsel resultiert in ungünstigen Strömungsmustern, welche unter anderem zu erhöhten Druckverlusten und lokal erhöhten Materialtemperaturen führen.The outlet openings usually have circular or elliptical cross-sections, and do not coincide with the cross-sectional shape of the cooling channel, which leads the cooling air to the outlet opening. The sudden abrupt change in cross section resulting in unfavorable flow patterns, which among other things lead to increased pressure losses and locally increased material temperatures.

Darstellung der ErfindungPresentation of the invention

Gemäss einem Aspekt der vorliegenden Erfindung soll eine Gasturbinenschaufel der eingangs genannten Art so angegeben werden, dass die Nachteile des Standes der Technik vermieden werden. Spezifischer soll die Gasturbinenschaufel derart angegeben werden, dass der Wärmeübergang auf der Kühlungsseite vergleichmässigt wird und auf diese Weise ungleichmässige Temperaturvorteilungen mit lebensdauerverkürzenden Thermospannungen vermieden werden.According to one aspect of the present invention, a gas turbine blade of the type mentioned is to be specified so that the disadvantages of the prior art are avoided. More specifically, the gas turbine blade is to be specified such that the heat transfer is uniformed on the cooling side and in this way uneven Temperaturvorteilungen be avoided with life-shortening thermoelectric voltages.

Dies, neben anderen vorteilhaften Wirkungen, vermag die im Anspruch 1 beschriebene Gasturbinenschaufel zu leisten. Bei der im Anspruch 1 angegebenen Schaufel ist die Kontur der Austrittsöffnung des entlang der Vorderkante verlaufenden Kühlluftkanals dem Querschnitt des Kühlluftkanals geometrisch ähnlich gestaltet. Daraus resultiert, dass die Querschnittsübergänge beim Durchströmen der Kühlluft aus dem Kühlluftkanal in die Austrittsöffnung minimiert werden. Totwasserzonen der Kühlluft und Abweichungen der Strömungsrichtung der ausgeblasenen Kühlluft mit ihren negativen Auswirkungen werden damit vermieden.This, among other advantageous effects, can afford the gas turbine blade described in claim 1. In the blade specified in claim 1, the contour of the outlet opening of the along the leading edge extending cooling air duct is designed geometrically similar to the cross section of the cooling air duct. As a result, the cross-sectional transitions are minimized when flowing through the cooling air from the cooling air duct into the outlet opening. Dead water zones of the cooling air and deviations of the flow direction of the blown cooling air with its negative effects are thus avoided.

In einer Weiterbildung der Schaufel ist die Querschnittsfläche der Austrittsöffnung kleiner als die Querschnittsfläche des Kühlluftkanals. Damit kann die Austrittsöffnung als Drosselstelle wirken und somit zur Begrenzung des Massenstroms dienen. Das heisst, im Bereich der Austrittsöffnung ist ein Steg angeordnet. In einer Ausführungsform der Erfindung nimmt der Abstand der Konturlinie der Austrittsöffnung von der Schaufelblattaussenkontur im Bereich der Schaufelblatt-Vorderkante Werte zwischen 138% und 162% der lokalen Wanddicke der Schaufelblattwand an. Das heisst; die Höhe des Steges beträgt im Bereich der Schaufelblattvorderkante 38% bis 62% der lokalen Wanddicke. Im Bereich der saugseitigen Wand und/oder der druckseitigen Wand des Schaufelblattes nimmt der Abstand der Konturlinie der Austrittsöffnung von der Schaufelblatt-Aussenkontur Werte von 113% bis 138% der lokalen Wanddicke der Schaufelblattwand an. Die Höhe des Steges beträgt also in diesem Bereich 13% bis 38% der lokalen Wanddicke. Im Bereich der schaufelinneren Trennwand, welche beispielsweise den entlang der Vorderkante verlaufenden Kühlluftkanal von anderen Kühlluftkanälen abtrennt, liegt die Höhe des Steges in einer Ausführungsform im Bereich von 0% bis 225% der Wanddicke der Schaufelblattwand. Diese geometrischen Spezifikationen können selbstverständlich unabhängig voneinander oder in Kombination Anwendung finden. Die Wanddicke der Schaufelblattwand kann dabei in Umströmungsrichtung des Schaufelblattes variieren; in einer Ausführungsform der Erfindung ist die Wanddicke der Schaufelbfattwand im Bereich der Austrittsöffnung konstant.In a development of the blade, the cross-sectional area of the outlet opening is smaller than the cross-sectional area of the cooling air channel. Thus, the outlet opening act as a throttle point and thus serve to limit the mass flow. That is, in the region of the outlet opening a web is arranged. In one embodiment of the invention, the distance of the contour line of the outlet opening from the blade outer contour in the area of the blade leaf leading edge assumes values between 138% and 162% of the local wall thickness of the blade leaf wall. This means; the height of the web is 38% to 62% of the local wall thickness in the area of the blade leading edge. In the region of the suction-side wall and / or the pressure-side wall of the airfoil, the distance between the contour line of the outlet opening and the airfoil outer contour assumes values of 113% to 138% of the local wall thickness of the airfoil wall. The height of the web is therefore 13% to 38% of the local wall thickness in this area. Around blade-inside partition wall, which separates, for example, along the leading edge extending cooling air duct from other cooling air ducts, the height of the web is in one embodiment in the range of 0% to 225% of the wall thickness of the airfoil wall. Of course, these geometric specifications may apply independently or in combination. The wall thickness of the airfoil wall can vary in the direction of flow of the airfoil; In one embodiment of the invention, the wall thickness of the blade flap wall in the region of the outlet opening is constant.

In einer Weiterbildung der Erfindung weist der Kühlluftkanal eine am Schaufelfuss angeordnete Einlassöffnung auf. Dabei wird in einer Ausführungsform frische Kühlluft am Schaufelfuss zugeführt, welche entlang der Schaufelblattvorderkante im Schaufelblattinneren zum Schaufelkopf strömt, und dort durch die Austrittsöffnung ausströmt. Insbesondere ist in einer Weiterbildung der hier spezifizierten Schaufeln die Schaufel im Bereich des Kühlkanals rein konvektiv gekühlt ausgeführt. Das heisst, es liegen keine Öffnungen vor, durch welche Kühlluft beispielsweise als Filmkühlluft zur Schaufelblatt-Aussenseite gelangen kann. Der gesamte in den Kühlluftkanal einströmende Kühlluftmassenstrom strömt also wieder durch die Austrittsöffnung ab.In a development of the invention, the cooling air duct has an inlet opening arranged on the blade root. In one embodiment, fresh cooling air is supplied to the blade root, which flows along the blade leading edge in the blade inner side to the blade head, where it flows out through the outlet opening. In particular, in a development of the blades specified here, the blade is designed to be purely convectionally cooled in the region of the cooling channel. This means that there are no openings through which cooling air, for example as film cooling air, can reach the outside of the airfoil. The entire cooling air mass flow flowing into the cooling air duct therefore flows again through the outlet opening.

Schaufeln der vorstehend beschriebenen Art finden bevorzugt in Gasturbinen, als Bestandteile eines Rotors und/oder eines Stators, Verwendung.Blades of the type described above are preferably used in gas turbines, as components of a rotor and / or a stator.

Kurze Beschreibung der ZeichnungShort description of the drawing

Die Erfindung wird nachfolgend anhand eines in der Zeichnung illustrierten Ausführungsbeispiels näher erläutert. Im Einzelnen zeigen

  • Figur 1 eine Gasturbogruppe;
  • Figur 2 eine Gasturbinenschaufel;
  • Figur 3 einen Austrittsbereich eines Kühlluftkanals einer Gasturbinenschaufel.
The invention will be explained in more detail with reference to an embodiment illustrated in the drawing. Show in detail
  • FIG. 1 a gas turbine group;
  • FIG. 2 a gas turbine blade;
  • FIG. 3 an exit portion of a cooling air passage of a gas turbine blade.

Alle Figuren sind stark vereinfacht und dienen lediglich dem besseren Verständnis der Erfindung; sie sollen nicht zur Einschränkung der in den Ansprüchen gekennzeichneten Erfindung herangezogen werden.All figures are greatly simplified and are only for a better understanding of the invention; they should not be used to limit the invention characterized in the claims.

Wege zur Ausführung der ErfindungWays to carry out the invention

In der Figur 1 ist beispielhaft eine Gasturbogruppe dargestellt. Diese umfasst auf an sich bekannte Weise einen Verdichter 1, eine Brennkammer 2, sowie die Turbine 3. Die Turbine 3 ist im Schnitt dargestellt. Ein Turbinenstator umfasst ein Gehäuse 4 sowie Leitschaufeln 61, 62, 63 und 64. Ein Turbinenrotor umfasst eine Welle 5 sowie Laufschaufeln 65, 66, 67 und 68.In the FIG. 1 is exemplified a gas turbine group. This includes a known manner, a compressor 1, a combustion chamber 2, and the turbine 3. The turbine 3 is shown in section. A turbine stator comprises a housing 4 and vanes 61, 62, 63 and 64. A turbine rotor comprises a shaft 5 and rotor blades 65, 66, 67 and 68.

In modernen Gasturbogruppen mit hohen Heissgastemperaturen werden die Turbinenschaufeln wenigstens der ersten Turbinenstufen gekühlt ausgeführt. Ein Beispiel für eine derartige gekühlte Turbinenschaufel 6 ist in der Figur 2 dargestellt. Figur 2a zeigt dabei eine Seitenansicht einer beispielhaften Turbinenschaufel in einer Schnittdarstellung, welche die interne Kühlungskonfiguration der Schaufel erkennen lässt. Die Schaufel 6 umfasst einen Schaufelfuss 601, ein Schaufelblatt 602, sowie einen Schaufelkopf 603. Ein Querschnitt des Schaufelblattes, welcher das Schaufelblattprofil erkennen lässt, ist in der Figur 2b dargestellt. Das Profil des Schaufelblattes weist eine Vorderkante 604, eine Hinterkante 605, eine Druckseite 606 sowie eine Saugseite 607 auf. Innerhalb des Schaufelblattes verläuft entlang der Schaufelblattvorderkante 604 ein Kühlluftkanal 609. Wie in der Darstellung der Figur 2b zu erkennen ist, wird dieser Kanal einerseits von der Wand des Schaufelblattes im Bereich der Vorderkante 604, im Bereich der Druckseite 606, im Bereich der Saugseite 607, sowie von einer von der saugseitigen Schaufelblattwand zur druckseitigen Schaufelblattwand verlaufenden Trennwand 614 begrenzt. Der Kühlluftkanal 609 weist im fusseitigen Bereich des Schaufelblattes eine Eintrittsöffnung 610 für Kühlluft auf, und weist im Bereich des Schaufelkopfes eine Austrittsöffnung 611 für Kühlluft auf. Innerhalb des Schaufelblattes ist ein weiterer serpentinenförmig verlaufender Kühlluftkanal 608 angeordnet, wobei die diesen durchströmende Kühlluft im Bereich der Schaufelblatthinterkante ausgeblasen wird. Das Schaufelblatt wird im Bereich der Hinterkante durch die ausgeblasene Kühlluft gekühlt; in den weiteren Bereichen des Schaufelblattes wird das Schaufelblatt rein konvektiv gekühlt. Zur Verbesserung der konvektiven Kühlwirkung sind innerhalb der Kühlluftkanäle Rippen 613 angeordnet, welche dort den Wärmeübergang von der Schaufelblattwand zur Kühlluft intensivieren. Die Kühlluft des Vorderkanten-Kühlluftkanals 609 wird an der Einlassöffnung 610 zugeführt und im Schaufelkopfbereich an der Austrittsöffnung 611 wieder ausgeblasen, und dient dort zur Kühlung des Schaufelkopfes und der nicht dargestellten Dichtungen. Im Bereich des Schaufelkopfes ist ein Steg 612 angeordnet, welcher vermeidet, dass die Kühlluft vorschnell mit Heissgas vermischt wird.In modern gas turbine groups with high hot gas temperatures, the turbine blades of at least the first turbine stages are cooled. An example of such a cooled turbine blade 6 is shown in FIG FIG. 2 shown. FIG. 2a shows a side view of an exemplary turbine blade in a sectional view, which reveals the internal cooling configuration of the blade. The blade 6 comprises a blade root 601, an airfoil 602, and a blade head 603. A cross-section of the airfoil that reveals the airfoil profile is shown in FIG FIG. 2b shown. The profile of the airfoil has a front edge 604, a trailing edge 605, a pressure side 606 and a suction side 607. Within the airfoil, along the airfoil leading edge 604, there is a cooling air channel 609. As shown in FIG FIG. 2b can be seen, this channel is bounded on the one hand by the wall of the airfoil in the region of the front edge 604, in the region of the pressure side 606, in the region of the suction side 607, and by a partition wall 614 extending from the suction-side airfoil wall to the pressure-side airfoil wall. The cooling air channel 609 has in the fusseitigen area of the Airfoil on an inlet opening 610 for cooling air, and has in the region of the blade head on an outlet opening 611 for cooling air. Within the airfoil, a further serpentine running cooling air passage 608 is arranged, wherein the cooling air flowing through this is blown out in the region of the blade air trailing edge. The blade is cooled in the region of the trailing edge by the blown cooling air; in the other areas of the airfoil, the airfoil is cooled purely convective. To improve the convective cooling effect, ribs 613 are arranged inside the cooling air ducts, which there intensify the heat transfer from the airfoil wall to the cooling air. The cooling air of the leading edge cooling air channel 609 is supplied to the inlet opening 610 and blown out again in the blade head area at the outlet opening 611, where it serves to cool the blade head and the seals, not shown. In the region of the blade head, a web 612 is arranged, which avoids that the cooling air is prematurely mixed with hot gas.

Der Bereich der Austrittsöffnung 611 ist in den Figuren 3a und 3b vergrössert dargestellt. In der Draufsicht der Figur 3a ist zu erkennen, dass die Kontur der Austrittsöffnung 611 eine dem Querschnitt des Kühlluftkanals 609 im Wesentlichen geometrisch ähnliche Form aufweist, diesem gegenüber aber im Querschnitt verkleinert ist. Der vorderkantenseitig verlaufende Kühlluftkanal ist gestrichelt angedeutet. Im Bereich der Schaufelblatt-Vorderkante 604 beträgt der Abstand der Kontur der Austrittsöffnung von der Schaufelblatt-Aussenkontur das Mass A. Im Bereich der druckseitigen Wand 606 und der saugseitigen Wand Schaufelblattes 607 beträgt der Abstand der Kontur der Austrittsöffnung von der Schaufelblatt-Aussenkontur das Maß B. Im Bereich der Trennwand 614 beträgt der Abstand der Kontur der Austrittsöffnung von der Trennwand das Mass C. Die Dicke der Schaufelblattaussenwand ist mit δ bezeichnet. Dabei beträgt A bevorzugt A=δ (1,5±0,12). B beträgt B=δ ·(1,25±0,12). C beträgt 0<C<δ ·(2±0,25).The region of the outlet opening 611 is in the FIGS. 3a and 3b shown enlarged. In the plan view of FIG. 3a It can be seen that the contour of the outlet opening 611 has a cross-section of the cooling air channel 609 substantially geometrically similar shape, but compared to this reduced in cross-section. The front edge side extending cooling air channel is indicated by dashed lines. In the area of the airfoil leading edge 604, the distance of the contour of the outlet opening from the airfoil outer contour is dimension A. In the region of the pressure-side wall 606 and the suction-side wall airfoil 607, the distance between the contour of the outlet opening and the airfoil outer contour is dimension B In the region of the dividing wall 614, the distance of the contour of the outlet opening from the dividing wall is the dimension C. The thickness of the airfoil outer wall is denoted by δ. In this case, A is preferably A = δ (1.5 ± 0.12). B is B = δ · (1.25 ± 0.12). C is 0 <C <δ · (2 ± 0.25).

Obschon die Erfindung vorstehend anhand eines Ausführungsbeispiels näher erläutert wurde, ist für den Fachmann selbstverständlich, dass dieses Ausführungsbeispiel die Erfindung nicht einschränkt. Im Lichte der vorstehenden Beschreibung eröffnen sich für einen Fachmann weitere im Umfang der Patentansprüche enthaltene Ausführungsformen der Erfindung.Although the invention has been explained in detail above with reference to an exemplary embodiment, it is obvious to the person skilled in the art that this exemplary embodiment does not restrict the invention. In light of the above description, those skilled in the art will be aware of other embodiments of the invention within the scope of the claims.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Verdichtercompressor
22
Brennkammercombustion chamber
33
Turbineturbine
44
Gehäusecasing
55
Wellewave
66
Turbinenschaufelturbine blade
61, 62, 63, 6461, 62, 63, 64
Leitschaufeln, StatorschaufelnVanes, stator vanes
65, 66, 67, 6865, 66, 67, 68
Laufschaufeln, RotorschaufelnBlades, rotor blades
601601
Schaufelfussblade root
602602
Schaufelblattairfoil
603603
Schaufelkopfshovel head
604604
Schaufelblatt-VorderkanteAn airfoil leading edge
605605
Schaufellbaltt-HinterkanteSchaufellbaltt trailing edge
606606
druckseitige Schaufelblattwandpressure side airfoil wall
607607
Saugseitige SchaufelblattwandSuction-side airfoil wall
608608
KühlluftkanalCooling air duct
609609
vorderkantenseitiger Kühlluftkanalfront edge-side cooling air duct
610610
KühllufteinlassCooling air intake
611611
Austrittsöffnungoutlet opening
612612
Stegweb
613613
KühlkanalrippenCooling channel fins
614614
Trennwandpartition wall

Claims (9)

  1. Gas turbine blade (6), with a blade airfoil (602), which extends from a blade root (601) to a blade tip (603), wherein the blade airfoil comprises a blade airfoil leading edge (604) and a cooling air passage (609) which extends along the leading edge of the blade airfoil inside the blade airfoil, which cooling air passage is defined by the wall of the blade airfoil on the leading edge (604), and also on the suction side (607) and the pressure side (606) of the blade airfoil, and which, furthermore, is defined by a partition (614) which extends inside the blade airfoil from the pressure-side wall to the suction-side wall, and which cooling air passage (609) has an outlet opening (611) which is arranged in the region of the blade tip, wherein the cross-sectional area of the outlet opening (611) is geometrically similar to the cross-sectional area of the cooling air passage (609), wherein the cross-sectional area of the outlet opening (611) is smaller than the cross-sectional area of the cooling air passage (609), characterized in that the cross-sectional areas of the outlet opening (611) and of the cooling air passage (609) are aligned with identical contour to one another.
  2. Gas turbine blade according to Claim 1, characterized in that the distance (A) of the contour of the outlet opening (611) with respect to the outer contour of the blade airfoil in the region of the leading edge is within the range of 138% to 162% of the local wall thickness (δ) of the wall of the blade airfoil.
  3. Gas turbine blade according to Claim 1, characterized in that the distance (B) of the contour of the outlet opening with respect to the outer contour of the blade airfoil in the region of the pressure-side wall and/or the suction-side wall is within the range of 113% to 138% of the local wall thickness (δ) of the wall of the blade airfoil.
  4. Gas turbine blade according to Claim 1, characterized in that in the region of the partition (614), the distance (C) of the contour of the outlet opening from the partition is within the range of 0% to 225% of the wall thickness (δ) of the wall of the blade airfoil.
  5. Gas turbine blade according to one of the preceding claims, characterized in that the wall thickness of the wall of the blade airfoil is constant in the region of the outlet opening.
  6. Gas turbine blade according to one of the preceding claims, characterized in that the cooling air passage (609) has an inlet opening (610) which is arranged in the region of the blade root (601).
  7. Gas turbine blade according to one of the preceding claims, characterized in that the blade is designed in a way in which it is purely convectively cooled in the region of the cooling passage.
  8. Gas turbine assembly, especially rotor or stator of a gas turbine, comprising at least one gas turbine blade according to one of the preceding claims.
  9. Gas turbine, comprising at least one gas turbine blade according to one of Claims 1 to 7.
EP06725419.3A 2005-04-14 2006-03-30 Convectively cooled gas turbine blade Not-in-force EP1869291B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
RU2005110990/06A RU2425982C2 (en) 2005-04-14 2005-04-14 Gas turbine vane
PCT/EP2006/061163 WO2006108764A1 (en) 2005-04-14 2006-03-30 Convectively cooled gas turbine blade

Publications (2)

Publication Number Publication Date
EP1869291A1 EP1869291A1 (en) 2007-12-26
EP1869291B1 true EP1869291B1 (en) 2014-07-30

Family

ID=36615644

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06725419.3A Not-in-force EP1869291B1 (en) 2005-04-14 2006-03-30 Convectively cooled gas turbine blade

Country Status (4)

Country Link
US (1) US7766619B2 (en)
EP (1) EP1869291B1 (en)
RU (1) RU2425982C2 (en)
WO (1) WO2006108764A1 (en)

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FR3056631B1 (en) * 2016-09-29 2018-10-19 Safran IMPROVED COOLING CIRCUIT FOR AUBES
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US12012866B1 (en) * 2023-06-12 2024-06-18 Rtx Corporation Non-circular stress reducing crossover

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Also Published As

Publication number Publication date
RU2425982C2 (en) 2011-08-10
US20080181784A1 (en) 2008-07-31
RU2005110990A (en) 2006-10-20
EP1869291A1 (en) 2007-12-26
WO2006108764A1 (en) 2006-10-19
US7766619B2 (en) 2010-08-03

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