EP1869291A1 - Convectively cooled gas turbine blade - Google Patents

Convectively cooled gas turbine blade

Info

Publication number
EP1869291A1
EP1869291A1 EP06725419A EP06725419A EP1869291A1 EP 1869291 A1 EP1869291 A1 EP 1869291A1 EP 06725419 A EP06725419 A EP 06725419A EP 06725419 A EP06725419 A EP 06725419A EP 1869291 A1 EP1869291 A1 EP 1869291A1
Authority
EP
European Patent Office
Prior art keywords
airfoil
gas turbine
cooling air
wall
blade
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP06725419A
Other languages
German (de)
French (fr)
Other versions
EP1869291B1 (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
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1869291A1 publication Critical patent/EP1869291A1/en
Application granted granted Critical
Publication of EP1869291B1 publication Critical patent/EP1869291B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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.
  • Gas turbine blade of the type mentioned are specified so that the disadvantages of the prior art are avoided. More specifically, the gas turbine blade should be specified such that the heat transfer on the cooling side is made uniform and in this way uneven temperature distributions are 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.
  • Outlet opening smaller than the cross-sectional area of the cooling air duct.
  • 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 that the height of the web in the region of the blade leading edge is 38% to 62% of the local wall thickness.
  • 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 the range from 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 airfoil 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 in an embodiment, which along the blade leading edge in the blade inner to the Blade head flows, and there flows 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, use.
  • FIG. 1 shows a gas turbine group
  • FIG. 2 shows a gas turbine blade
  • FIG. 3 shows an exit region of a cooling air channel of FIG
  • a gas turbine group is shown by way of example. 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 a shows a side view of an exemplary turbine blade in a sectional view, which shows 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.
  • the profile of the airfoil has a front edge 604, a trailing edge 605, a pressure side 606 and a suction side 607. As can be seen in the illustration of FIG.
  • this channel is formed, 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 bounded 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 practiceen area of the airfoil on an inlet opening 610 for cooling air, and has in the region of the blade head an outlet opening 61 1 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 port 610 and blown in the blade head area at the outlet opening 61 1 again, 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 shown enlarged in Figures 3a and 3b.
  • the contour of the outlet opening 611 has a shape that is substantially geometrically similar to the cross section of the cooling air channel 609, but is reduced in cross-section relative thereto.
  • 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).

Abstract

The invention relates to a gas turbine blade comprising a cooling air channel (609) which extends along the front edge (604) of the blade and has an outlet (611) arranged in the region of the blade head. The contour of the outlet is geometrically similar to the cross-section of the cooling air channel, enabling flow inhomogeneities of the cooling air flow, which locally negatively influence the heat transfer and thus the cooling efficiency, to be eliminated.

Description

Beschreibungdescription
KONVEKTIV GEKÜHLTE GASTURBINENSCHAUFELCONVECTIVELY COOLED GUESTURBINE BUCKET
Technisches GebietTechnical area
[0001] 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
[0002] Es ist bekannt, bei gekühlten Schaufeln von Gasturbinen Kühlluft am Schaufelkopf auszublasen, was beispielsweise zu einer verbesserten Kühlung der dort angeordneten Dichtungen beiträgt. Die Querschnitte dieser Austrittsöffnungen werden allgemein kleiner dimensioniert als die der Kühlluftkanäle. Sie dienen damit als Drosselstellen und begrenzen den Massenstrom des ausgeblasenen Kühlfluids. 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.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. The cross sections of these outlet openings are generally smaller than those of the cooling air channels. They serve as throttling points and limit the mass flow of the blown cooling fluid. 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
[0003] Gemäss einem Aspekt der vorliegenden Erfindung soll eineAccording to one aspect of the present invention, a
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 Temperaturverteilungen mit lebensdauerverkürzenden Thermospannungen vermieden werden.Gas turbine blade of the type mentioned are specified so that the disadvantages of the prior art are avoided. More specifically, the gas turbine blade should be specified such that the heat transfer on the cooling side is made uniform and in this way uneven temperature distributions are avoided with life-shortening thermoelectric voltages.
[0004] 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, is able to 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.
[0005] In einer Weiterbildung der Schaufel ist die Querschnittsfläche derIn a further development of the blade, the cross-sectional area of the
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 Schaufelblattwand im Bereich der Austrittsöffnung konstant.Outlet opening smaller than the cross-sectional area of the cooling air duct. 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 that the height of the web in the region of the blade leading edge is 38% to 62% of the local wall thickness. 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. In the region of the blade-inner partition wall, which, for example, separates the cooling air duct running along the leading edge from other cooling air ducts, in one embodiment the height of the web is in the range from 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 airfoil wall in the region of the outlet opening is constant.
[0006] 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. [0007] Schaufeln der vorstehend beschriebenen Art finden bevorzugt in Gasturbinen, als Bestandteile eines Rotors und/oder eines Stators, Verwendung.In one development of the invention, the cooling air duct has an inlet opening arranged on the blade root. In this case, fresh cooling air is supplied to the blade root in an embodiment, which along the blade leading edge in the blade inner to the Blade head flows, and there flows 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. Blades of the type described above are preferably used in gas turbines, as components of a rotor and / or a stator, use.
Kurze Beschreibung der ZeichnungShort description of the drawing
[0008] Die Erfindung wird nachfolgend anhand eines in der Zeichnung illustriertenThe invention will be described below with reference to an illustrated in the drawing
Ausführungsbeispiels näher erläutert. Im Einzelnen zeigen [0009] Figur 1 eine Gasturbogruppe; [0010] Figur 2 eine Gasturbinenschaufel; [0011] Figur 3 einen Austrittsbereich eines Kühlluftkanals einerEmbodiment explained in more detail. In detail, FIG. 1 shows a gas turbine group; FIG. 2 shows a gas turbine blade; FIG. 3 shows an exit region of a cooling air channel of FIG
Gastu rbi nenschaufel . [0012] Alle Figuren sind stark vereinfacht und dienen lediglich dem besserenGastro ranger shovel. All figures are greatly simplified and are only for the better
Verständnis der Erfindung; sie sollen nicht zur Einschränkung der in denUnderstanding of the invention; they should not be restricted to the
Ansprüchen gekennzeichneten Erfindung herangezogen werden.Claims characterized invention are used.
Wege zur Ausführung der ErfindungWays to carry out the invention
[0013] 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 figure 1 a gas turbine group is shown by way of example. 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.
[0014] 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 Schaufel kopfes eine Austrittsöffnung 61 1 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 Schaufel köpf bereich an der Austrittsöffnung 61 1 wieder ausgeblasen, und dient dort zur Kühlung des Schaufelkopfes und der nicht dargestellten Dichtungen. Im Bereich des Schaufel kopfes ist ein Steg 612 angeordnet, welcher vermeidet, dass die Kühlluft vorschnell mit Heissgas vermischt wird. [0015] 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).In modern gas turbine groups with high hot gas temperatures, the turbine blades are cooled at least the first turbine stages. An example of such a cooled turbine blade 6 is shown in the figure 2. FIG. 2 a shows a side view of an exemplary turbine blade in a sectional view, which shows 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. The profile of the airfoil has a front edge 604, a trailing edge 605, a pressure side 606 and a suction side 607. As can be seen in the illustration of FIG. 2b, this channel is formed, 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 bounded 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 an outlet opening 61 1 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 port 610 and blown in the blade head area at the outlet opening 61 1 again, 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. The region of the outlet opening 611 is shown enlarged in Figures 3a and 3b. In the plan view of FIG. 3 a, it can be seen that the contour of the outlet opening 611 has a shape that is substantially geometrically similar to the cross section of the cooling air channel 609, but is reduced in cross-section relative thereto. 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).
[0016] 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 embodiment, it is obvious to the skilled person that this embodiment does not limit 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
[0017] 1 Verdichter1 compressor
[0018] 2 Brennkammer2 combustion chamber
[0019] 3 Turbine3 turbine
[0020] 4 Gehäuse4 housing
[0021] 5 Welle5 shaft
[0022] 6 Turbinenschaufel6 turbine blade
[0023] 61 , 62, 63, 64 Leitschaufeln, Statorschaufeln61, 62, 63, 64 vanes, stator blades
[0024] 65, 66, 67, 68 Laufschaufeln, Rotorschaufeln65, 66, 67, 68 blades, rotor blades
[0025] 601 Schaufelfuss601 blade root
[0026] 602 Schaufelblatt [0027] 603 Schaufelkopf602 airfoil 603 blade head
[0028] 604 Schaufelblatt-Vorderkante604 airfoil leading edge
[0029] 605 Schaufelbaltt-Hinterkante605 Schaufelbaltt trailing edge
[0030] 606 druckseitige Schaufelblattwand606 pressure-side airfoil wall
[0031] 607 Saugseitige Schaufelblattwand607 suction side airfoil wall
[0032] 608 Kühlluftkanal[0032] 608 cooling air channel
[0033] 609 vorderkantenseitiger Kühlluftkanal609 front edge-side cooling air duct
[0034] 610 Kühllufteinlass[0034] 610 Cooling air inlet
[0035] 611 Austrittsöffnung611 outlet opening
[0036] 612 Steg612 bridge
[0037] 613 Kühlkanalrippen[0037] 613 cooling channel ribs
[0038] 614 Trennwand 614 partition wall

Claims

Ansprüche claims
1. Gasturbinenschaufel (6), mit einem Schaufelblatt (602), welches sich von einem Schaufelfuss (601) zu einem Schaufelkopf (603) erstreckt, wobei das Schaufelblatt eine Schaufelblatt-Vorderkante (604) und einen entlang der Schaufelblatt-Vorderkante im Schaufelblattinneren verlaufenden Kühlluftkanal (609) umfasst, welcher Kühlluftkanal an der Vorderkante (604) sowie an der Saugseite (607) und der Druckseite (606) des Schaufelblattes von der Schaufelblattwand begrenzt ist, und der weiterhin von einer im Schaufelblattinneren von der druckseitigen Wand zu der saugseitigen Wand verlaufenden Trennwand (614) begrenzt ist, und welcher Kühlluftkanal eine im Bereich des Schaufel kopfes angeordnete Austrittsöffnung (611) aufweist, dadurch gekennzeichnet, dass die Kontur der Öffnung (611) dem Querschnitt des Kühlluftkanals geometrisch ähnlich ist.A gas turbine blade (6) having an airfoil (602) extending from a blade root (601) to a blade head (603), said airfoil having a blade leading edge (604) and a blade blade leading edge in said airfoil inner Cooling air passage (609), which cooling air channel at the front edge (604) and on the suction side (607) and the pressure side (606) of the airfoil is bounded by the airfoil wall, and further from a in the airfoil inside of the pressure side wall to the suction side wall extending partition (614) is limited, and which cooling air channel has a head arranged in the region of the blade outlet opening (611), characterized in that the contour of the opening (611) is geometrically similar to the cross section of the cooling air duct.
2. Gasturbinenschaufel gemäss Anspruch 1 , dadurch gekennzeichnet, dass die Querschnittsfläche der Austrittsöffnung (611) kleiner ist als die Querschnittsfläche des Kühlluftkanals (609).2. Gas turbine blade according to claim 1, characterized in that the cross-sectional area of the outlet opening (611) is smaller than the cross-sectional area of the cooling air channel (609).
3. Gasturbinenschaufel gemäss einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass der Abstand (A) der Kontur der Austrittsöffnung (611) von der Schaufelblatt-Aussenkontur im Bereich der Vorderkante im Bereich von 138% und 162% der lokalen Wanddicke (δ) der Schaufelblattwand beträgt.3. Gas turbine blade according to one of the preceding claims, characterized in that the distance (A) of the contour of the outlet opening (611) of the airfoil outer contour in the region of the leading edge in the range of 138% and 162% of the local wall thickness (δ) of the airfoil wall is.
4. Gasturbinenschaufel gemäss einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass der Abstand (B) der Kontur der Austrittsöffnung von der Schaufelblatt-Aussenkontur im Bereich der druckseitigen Wand und/oder der saugseitigen Wand im Bereich von 1 13% und 138% der lokalen Wanddicke (δ) der Schaufelblattwand betagt.4. Gas turbine blade according to one of the preceding claims, characterized in that the distance (B) of the contour of the outlet opening of the airfoil outer contour in the region of the pressure-side wall and / or the suction-side wall in the range of 1 13% and 138% of the local wall thickness (δ) of the airfoil wall.
5. Gasturbinenschaufel gemäss einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass im Bereich der Trennwand (614) der Abstand (C)der Kontur der Austrittsöffnung von der Trennwand im Bereich von 0% bis 225% der Wanddicke (δ) der Schaufelblattwand beträgt.5. Gas turbine blade according to one of the preceding claims, characterized in that in the region of the dividing wall (614) the distance (C) of the contour of the outlet opening from the dividing wall in the range of 0% to 225% the wall thickness (δ) of the airfoil wall is.
6. Gasturbinenschaufel gemäss einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass im Bereich der Austrittsöffnung die Wanddicke der Schaufelblattwand konstant ist.6. Gas turbine blade according to one of the preceding claims, characterized in that in the region of the outlet opening, the wall thickness of the airfoil wall is constant.
7. Gasturbinenschaufel gemäss einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass der Kühlluftkanal (609) eine im Bereich des Schaufelfusses (601) angeordnete Einlassöffnung (610) aufweist.7. Gas turbine blade according to one of the preceding claims, characterized in that the cooling air channel (609) in the region of the blade root (601) arranged inlet opening (610).
8. Gasturbinenschaufel gemäss einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass die Schaufel im Bereich des Kühlkanals rein konvektionsgekühlt ausgeführt ist.8. Gas turbine blade according to one of the preceding claims, characterized in that the blade in the region of the cooling channel is designed purely convection cooled.
9. Gasturbinenbaugruppe, insbesondere Rotor oder Stator einer Gasturbine, umfassend wenigstens eine Gasturbinenschaufel gemäss einem der vorstehenden Ansprüche.9. gas turbine assembly, in particular rotor or stator of a gas turbine, comprising at least one gas turbine blade according to one of the preceding claims.
10. Gasturbine, umfassend wenigstens eine Gasturbinenschaufel gemäss einem der Ansprüche 1 bis 8. 10. Gas turbine, comprising at least one gas turbine blade according to one of claims 1 to 8.
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

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

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EP (1) EP1869291B1 (en)
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US20080181784A1 (en) 2008-07-31
RU2005110990A (en) 2006-10-20
WO2006108764A1 (en) 2006-10-19
US7766619B2 (en) 2010-08-03
RU2425982C2 (en) 2011-08-10
EP1869291B1 (en) 2014-07-30

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