EP1644614A1 - Cooled blade for a gas turbine - Google Patents

Cooled blade for a gas turbine

Info

Publication number
EP1644614A1
EP1644614A1 EP04766104A EP04766104A EP1644614A1 EP 1644614 A1 EP1644614 A1 EP 1644614A1 EP 04766104 A EP04766104 A EP 04766104A EP 04766104 A EP04766104 A EP 04766104A EP 1644614 A1 EP1644614 A1 EP 1644614A1
Authority
EP
European Patent Office
Prior art keywords
blade
cooling
bores
flow
cooling channel
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
EP04766104A
Other languages
German (de)
French (fr)
Other versions
EP1644614B1 (en
Inventor
Shailendra Naik
Sacha Parneix
Ulrich Rathmann
Helene Saxer-Felici
Stefan Schlechtriem
Beat Von Arx
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 EP1644614A1 publication Critical patent/EP1644614A1/en
Application granted granted Critical
Publication of EP1644614B1 publication Critical patent/EP1644614B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/185—Two-dimensional patterned serpentine-like
    • 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
    • F05D2260/211—Heat transfer, e.g. cooling by intercooling, e.g. during a compression cycle

Definitions

  • the present invention relates to the field of gas turbine technology. It relates to a cooled blade for a gas turbine according to the preamble of claim 1.
  • Such a blade is e.g. known from US-A-4,278,400.
  • FIG. 1 shows a basic configuration of such a shovel with a shroud.
  • the blade 10 comprises an airfoil 11 which merges downwards into a blade root 12 via a blade shaft 25. At the upper end, the airfoil 11 merges into a shroud section 21 which, in the case of a complete shroud, together with the shroud sections of the other
  • Blades form a closed, ring-shaped shroud.
  • the airfoil 11 has a leading edge 19, which is flown by the hot gas, and a rear edge 20.
  • a plurality of radial cooling channels 13, 14 and 15 are arranged, which are connected to one another in terms of flow by deflection regions 17, 18 and one Form a serpentine with several turns (see the flow arrows in the cooling channels 13, 14, 15 of FIG. 1).
  • the cooling medium Due to the one-time passage of the cooling medium through the serpentine cooling channels 13, 14, 15, the cooling medium flows through the cooling channels with increasing temperature and reaches the highest temperature in the last cooling channel 15 of the rear edge 20.
  • the rear edge 20 of the blade 10 can therefore be below certain excessive operating temperatures of the cooling medium and the blade material or metal.
  • the resulting mismatch of the metal temperature over the axial length of the blade can lead to high temperature creep and consequently to the deformation of the trailing edge 20.
  • the secondary effect of the trailing edge deformation is a tilting of the shroud segments 21 in the axial, radial and circumferential direction.
  • the tilting of the shroud segments 21 can lead to the gaps between individual shroud segments opening and the entry of high-temperature hot gas into the shroud cavity.
  • the temperatures of the shroud metal can rise significantly and quickly cause the shroud to creep and ultimately lead to the high-temperature failure of the shroud.
  • This known type of multiple supply with cooling medium has various disadvantages: the injector changes the pressure conditions and flow conditions in the cooling ducts massively compared to the configuration with single supply through the entrance of the cooling duct at the front edge. In particular, a balance must be found between the cooling medium flowing out at the front edge for film cooling and the cooling medium drawn in by the injector. This requires a completely new design of the blade cooling, which is difficult to adapt to changing requirements.
  • the injector principle and the associated negative pressure generation are not suitable for blades without film cooling of the leading edge and blades with a cooled shroud.
  • the object is achieved by the entirety of the features of claim 1.
  • the essence of the invention is that the additional flow is supplied via bores which run transversely through the blade or the blade shaft and are directly or indirectly connected to the deflection region.
  • the pressure and the temperature of the additional flow supplied through the core opening are the same as for the main flow flowing into the main cooling inlet.
  • the holes can open directly into the deflection area. However, they can also open into a radially extending channel below the deflection area, which is connected to the deflection area.
  • a first preferred embodiment of the invention is characterized in that a radially oriented core opening is provided in the blade root and that the bores run through the blade shaft and open into the core opening.
  • At least two bores lying opposite one another are provided which run obliquely upward in the direction of flow and each form an angle between 30 ° and 90 ° with the vertical.
  • the bores are staggered in the radial and axial directions, the bores having a predetermined inner diameter, the radial distance of the bores, standardized to the inner diameter, in the range between 1 and 4, the axial distance, standardized to the inner diameter, in the range is between 0 and 3, and the radial distance of the upper bore from the second deflection area, normalized to the inside diameter, is in the range between 1 and 4.
  • second means are provided which ensure that the main flow of the cooling medium through the first cooling channel remains essentially unchanged despite the addition of the additional flow.
  • the second means comprise additional outlet openings which are arranged between the main cooling inlet and the second deflection area and through which a partial flow of the main flow of the cooling medium emerges.
  • the blade has a shroud section at the upper end and the additional outlet openings are bores arranged in the shroud section. This also enables significantly improved cooling of the shroud.
  • FIG. 1 shows in longitudinal section the configuration of a cooled gas turbine blade with multiple supply of the cooling medium and cooled cover band according to a preferred embodiment of the invention
  • FIG. 2 shows the foot region of the blade from FIG. 1 in an enlarged view with two bores for supplying the additional cooling medium flow; 3, 4 each show a section through the base of the blade from FIG. 2 in a plane perpendicular to the section plane of FIG. 2 through one of the two bores for supplying the additional coolant flow;
  • FIGS. 1, 2 shows a top view of the shroud section of the blade from FIGS. 1, 2;
  • FIG. 6-8 different sections through the shroud area of the blade from Fig. 1, 2 along the parallel sectional planes A-A, B-B and C-C shown in Fig. 5.
  • FIGS. 1 to 4 A preferred embodiment of a cooled gas turbine blade with multiple supply of the cooling medium according to the invention is shown in FIGS. 1 to 4.
  • the main flow of the cooling medium in the area of the blade shaft 25 enters the cooling channel 13 from below through a main cooling inlet 16 and partly passes through openings in the shroud section 21 (bores 27,..., 29 in FIGS. 5 to 8) and partly along the rear edge 20 again (see the arrows drawn in FIG. 1 on the shroud section 21 and on the rear edge 20).
  • Additional cooling medium is supplied through the blade shaft 25 and a core opening 24 present in the blade root by means of two bores 22, 23.
  • the bores 22, 23 are - as can be clearly seen from FIGS. 2 to 4 - staggered in the radial and in the axial direction and lie opposite one another (FIGS. 3, 4).
  • the bores 22, 23 are inclined at an angle between 30 ° and 90 ° to the vertical, whereby they run obliquely upwards in the direction of flow (from the outside inwards).
  • the bores 22, 23 end in the core opening 24 in the blade root 12. They are thus incorporated in the area of the blade 10 that serves to support and remove the cast core and is therefore available anyway.
  • the bores 22, 23 can also extend further up and open directly into the deflection area 18. Furthermore, it is conceivable to provide a radially arranged quartz rod instead of the core opening, which ensures a connection of the bores to the deflection area.
  • the purpose of the multiple supply of cooling medium is to introduce cooler cooling medium directly into the rear edge area of the blade 10. This introduction takes place in such a way that the main flow of the cooling medium supplied through the main cooling inlet 16 is prevented or blocked as little as possible.
  • the axial distance x between the bores 22 and 23 is, normalized to the diameter d of the bores 22, 23, preferably in a range of x / d between 0 and 3 (see FIG. 2).
  • the radial distance y between the bores 22 and 23 is, normalized to the diameter d, preferably in a range of y / d between 1 and 4 (see FIG. 2).
  • the distance of the upper bore 22 normalized to d from the second inner deflection area 18 is preferably in a range of 1 / d between 1 and 4 (FIG. 2).
  • further bores 27, 28, 29 are provided in the shroud section 21 of the blade (FIGS. 5 to 8).
  • the purpose of these additional bores 27, 28, 29 is to ensure that the mass flow of the cooling medium in the front cooling channel 13 remains largely unchanged despite the supply of the additional cooling medium through the bores 23, 24.
  • the cooling medium emerging through the bores 27, 28, 29 serves to actively cool the shroud section.
  • the cooling bores 27, 28, 29 in the shroud section 21 preferably have an inner diameter in the range between 0.6 mm and 4 mm. All three bores 27, 28, 29 are positioned and dimensioned on the shroud section 21 in such a way that an uneven beam penetration into the main stream of the shroud cavity takes place.
  • the cooling medium has the same pressure and the same temperature. There is therefore a mixture of the cooling medium main flow with the additional flow within the deflection region 18, which leaves the pressure and the flow rate largely unchanged.
  • the main flow is deflected by approximately 135 °.
  • the additional flow is then advantageously supplied at a point of the deflection area 18 where a deflection of approximately 90 ° has already taken place. If - starting from a blade configuration without multiple supply of the cooling medium - bores 22, 23 and 27,..., 29 are provided in the region of the blade root 12 and in the shroud section 21 according to FIG. 1, the cooling in the region is provided the trailing edge 20 is significantly improved without the main cooling flow and thus the cooling of the remaining blade being changed. Active cooling of the shroud section 21 is also obtained.
  • the blade does not have a shroud through which a part of the cooling medium flow exits, it is necessary to expand the cross section of the second cooling channel 15 so that it takes into account the additional flow mixed in the second deflection area 18.

Landscapes

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

Abstract

The invention relates to a cooled blade (10) for a gas turbine. Said blade comprises a paddle (11) leading from a blade root (12) and a blade shaft (25), said paddle having a leading edge (19) and a trailing edge (20), in addition to a plurality of radially extending cooling channels (13, 14, 15) in its interior that are fluidically connected in sequence. A first cooling channel (13) is traversed along the leading edge (19) and a second cooling channel (15) is traversed along the trailing edge (20), from the blade root (12) to the tip of the paddle (11), by a primary stream of coolant and the outlet of the first cooling channel (13) is connected to the inlet of the second cooling channel (15) via a first deviation zone (17), a third cooling channel (14) that is situated between the first and the second cooling channels (13, 15) and a second deviation zone (18). The blade is provided with elements (22, 23, 24), by means of which a supplementary stream of cooler coolant is added externally to the heated primary stream of coolant that flows from the third cooling channel (14) into the second cooling channel (15). Bores in the vicinity of the blade root constitute said elements.

Description

BESCHREIBUNG DESCRIPTION
GEKÜHLTE SCHAUFEL FÜR EINE GASTURBINECOOLED SHOVEL FOR A GAS TURBINE
TECHNISCHES GEBIETTECHNICAL AREA
Die vorliegende Erfindung bezieht sich auf das Gebiet der Gasturbinentechnik. Sie betrifft eine gekühlte Schaufel für eine Gasturbine gemäss dem Oberbegriff des Anspruchs 1.The present invention relates to the field of gas turbine technology. It relates to a cooled blade for a gas turbine according to the preamble of claim 1.
Eine solche Schaufel ist z.B. aus der Druckschrift US-A-4,278,400 bekannt.Such a blade is e.g. known from US-A-4,278,400.
STAND DER TECHNIKSTATE OF THE ART
Bei modernen Gasturbinen mit hohem Wirkungsgrad werden mit einem Deckband versehene Schaufeln eingesetzt, die während des Betriebes Heissgasen mit Temperaturen von mehr als 1200 K und Drücken von mehr als 6 bar ausgesetzt sind. In Fig. 1 ist eine grundlegende Konfiguration einer solchen Schaufel mit Deckband dargestellt. Die Schaufel 10 umfasst ein Schaufelblatt 11, dass nach unten zu über einen Schaufelschaft 25 in einen Schaufelfuss 12 übergeht. Am oberen Ende geht das Schaufelblatt 11 in einen Deckbandabschnitt 21 über, der bei einem vollstän- digen Schaufelkranz zusammen mit den Deckbandabschnitten der anderenIn modern gas turbines with a high degree of efficiency, blades with a cover band are used which are exposed to hot gases during operation at temperatures of more than 1200 K and pressures of more than 6 bar. 1 shows a basic configuration of such a shovel with a shroud. The blade 10 comprises an airfoil 11 which merges downwards into a blade root 12 via a blade shaft 25. At the upper end, the airfoil 11 merges into a shroud section 21 which, in the case of a complete shroud, together with the shroud sections of the other
Schaufeln ein geschlossenes, ringförmiges Deckband bildet. Das Schaufelblatt 11 hat eine Vorderkante 19, die von dem Heissgas angeströmt wird, und eine Hinterkante 20. Im Inneren des Schaufelblattes 11 sind mehrere radiale Kühlkanäle 13, 14 und 15 angeordnet, die durch Umlenkbereiche 17, 18 untereinander strö- mungsmässig verbunden sind und eine Serpentine mit mehreren Windungen bilden (siehe die Strömungspfeile in den Kühlkanälen 13, 14, 15 der Fig. 1).Blades form a closed, ring-shaped shroud. The airfoil 11 has a leading edge 19, which is flown by the hot gas, and a rear edge 20. Inside the airfoil 11, a plurality of radial cooling channels 13, 14 and 15 are arranged, which are connected to one another in terms of flow by deflection regions 17, 18 and one Form a serpentine with several turns (see the flow arrows in the cooling channels 13, 14, 15 of FIG. 1).
Aufgrund des Einmaldurchlaufs des Kühlmediums durch die serpentinenartig hin- tereinandergeschalteten Kühlkanäle 13, 14, 15 strömt das Kühlmedium mit zu- nehmender Temperatur durch die Kühlkanäle und erreicht die höchste Temperatur im letzten Kühlkanal 15 der Hinterkante 20. Die Hinterkante 20 der Schaufel 10 kann daher unter bestimmten Betriebsbedingungen übermässige hohe Temperaturen des Kühlmediums und des Schaufelmaterials bzw. -metalls erreichen. Die sich daraus ergebende Fehlanpassung der Metalltemperatur über die axiale Länge der Schaufel kann zum Hochtemperaturkriechen und folglich zur Deformation der Hinterkante 20 führen. Für eine Schaufel mit Deckband, wie sie in Fig. 1 gezeigt ist, ergibt sich als sekundärer Effekt der Hinterkantendeformation eine Verkippung der Deckbandsegmente 21 in axialer, radialer und Umfangsrichtuπg. Die Verkippung der Deckbandsegmente 21 kann dazu führen, dass sich die Spalte zwischen einzelnen Deckbandsegmenten öffnen und den Eintritt von Hochtempe- ratur-Heissgas in den Deckband-Hohlraum ermöglichen. Infolge davon können sich die Temperaturen des Deckband- etalls signifikant erhöhen und schnell ein Kriechen des Deckbandes einleiten und schliesslich zum Hochtemperaturausfall des Deckbandes führen.Due to the one-time passage of the cooling medium through the serpentine cooling channels 13, 14, 15, the cooling medium flows through the cooling channels with increasing temperature and reaches the highest temperature in the last cooling channel 15 of the rear edge 20. The rear edge 20 of the blade 10 can therefore be below certain excessive operating temperatures of the cooling medium and the blade material or metal. The resulting mismatch of the metal temperature over the axial length of the blade can lead to high temperature creep and consequently to the deformation of the trailing edge 20. For a blade with a shroud, as shown in FIG. 1, the secondary effect of the trailing edge deformation is a tilting of the shroud segments 21 in the axial, radial and circumferential direction. The tilting of the shroud segments 21 can lead to the gaps between individual shroud segments opening and the entry of high-temperature hot gas into the shroud cavity. As a result, the temperatures of the shroud metal can rise significantly and quickly cause the shroud to creep and ultimately lead to the high-temperature failure of the shroud.
In der eingangs genannten Druckschrift US-A-4,278,400 ist für Schaufeln mit gekühlter Spitze und fein verteilten Kühlöffnungen an der Vorderkante (Filmkühlung) bereits eine Mehrfachversorgung bei der Kühlung der Schaufel vorgeschlagen worden. Am Ende einer 90°-Umlenkung des Hauptkühlstromes ist quer zur Strömungsrichtung des Hauptkühlstromes ein Ejektor angeordnet, durch den ein zusätzlicher Strom kühleren Kühlmediums in den an der Hinterkante entlanglaufen- den Kühlkanal injiziert wird. Der Ejektor wird über einen radial durch den Fuss laufenden Kanal mit Kühlmedium versorgt. Das aus der Düse des Ejektors mit erhöhter Geschwindigkeit ausströmende Kühlmedium erzeugt einen Unterdruck, der das erwärmte Kühlmedium aus dem Kühlkanal der Vorderkante in den Kühlkanal der Hinterkante zieht. Etwa 45% des an der Vorderkante entlangströmenden Kühlmediums treten durch die Kühlöffnungen an der Vorderkante aus. 40% werden durch den Injektor angesaugt. Der Rest tritt durch Kühlöffnungen an der Schaufelspitze aus.In the publication US-A-4,278,400 mentioned at the outset, for blades with a cooled tip and finely divided cooling openings on the front edge (film cooling) A multiple supply for cooling the blade has already been proposed. At the end of a 90 ° deflection of the main cooling flow, an ejector is arranged transversely to the direction of flow of the main cooling flow, through which an additional flow of cooler cooling medium is injected into the cooling channel running along the rear edge. The ejector is supplied with cooling medium via a channel running radially through the foot. The cooling medium flowing out of the nozzle of the ejector at an increased speed creates a negative pressure which draws the heated cooling medium from the cooling channel of the front edge into the cooling channel of the rear edge. About 45% of the cooling medium flowing along the front edge exits through the cooling openings on the front edge. 40% are sucked in by the injector. The rest exits through cooling openings at the tip of the blade.
Diese bekannte Art der Mehrfachversorgung mit Kühlmedium hat verschiedene Nachteile: Durch den Injektor werden die Druckverhältnisse und Strömungsverhältnisse in den Kühlkanälen gegenüber der Konfiguration mit Einfachversorgung durch den Eingang des Kühlkanals an der Vorderkante massiv verändert. Insbesondere muss ein Gleichgewicht zwischen dem an der Vorderkante zur Filmkühlung ausströmenden Kühlmedium und dem durch den Injektor angesaugten Kühl- medium gefunden und eingestellt werden. Dies bedingt eine völlig neue konstruktive Auslegung der Schaufelkühlung, die nur schwer an sich ändernde Anforderungen angepasst werden kann. Das Injektorprinzip und die damit verbundene Unterdruckerzeugung ist nicht geeignet für Schaufeln ohne Filmkühlung der Vorderkante und Schaufeln mit gekühltem Deckband.This known type of multiple supply with cooling medium has various disadvantages: the injector changes the pressure conditions and flow conditions in the cooling ducts massively compared to the configuration with single supply through the entrance of the cooling duct at the front edge. In particular, a balance must be found between the cooling medium flowing out at the front edge for film cooling and the cooling medium drawn in by the injector. This requires a completely new design of the blade cooling, which is difficult to adapt to changing requirements. The injector principle and the associated negative pressure generation are not suitable for blades without film cooling of the leading edge and blades with a cooled shroud.
DARSTELLUNG DER ERFINDUNGPRESENTATION OF THE INVENTION
Es ist daher Aufgabe der Erfindung, eine gekühlte Schaufel für Gasturbinen mit Mehrfachversorgung des Kühlmediums zu schaffen, welche die Nachteile bekannter Schaufeln vermeidet, auf schaufeln mit gekühltem Deckband und ohne Filmkühlung der Vorderkante anwendbar ist, und sich auch bei vorhandenen Schaufelkonfigurationen leicht und ohne grossen zusätzlichen Aufwand verwirklichen lässt.It is therefore an object of the invention to provide a cooled blade for gas turbines with multiple supply of the cooling medium, which avoids the disadvantages of known blades, can be used on blades with a cooled shroud and without film cooling of the leading edge, and can also be used with existing ones Bucket configurations can be implemented easily and without much additional effort.
Die Aufgabe wird durch die Gesamtheit der Merkmale des Anspruchs 1 gelöst. Der Kern der Erfindung besteht darin, dass der Zusatzstrom über quer durch die Schaufel bzw. den Schaufelschaft verlaufende, mit dem Umlenkbereich direkt oder indirekt in Verbindung stehende Bohrungen zugeführt wird. Der Druck und die Temperatur des durch die Kernöffnung zugeführten Zusatzstroms sind dabei dieselben, wie beim in den Hauptkühleinlass einströmenden Hauptstrom. Durch die Zuführung über die Bohrungen wird eine Mischung der beiden Ströme erreicht, die zu einer deutlich verbesserten Kühlung der Hinterkante der Schaufel führt.The object is achieved by the entirety of the features of claim 1. The essence of the invention is that the additional flow is supplied via bores which run transversely through the blade or the blade shaft and are directly or indirectly connected to the deflection region. The pressure and the temperature of the additional flow supplied through the core opening are the same as for the main flow flowing into the main cooling inlet. By feeding through the holes, a mixture of the two streams is achieved, which leads to a significantly improved cooling of the rear edge of the blade.
Die Bohrungen können direkt in den Umlenkbereich münden. Sie können aber auch in einen radial verlaufenden Kanal unterhalb des Umlenkbereiches münden, der mit dem Umlenkbereich in Verbindung steht.The holes can open directly into the deflection area. However, they can also open into a radially extending channel below the deflection area, which is connected to the deflection area.
Eine erste bevorzugte Ausführungsform der Erfindung ist dadurch gekennzeichnet, dass im Schaufelfuss eine radial orientierte Kernöffnung vorgesehen ist, und dass die Bohrungen durch den Schaufel schaft verlaufen und in die Kernöffnung münden.A first preferred embodiment of the invention is characterized in that a radially oriented core opening is provided in the blade root and that the bores run through the blade shaft and open into the core opening.
Gemäss einer zweiten bevorzugten Ausführungsform der Erfindung sind wenigstens zwei einander gegenüberliegende Bohrungen vorgesehen welche in Strömungsrichtung schräg nach oben verlaufen und mit der Vertikalen jeweils einen Winkel zwischen 30° und 90° einschliessen. Insbesondere sind die Bohrungen in radialer und axialer Richtung gestaffelt angeordnet, wobei die Bohrungen einen vorgegebenen Innendurchmesser aufweisen, der radiale Abstand der Bohrungen, normiert auf den Innendurchmesser, im Bereich zwischen 1 und 4 liegt, der axiale Abstand, normiert auf den Innendurchmesser, im Bereich zwischen 0 und 3 liegt, und der radiale Abstand der oberen Bohrung von dem zweiten Umlenkbereich, normiert auf den Innendurchmesser, im Bereich zwischen 1 und 4 liegt. Für die Realisierung der Mehrfachzuführung bei bereits vorliegenden Schaufelkonfigurationen ist es besonders günstig, wenn gemäss einer zweiten bevorzugten Ausführungsform zweite Mittel vorgesehen sind, welche sicherstellen, dass der Hauptstrom des Kühlmediums durch den ersten Kühlkanal trotz dem Zusetzen des Zusatzstromes im wesentlichen unverändert bleibt. Insbesondere wird dies dadurch erreicht, dass die zweiten Mittel zusätzliche Auslassöffnungen umfassen, welche zwischen dem Hauptkühleinlass und dem zweiten Umlenkbereich angeordnet sind, und durch welche ein Teilstrom des Hauptstroms des Kühlmediums austritt. Besonders günstig ist es dabei, wenn gemäss einer Weiterbildung die Schaufel am oberen Ende einen Deckbandabschnitt aufweist, und die zusätzlichen Auslassöffnungen im Deckbandabschnitt angeordnete Bohrungen sind. Hierdurch wird gleichzeitig eine deutlich verbesserte Kühlung des Deckbandes ermöglicht.According to a second preferred embodiment of the invention, at least two bores lying opposite one another are provided which run obliquely upward in the direction of flow and each form an angle between 30 ° and 90 ° with the vertical. In particular, the bores are staggered in the radial and axial directions, the bores having a predetermined inner diameter, the radial distance of the bores, standardized to the inner diameter, in the range between 1 and 4, the axial distance, standardized to the inner diameter, in the range is between 0 and 3, and the radial distance of the upper bore from the second deflection area, normalized to the inside diameter, is in the range between 1 and 4. For the implementation of the multiple feed in already existing blade configurations, it is particularly favorable if, according to a second preferred embodiment, second means are provided which ensure that the main flow of the cooling medium through the first cooling channel remains essentially unchanged despite the addition of the additional flow. In particular, this is achieved in that the second means comprise additional outlet openings which are arranged between the main cooling inlet and the second deflection area and through which a partial flow of the main flow of the cooling medium emerges. It is particularly advantageous if, according to a further development, the blade has a shroud section at the upper end and the additional outlet openings are bores arranged in the shroud section. This also enables significantly improved cooling of the shroud.
Weitere Ausführungsformen ergeben sich aus den abhängigen Ansprüchen.Further embodiments result from the dependent claims.
KURZE ERLÄUTERUNG DER FIGURENBRIEF EXPLANATION OF THE FIGURES
Die Erfindung soll nachfolgend anhand von Ausführungsbeispielen im Zusammenhang mit der Zeichnung näher erläutert werden. Es zeigenThe invention will be explained in more detail below on the basis of exemplary embodiments in connection with the drawing. Show it
Fig. 1 im Längsschnitt die Konfiguration einer gekühlten Gasturbinenschaufel mit Mehrfachversorgung des Kühlmediums und gekühl- tem Deckband gemäss einem bevorzugten Ausführungsbeispiel der Erfindung;1 shows in longitudinal section the configuration of a cooled gas turbine blade with multiple supply of the cooling medium and cooled cover band according to a preferred embodiment of the invention;
Fig. 2 den Fussbereich der Schaufel aus Fig. 1 in einer vergrösserten Darstellung mit zwei Bohrungen zur Zuführung des Kühlmedium- Zusatzstroms; Fig. 3, 4 jeweils einen Schnitt durch den Fuss der Schaufel aus Fig. 2 in einer zu der Schnittebene der Fig. 2 senkrechten Ebene durch eine der beiden Bohrungen zur Zuführung des Kühlmedium-Zu- satzstroms;FIG. 2 shows the foot region of the blade from FIG. 1 in an enlarged view with two bores for supplying the additional cooling medium flow; 3, 4 each show a section through the base of the blade from FIG. 2 in a plane perpendicular to the section plane of FIG. 2 through one of the two bores for supplying the additional coolant flow;
Fig. 5 in der Draufsicht von oben den Deckbandabschnitt der Schaufel aus Fig. 1 , 2; und5 shows a top view of the shroud section of the blade from FIGS. 1, 2; and
Fig. 6-8 verschiedene Schnitte durch den Deckbandbereich der Schaufel aus Fig. 1 , 2 entlang der in Fig. 5 eingezeichneten parallelen Schnittebenen A-A, B-B und C-C.Fig. 6-8 different sections through the shroud area of the blade from Fig. 1, 2 along the parallel sectional planes A-A, B-B and C-C shown in Fig. 5.
WEGE ZUR AUSFÜHRUNG DER ERFINDUNGWAYS OF CARRYING OUT THE INVENTION
Ein bevorzugtes Ausführungsbeispiel einer gekühlten Gasturbinenschaufel mit Mehrfachzuführung des Kühlmediums gemäss der Erfindung ist in den Fig. 1 bis 4 wiedergegeben. Der Hauptstrom des Kühlmediums tritt im Bereich des Schaufelschaftes 25 durch einen Hauptkühleinlass 16 von unten in den Kühlkanal 13 ein und tritt teilweise durch Öffnungen im Deckbandabschnitt 21 (Bohrungen 27, ..,29 in Fig. 5 bis 8) und teilweise entlang der Hinterkante 20 wieder aus (siehe die in Fig. 1 eingezeichneten Pfeile am Deckbandabschnitt 21 und an der Hinterkante 20).A preferred embodiment of a cooled gas turbine blade with multiple supply of the cooling medium according to the invention is shown in FIGS. 1 to 4. The main flow of the cooling medium in the area of the blade shaft 25 enters the cooling channel 13 from below through a main cooling inlet 16 and partly passes through openings in the shroud section 21 (bores 27,..., 29 in FIGS. 5 to 8) and partly along the rear edge 20 again (see the arrows drawn in FIG. 1 on the shroud section 21 and on the rear edge 20).
Zusätzliches Kühlmedium wird durch den Schaufelschaft 25 und eine im Schau- felfuss vorhanden Kemöffnuπg 24 mittels zweier Bohrungen 22, 23 zugeführt. Die Bohrungen 22, 23 sind - wie aus den Fig. 2 bis 4 gut erkennbar ist - in radialer und in axialer Richtung gestaffelt und liegen einander gegenüber (Fig. 3, 4). Die Bohrungen 22, 23 sind mit einem Winkel zwischen 30° und 90° gegen die Verti- kale geneigt, wobei sie in Strömungsrichtung (von aussen nach innen) schräg nach oben verlaufen. Die Bohrungen 22, 23 enden in der Kernöffnung 24 im Schaufelfuss 12. Sie sind damit in dem Bereich der Schaufel 10 eingearbeitet, der zum Abstützen und zum Entfernen des Gusskernes dient und damit ohnehin vorhanden ist. Ist keine Kernöffnung vorhanden, d.h., hat der Umlenkbereich 18 keine Verbindung nach aussen, können die Bohrungen 22, 23 aber auch weiter oben verlaufen und direkt in den Umlenkbereich18 münden. Weiterhin ist es denkbar, anstelle der Kernöffnung einen radial angeordneten Quarzstab vorzusehen, der eine Verbindung der Bohrungen mit dem Umlenkbereich sicherstellt.Additional cooling medium is supplied through the blade shaft 25 and a core opening 24 present in the blade root by means of two bores 22, 23. The bores 22, 23 are - as can be clearly seen from FIGS. 2 to 4 - staggered in the radial and in the axial direction and lie opposite one another (FIGS. 3, 4). The bores 22, 23 are inclined at an angle between 30 ° and 90 ° to the vertical, whereby they run obliquely upwards in the direction of flow (from the outside inwards). The bores 22, 23 end in the core opening 24 in the blade root 12. They are thus incorporated in the area of the blade 10 that serves to support and remove the cast core and is therefore available anyway. If there is no core opening, ie if the deflection area 18 has no connection to the outside, the bores 22, 23 can also extend further up and open directly into the deflection area 18. Furthermore, it is conceivable to provide a radially arranged quartz rod instead of the core opening, which ensures a connection of the bores to the deflection area.
Der Zweck der Mehrfachzuführung von Kühlmedium besteht darin, kühleres Kühlmedium direkt in den Hinterkantenbereich der Schaufel 10 einzuführen. Diese Einführung geschieht so, dass der durch den Hauptkühleinlass 16 zugeführte Hauptstrom des Kühlmediums möglichst wenig behindert bzw. blockiert wird. Der axiale Abstand x zwischen den Bohrungen 22 und 23 liegt, normiert auf den Durchmesser d der Bohrungen 22, 23, vorzugsweise in einem Bereich von x/d zwischen 0 und 3 (siehe Fig. 2). Der radiale Abstand y zwischen den Bohrungen 22 und 23 liegt, normiert auf den Durchmesser d, vorzugsweise in einem Bereich von y/d zwischen 1 und 4 (siehe Fig. 2). Der auf d normierte Abstand der oberen Bohrung 22 vom zweiten inneren Umlenkbereich 18 liegt vorzugsweise in einem Bereich von l/d zwischen 1 und 4 (Fig. 2).The purpose of the multiple supply of cooling medium is to introduce cooler cooling medium directly into the rear edge area of the blade 10. This introduction takes place in such a way that the main flow of the cooling medium supplied through the main cooling inlet 16 is prevented or blocked as little as possible. The axial distance x between the bores 22 and 23 is, normalized to the diameter d of the bores 22, 23, preferably in a range of x / d between 0 and 3 (see FIG. 2). The radial distance y between the bores 22 and 23 is, normalized to the diameter d, preferably in a range of y / d between 1 and 4 (see FIG. 2). The distance of the upper bore 22 normalized to d from the second inner deflection area 18 is preferably in a range of 1 / d between 1 and 4 (FIG. 2).
Zusätzlich zu dieser Zuführung von kälterem Kühlmedium sind im Deckbandabschnitt 21 der Schaufel 10 weitere Bohrungen 27, 28, 29 vorgesehen (Fig. 5 bis 8). Der Zweck dieser zusätzlichen Bohrungen 27, 28, 29 besteht darin, sicherzustellen, dass der Massenstrom des Kühlmediums im vorderen Kühlkanal 13 trotz der Zuführung des zusätzlichen Kühlmediums durch die Bohrungen 23, 24 weitgehend unverändert bleibt. Gleichzeitig dient das durch die Bohrungen 27, 28, 29 austretende Kühlmedium dazu, den Deckbandabschnitt aktiv zu kühlen. Die Kühlbohrungen 27, 28, 29 im Deckbandabschnitt 21 haben vorzugsweise einen Innendurchmesser im Bereich zwischen 0,6 mm und 4 mm. Alle drei Bohrungen 27, 28, 29 sind am Deckbandabschnitt 21 so positioniert und dimensioniert, dass eine un- gleichmassige Strahldurchdringung in den Hauptstrom des Deckbandhohlraums stattfindet. An beiden Zuführungsstellen des Kühlmediums am Hauptkühleinlass 16 und an den Bohrungen 22, 23 hat das Kühlmedium denselben Druck und dieselbe Temperatur. Es findet daher eine Mischung des Kühlmedium-Hauptstroms mit dem Zusatzstrom innerhalb des Umlenkbereiches 18 statt, der den Druck und die Strömungsgeschwindigkeit weitgehend unverändert lässt. Im Umlenkbereich 18 erfolgt eine Umlenkung des Hauptstromes um etwa 135°. Der Zusatzstrom wird dann mit Vorteil an einem Punkt des Umlenkbereiches 18 zugeführt, wo bereits eine Umlenkung um etwa 90° erfolgt ist. Werden - ausgehend von einer Schaufelkonfiguration ohne Mehrfachzuführung des Kühlmediums - im Bereich des Schaufelfusses 12 und im Deckbandabschnitt 21 gemäss Fig. 1 Bohrungen 22, 23 bzw. 27,..,29 für die Zufuhr und Abfuhr von Kühlmedium vorgesehen, wird die Kühlung im Bereich der Hinterkante 20 deutlich verbessert, ohne dass der Hauptkühlstrom und damit die Kühlung der übrigen Schaufel verändert wird. Zusätzlich gewonnen wird eine aktive Kühlung des Deckbandabschnitts 21.In addition to this supply of colder cooling medium, further bores 27, 28, 29 are provided in the shroud section 21 of the blade (FIGS. 5 to 8). The purpose of these additional bores 27, 28, 29 is to ensure that the mass flow of the cooling medium in the front cooling channel 13 remains largely unchanged despite the supply of the additional cooling medium through the bores 23, 24. At the same time, the cooling medium emerging through the bores 27, 28, 29 serves to actively cool the shroud section. The cooling bores 27, 28, 29 in the shroud section 21 preferably have an inner diameter in the range between 0.6 mm and 4 mm. All three bores 27, 28, 29 are positioned and dimensioned on the shroud section 21 in such a way that an uneven beam penetration into the main stream of the shroud cavity takes place. At both supply points of the cooling medium at the main cooling inlet 16 and at the bores 22, 23, the cooling medium has the same pressure and the same temperature. There is therefore a mixture of the cooling medium main flow with the additional flow within the deflection region 18, which leaves the pressure and the flow rate largely unchanged. In the deflection area 18, the main flow is deflected by approximately 135 °. The additional flow is then advantageously supplied at a point of the deflection area 18 where a deflection of approximately 90 ° has already taken place. If - starting from a blade configuration without multiple supply of the cooling medium - bores 22, 23 and 27,..., 29 are provided in the region of the blade root 12 and in the shroud section 21 according to FIG. 1, the cooling in the region is provided the trailing edge 20 is significantly improved without the main cooling flow and thus the cooling of the remaining blade being changed. Active cooling of the shroud section 21 is also obtained.
Hat die Schaufel kein Deckband, durch welches ein Teil des Kühlmediumstromes austritt, ist es notwendig, den Querschnitt des zweiten Kühlkanals 15 so zu erweitern, dass er dem im zweiten Umlenkbereich 18 zugemischte Zusatzstrom Rechnung trägt.If the blade does not have a shroud through which a part of the cooling medium flow exits, it is necessary to expand the cross section of the second cooling channel 15 so that it takes into account the additional flow mixed in the second deflection area 18.
BEZUGSZEICHENLISTELIST OF REFERENCE NUMBERS
10 Schaufel10 shovel
11 Schaufelblatt11 airfoil
12 Schaufelfuss12 blade root
13,14,15 Kühlkanal13, 14, 15 cooling channel
16 Hauptkühleinlass16 main cooling inlet
17,18 Umlenkbereich17.18 deflection area
19 Vorderkante19 leading edge
20 Hinterkante20 trailing edge
21 Deckbandabschnitt21 shroud section
22,23 Bohrung 24 Kernöffnung22.23 bore 24 core opening
25 Schaufelschaft 27,..,29 Bohrung d Innendurchmesser der Bohrungen 22, 2325 shovel shaft 27, .., 29 bore d inner diameter of the bores 22, 23
I Abstand der oberen Bohrung 22 vom zweiten Umlenkbereich y Abstand der Bohrungen 22, 23 in radialer Richtung x Abstand der Bohrungen 22, 23 in axialer Richtung I distance of the upper bore 22 from the second deflection area y distance of the bores 22, 23 in the radial direction x distance of the bores 22, 23 in the axial direction

Claims

PATENTANSPRÜCHE
1. Gekühlte Schaufel (10) für eine Gasturbine, mit einer Einbau- Radialrichtung und einer Einbau-Axialrichtung, welche Schaufel (10) ein von einem Schaufelfuss (12) und einem Schaufelschaft (25) ausgehendes und sich in Radialrichtung erstreckendes Schaufelblatt (11) aufweist, und wobei das Schaufelblatt eine Vorderkante (19) und eine Hinterkante (20) sowie innerhalb des Schaufelblatts (11 ) eine Mehrzahl von sich in radialer Richtung erstreckenden, strömungsmässig hintereinandergeschalteten Kühlkanälen (13, 14, 15) aufweist, von denen ein erster Kühlkanal (13) entlang der Vorderkante (19) angeordnet ist und ein zweiter Kühlkanal (15) entlang der Hinterkante (20) angeordnet ist, welcher erste und zweite Kühlkanal eine sich vom Schaufelfuss (12) ausgehend in Einbau-Radialrichtung erstreckende Durchströmungsrichtung für einen Hauptstrom eines Kühlmediums aufweisen, und wobei ein stromabwartiges Ende des ersten Kühlkanals (13) über einen über einen ersten Umlenkbereich (17), einen zwischen dem ersten und zweiten Kühlkanal (13, 15) angeordneten dritten Kühlkanal (14), und einen zweiten Umlenkbereich (18) mit einem zuströmseitigen Ende des zweiten Kühlkanals (15) in Fluidverbindung steht, und wobei erste Mittel (22, 23) vorgesehen sind, durch welche dem vom dritten Kühlkanal (14) in den zweiten Kühlkanal (15) strömenden, aufgewärmten Hauptstrom des Kühlmediums von aussen ein Zusatzstrom Kühlmediums zugesetzt wird, dadurch gekennzeichnet, dass die ersten Mittel Bohrungen (22, 23) umfassen, welche mit dem zweiten Umlenkbereich (18) in Verbindung stehen.1. Cooled blade (10) for a gas turbine, with a built-in radial direction and a built-in axial direction, which blade (10) is a blade blade (11) starting from a blade root (12) and a blade shaft (25) and extending in the radial direction. and wherein the airfoil has a front edge (19) and a rear edge (20) and, within the airfoil (11), a plurality of cooling channels (13, 14, 15) which extend in the radial direction and are connected in series in terms of flow, of which a first cooling channel (13) is arranged along the front edge (19) and a second cooling duct (15) is arranged along the trailing edge (20), which first and second cooling duct have a flow direction for a main flow of a flow extending from the blade root (12) in the installation radial direction Have cooling medium, and a downstream end of the first cooling channel (13) over a first deflection area (17), a third cooling channel (14) arranged between the first and second cooling channels (13, 15), and a second deflection area (18) in fluid communication with an upstream end of the second cooling channel (15), and first means (22, 23) being provided through which an additional flow of cooling medium is added to the warmed main flow of the cooling medium flowing from the third cooling duct (14) into the second cooling duct (15), characterized in that the first means comprise bores (22, 23) which are connected to the are connected to the second deflection area (18).
2. Schaufel nach Anspruch 1, dadurch gekennzeichnet, dass im Schaufelfuss (12) eine in Einbau-Radialichtung orientierte Kemöffnung (24) angeordnet ist, und, dass die Bohrungen (22, 23) durch den Schaufelschaft (25) verlaufen und in die Kernöffnung (24) münden.2. Blade according to claim 1, characterized in that a core opening (24) oriented in the installation radial direction is arranged in the blade root (12), and that the bores (22, 23) run through the blade shaft (25) and into the core opening (24) flow out.
3. Schaufel nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass wenigstens zwei einander gegenüberliegende Bohrungen (22, 23) vorgesehen sind, deren Mündung im Schaufelinneren zum Schaufelkopf weist und welche mit der Einbau-Radialrichtung jeweils einen Winkel zwischen 30° und 90° einschliessen. 3. Blade according to claim 1 or 2, characterized in that at least two mutually opposite bores (22, 23) are provided are, the mouth of which points in the interior of the blade to the blade head and which each enclose an angle between 30 ° and 90 ° with the radial installation direction.
4. Schaufel nach Anspruch 3, dadurch gekennzeichnet, dass die Bohrungen (22, 23) in Einbau-Radialrichtung und in Einbau-Axialrichtung gegenseitig versetzt angeordnet sind.4. Blade according to claim 3, characterized in that the bores (22, 23) are mutually offset in the installation radial direction and in the installation axial direction.
5. Schaufel nach Anspruch 4, dadurch gekennzeichnet, dass die Bohrun- gen (22, 23) einen vorgegebenen Innendurchmesser (d) aufweisen, dass der5. Blade according to claim 4, characterized in that the bores (22, 23) have a predetermined inner diameter (d) that the
Abstand (y) der Bohrungen (22, 23) in Einbau-Radialrichtung, bezogen auf den Innendurchmesser (d), im Bereich zwischen 1 und 4 liegt, und dass der Abstand (x) in Einbau-Axialrichtung, bezogen auf den Innendurchmesser (d), im Bereich zwischen 0 und 3 liegt.Distance (y) of the bores (22, 23) in the installation radial direction, based on the inner diameter (d), is in the range between 1 and 4, and that the distance (x) in the installation axial direction, based on the inner diameter (d ), is in the range between 0 and 3.
6. Schaufel nach Anspruch 5, dadurch gekennzeichnet, dass der radiale Abstand (I) der oberen Bohrung (22) von dem zweiten Umlenkbereich (18), bezogen auf den Innendurchmesser (d), im Bereich zwischen 1 und 4 liegt. 6. Blade according to claim 5, characterized in that the radial distance (I) of the upper bore (22) from the second deflection area (18), based on the inner diameter (d), is in the range between 1 and 4.
7. Schaufel nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass zweite Mittel (27,..,29) vorgesehen sind, welche sicherstellen, dass der Hauptstrom des Kühlmediums durch den ersten Kühlkanal (13) trotz dem Zusetzen des Zusatzstromes im wesentlichen unverändert bleibt. 7. Bucket according to one of claims 1 to 6, characterized in that second means (27, .., 29) are provided which ensure that the main flow of the cooling medium through the first cooling channel (13) despite the addition of the additional flow essentially remains unchanged.
8. Schaufel nach Anspruch 7, dadurch gekennzeichnet, dass die zweiten8. Bucket according to claim 7, characterized in that the second
Mittel zusätzliche Auslassöffnungen (27,..,29) umfassen, welche zwischen dem Hauptkühleinlass (16) und dem zweiten Umlenkbereich (18) angeordnet sind, und durch welche ein Teilstrom des Hauptstroms des Kühlmediums austritt. Means comprise additional outlet openings (27,..., 29), which are arranged between the main cooling inlet (16) and the second deflection area (18) and through which a partial flow of the main flow of the cooling medium emerges.
9. Schaufel nach Anspruch 8, dadurch gekennzeichnet, dass die Schaufel9. A blade according to claim 8, characterized in that the blade
(10) am oberen Ende einen Deckbandabschnitt (21 ) aufweist, und dass die zu- sätzlichen Auslassöffnungen im Deckbandabschnitt (21 ) angeordnete Bohrungen (27,..,29) sind.(10) has a shroud section (21) at the upper end, and that the Additional outlet openings in the shroud section (21) are bores (27, .., 29).
10. Schaufel nach Anspruch 9, dadurch gekennzeichnet, dass im Deckbandabschnitt wenigstens drei Bohrungen (27, ..,29) vorgesehen sind, welche einen Innendurchmesser im Bereich zwischen 0,6 mm und 4 mm aufweisen.10. Blade according to claim 9, characterized in that in the shroud section at least three bores (27, .., 29) are provided which have an inner diameter in the range between 0.6 mm and 4 mm.
11. Schaufel nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass der zweite Kühlkanal (15) eine Querschnittserweiterung entsprechend dem zugemischten Zusatzstrom aufweist. 11. Blade according to one of claims 1 to 6, characterized in that the second cooling channel (15) has a cross-sectional expansion corresponding to the admixed additional flow.
EP04766104.6A 2003-07-12 2004-06-30 Cooled blade for a gas turbine Expired - Lifetime EP1644614B1 (en)

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DE10331635.3A DE10331635B4 (en) 2003-07-12 2003-07-12 Cooled shovel for a gas turbine
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KR20110134505A (en) 2011-12-14
CN1849439A (en) 2006-10-18
EP1644614B1 (en) 2013-08-28
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CA2531754C (en) 2012-10-09
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DE10331635A1 (en) 2005-02-03
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US20060177310A1 (en) 2006-08-10
AR046072A1 (en) 2005-11-23

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