EP1907670B1 - Cooled turbine blade for a gas turbine and use of such a turbine blade - Google Patents

Cooled turbine blade for a gas turbine and use of such a turbine blade Download PDF

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Publication number
EP1907670B1
EP1907670B1 EP06764215A EP06764215A EP1907670B1 EP 1907670 B1 EP1907670 B1 EP 1907670B1 EP 06764215 A EP06764215 A EP 06764215A EP 06764215 A EP06764215 A EP 06764215A EP 1907670 B1 EP1907670 B1 EP 1907670B1
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EP
European Patent Office
Prior art keywords
blade
cavity
platform
airfoil
turbine
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EP06764215A
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German (de)
French (fr)
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EP1907670A1 (en
Inventor
Fathi Ahmad
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Siemens AG
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Siemens AG
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Priority to EP06764215A priority Critical patent/EP1907670B1/en
Priority to PL06764215T priority patent/PL1907670T3/en
Publication of EP1907670A1 publication Critical patent/EP1907670A1/en
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Publication of EP1907670B1 publication Critical patent/EP1907670B1/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
    • 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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/127—Vortex generators, turbulators, or the like, for mixing
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
    • 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
    • F05D2260/231—Preventing heat transfer

Definitions

  • the invention relates to a turbine blade for a gas turbine, with a blade root, followed sequentially by a platform region with a transversely extending platform and adjoining a longitudinally curved blade profile, with at least one foot end open and traversed by a coolant cavity extending through extends the blade root and the platform area into the blade profile. Moreover, the invention relates to the use of such a turbine blade.
  • a cooled blade of a gas turbine which has meandering cooling channels inside.
  • delimiting inner walls turbulators are provided in the region of the blade profile, which fan the heat transfer of blade material in the cavity flowing through the coolant. Due to the increased heat transfer, the turbine blade can thus withstand higher operating temperatures.
  • cracks can occur in the area of the hollow-throat-like transition from platform to blade profile, which is also referred to as fillet in English, and / or in the platform. If the resulting cracks exceed a critical crack length, safe operation of the gas turbine equipped with such a turbine blade is not ensured.
  • Another prior art turbine engine is known from the EP 1 267 040 known. Accordingly, a particularly long service life of the turbine blade is a design target with which the disposal period of a gas turbine equipped with it can be further increased.
  • the object of the invention is to provide a turbine blade for a gas turbine where the fatigue life is prolonged. In addition, it is an object of the invention to provide the use of such a turbine blade.
  • the invention is based on the finding that the wear and the crack formation and the subsequent crack growth are thermally induced.
  • the material of the turbine blade is exposed to thermal stresses caused by the external application of hot gas and the internal cooling. It has been found that during operation of the gas turbine in the trough-like transition region between the blade profile and the platform, locally comparatively low hot gas side temperatures occur compared to those in the area of the blade profile. Therefore, the internally cooled turbine blade with turbulators arranged on the inner walls in the area of the platform has hitherto been over-cooled in localized areas. As a result, locally comparatively large temperature differences in the blade material and correspondingly large thermal stresses occurred, which could cause the wear. This effect does not occur in the forefront in particular
  • the invention proposes to substantially reduce these local thermal stresses in the transition region merely by not cooling them as much as the blade profile. To achieve this, it is provided in a generic turbine blade that a section of the surface of the inner wall lying at least in the blade profile and adjacent to the platform region is free of structural elements.
  • the temperature gradient in the blade material is lowered due to the warmer transition region, which prolongs the life of the turbine blade.
  • the proposed measure extends the life, in particular the low cycle fatigue (LCF) for the platform and its transition into the blade profile, ie. H. in the fillet, extended.
  • LCF low cycle fatigue
  • the embodiment in which the surface of the inner wall at the level of the platform portion and the surface of the inner wall of the adjoining portion in the interior of the blade profile are flat. Due to the flow of coolant not swirled in this section, the heat transfer from the blade material into the coolant is reduced compared to the heat transfer in the airfoil profile, so that the temperature difference between a hot gas-charged outer surface of the turbine blade, the hot side, and the coolant-charged inner wall of the turbine blade, the cold side, can be significantly reduced by a permissible increase in the material temperature. The reduction leads to reduced thermal stresses, especially in the area of the transition between the blade profile and the platform, ie in the fillet.
  • the structural elements on the inner wall of the blade profile are generally flat, but - viewed in the radial direction - spaced to form a mean minimum distance from each other, provides an advantageous further development that between the platform surface and - also in the radial direction - the next adjacent structural element determined distance is greater than the average, minimum distance between two adjacent structural elements.
  • the distance is preferably at least 1.1 times the mean minimum distance.
  • the section has a height of 5% of the profile height of the blade profile to the profile peak, calculated from the platform surface.
  • the structural elements are designed as turbulators in the form of ribs, base fields, dimples and / or nipples.
  • the wear-causing local temperature difference between the hot side and the cold side occurs particularly in a middle region of the transitional region between a leading edge of the airfoil and a trailing edge of the airfoil, it is particularly advantageous if the surface of the intermediate region between the leading edge and the trailing edge lying inner wall is free of structural elements.
  • the turbine blade several, extending through the turbine blade radially extending and separated by support ribs cavities, in which only lying between the leading edge and the trailing edge of the blade profile, in the central region cavity has the portion of the inner wall whose surface of the inner wall in the blade profile is free of structural elements.
  • the arranged in the central region between the leading edge and trailing edge on the pressure side platform is structurally particularly wide, so far the local temperature minimum occurred in the blade material at this point.
  • the temperature minimum can be increased while reducing the thermal stress, in particular if the surface of the inner wall, which inner wall is formed by the suction-side profile wall of the blade profile, is free of structural elements. As a result, a particularly long service life extension of the expediently cast turbine blade can be brought about.
  • FIG. 1 shows a gas turbine 1 in a longitudinal partial section. It has inside a rotatably mounted about a rotation axis 2 rotor 3, which is also referred to as a turbine runner. Along the rotor 3 successive an intake 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of rotationally symmetrical to each other arranged burners 7, a turbine unit 8 and an exhaust housing 9.
  • the annular combustion chamber 6 forms a combustion chamber 17 which communicates with an annular hot gas channel 18.
  • There four successive turbine stages 10 form the turbine unit 8. Each turbine stage 10 is formed of two blade rings.
  • a hot gas 11 produced in the annular combustion chamber 6 follows in the hot gas channel 18 in each case one row of guide blades 13 formed by a rotor blades 15 row 14
  • the vanes 12 are attached to the stator, whereas the blades 15 a row 14 by means of a turbine disk 19 on the rotor are attached.
  • a generator or a working machine (not shown) coupled.
  • a hollow turbine blade 50 according to the invention shows FIG. 2 in perspective view.
  • the preferably cast turbine blade 50 comprises a blade root 52 on which a platform 54 is arranged along a blade axis and a blade profile 56, which is not shown in its entirety but shortened.
  • the blade profile 56 has a pressure-side profile wall 62 and a suction-side profile wall 64, which extend from a front edge 66 of the blade profile 56 to a trailing edge 68.
  • the hot gas 11 flows along the profile walls 62, 64, from the front edge 66 in the direction of the trailing edge 68.
  • a hollow throat-like transition region 48 is formed.
  • the first partial cavity 58a runs parallel to and in the region of the front edge.
  • a second partial cavity 58b follows - seen in the flow direction of the hot gas, behind it.
  • the partial cavities 58 extend in the radial direction, relative to the installation position of the turbine blade 50 in the gas turbine 1, and are separated from one another by support ribs 70.
  • the support ribs 70 connect the pressure-side profile wall 62 with the suction-side profile wall 64.
  • partial cavities 58 in FIG. 2 shown turbine blade 50 no structural elements shown.
  • FIG. 3 shows the inventive designed as a blade or vane turbine blade 50 according to the cross section III-III of FIG. 2 ,
  • the blade root 52 follows in the radial direction, based on the installation position in the gas turbine 1, the platform 54 and the blade profile 56. Both the outside of the blade profile 56 and the blade profile 56 facing surface 61 of the platform 54 are the gas turbine 1 flowing through the hot gas 11th exposed and are referred to as a hot side.
  • the sectional plane of the cross section III-III extends through the second of the three side open partial cavities 58.
  • the foot side supplied coolant K such as cooling air, cools the turbine blade 50, so that they can withstand the temperatures occurring during operation of the gas turbine.
  • the second partial cavity 58b is surrounded by an inner wall 59 which is partially formed by the pressure-side profile wall 62 and the suction-side profile wall 64.
  • On the inner surfaces of the profile walls 62, 64 and the inner walls 59 are provided to increase the heat transfer of heated by the hot gas 11 blade material in the interior flowing coolant K structural elements 72 in the form of turbulators, as ribs, base fields, dimples and / or Nipples can be formed. In the embodiment shown, it is transverse to the coolant flow direction ribs.
  • the turbulators or the structural elements 72 approximately over an entire profile height H from the platform 54 to the blade tip 74 (FIG. FIG. 4 ) on the surfaces of the inner walls 59, as shown on the pressure-side profile wall 62 in a first section.
  • a new path is now taken.
  • the structural elements 72 no longer begin in the region of the platform surface 61, but only from a predetermined height in the blade profile 56.
  • a second section A lying in the blade profile 56 and adjacent to the platform region is the surface
  • the second section A adjoining the platform region is already located in the blade profile 56
  • the surface of the inner wall 59 located in this region is accordingly flat and not profiled by structural elements.
  • Adjacent to the second gate A in the direction of the profile tip 74 is a region C of the surface of the inner wall 59, in which turbulators or structural elements 72 have an average, minimum distance m from each other, which is determined in the radial direction.
  • the radially measured distance D between the lowest structural element 73 adjacent to the platform surface 61 and the platform surface 61 is greater than the average, minimum distance m,
  • the inflowing coolant K flows first laminar in the second section A due to the locally flat surface and meanwhile cools the blade material convectively. Subsequently, the coolant K flowing in region C is swirled due to the structural elements 72, 73, which leads to an improved heat transfer. This ensures that the transition area 48 is local Less cooled than the rest of the blade profile 56 and so the thermal stresses are reduced at this point, which only rarely cause cracks. Crack growth is delayed as compared to a prior art turbine blade. As a result, the life of the turbine blade 50 is prolonged by the proposed measures.
  • FIG. 4 shows a further turbine blade according to the invention 50 in longitudinal section with a blade root 52, a platform 54 and a blade profile 56.
  • the profiled blade root 52 may be formed in the shape of a fir tree or dovetail in cross section.
  • the turbine blade 50 is also hollow and has four radially extending part cavities 58, which are separated from each other by support ribs 70 which connect the pressure side profile wall 62 with the suction side profile wall 64.
  • the surface of the inner wall 59 located in this region is flat and not profiled by structural elements.
  • the second section A for example, has a height of 5% of the profile height H, calculated from the platform surface 61.
  • the lower temperature differences reduce the thermal stresses in the blade material in the transition region, thereby reducing crack initiation and retarding crack growth, significantly increasing the fatigue life of the turbine blade 50.
  • a gas turbine equipped with such a turbine blade 50 can be operated longer; the turbine blades 50 used must less frequently be checked for defects such as cracks. This significantly increases the availability of the gas turbine 1.

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

Abstract

An aspect of the invention is a turbine blade for a gas turbine, comprising a blade root, adjoining which one after the other are a platform region having a transversely running platform and then a blade profile curved in the longitudinal direction, comprising at least one cavity which is open on the root side and through which a coolant can flow and which extends through the blade root and the platform region into the blade profile. The cavity is surrounded by an inner wall, on the surface of which structural elements influencing the coolant are provided. In order to prolong the service life of such a turbine blade, the invention proposes that a section, lying at least in the blade profile and adjoining the platform region, of the surface of the inner wall be free of structural elements. Such a turbine blade can preferably be used in a stationary gas turbine.

Description

Die Erfindung betrifft eine Turbinenschaufel für eine Gasturbine, mit einem Schaufelfuß, an den sich aufeinander folgend ein Plattformbereich mit einer quer verlaufenden Plattform und daran ein sich in Längsrichtung gekrümmtes Schaufelprofil anschließen, mit mindestens einem fußseitig offenen und von einem Kühlmittel durchströmbaren Hohlraum, der sich durch den Schaufelfuß und den Plattformbereich in das Schaufelprofil hinein erstreckt. Außerdem betrifft die Erfindung die Verwendung einer derartigen Turbinenschaufel.The invention relates to a turbine blade for a gas turbine, with a blade root, followed sequentially by a platform region with a transversely extending platform and adjoining a longitudinally curved blade profile, with at least one foot end open and traversed by a coolant cavity extending through extends the blade root and the platform area into the blade profile. Moreover, the invention relates to the use of such a turbine blade.

Aus der EP 1 469 163 A2 ist eine gekühlte Laufschaufel einer Gasturbine bekannt, die im Inneren mäanderförmig verlaufende Kühlkanäle aufweist. An den die Hohlräume begrenzenden Innenwänden sind im Bereich des Schaufelprofils Turbulatoren vorgesehen, die den Wärmeübergang von Schaufelmaterial in das den Hohlraum durchströmende Kühlmittel anfachen. Durch den erhöhten Wärmeübergang kann damit die Turbinenschaufel höheren Betriebstemperaturen standhalten.From the EP 1 469 163 A2 a cooled blade of a gas turbine is known which has meandering cooling channels inside. At the cavities delimiting inner walls turbulators are provided in the region of the blade profile, which fan the heat transfer of blade material in the cavity flowing through the coolant. Due to the increased heat transfer, the turbine blade can thus withstand higher operating temperatures.

Nachteilig ist hierbei, dass im Bereich des hohlkehlartigen Übergangs von Plattform zum Schaufelp.rofil, der auch im Englischen als Fillet bezeichnet wird, und/oder in der Plattform Risse auftreten können. Überschreiten die entstandenen Risse eine kritische Risslänge, so ist ein sicherer Betrieb der mit einer solchen Turbinenschaufel ausgestatteten Gasturbine nicht gewährleistet.The disadvantage here is that cracks can occur in the area of the hollow-throat-like transition from platform to blade profile, which is also referred to as fillet in English, and / or in the platform. If the resulting cracks exceed a critical crack length, safe operation of the gas turbine equipped with such a turbine blade is not ensured.

Eine andere Turbinenschanfel gemäß dem Stand der Technik ist aus der EP 1 267 040 bekannt. Demnach ist eine besonders hohe Lebensdauer der Turbinenschaufel ein Auslegungsziel, mit dem die Verfügungsdauer einer damit ausgerüsteten Gasturbine weiter erhöht werden kann. Aufgabe der Erfindung ist die Bereitstellung einer Turbinenschaufel für eine Gasturbine, bei der die Ermüdungslebensdauer verlängert ist. Zudem ist es Aufgabe der Erfindung, die Verwendung einer solchen Turbinenschaufel anzugeben.Another prior art turbine engine is known from the EP 1 267 040 known. Accordingly, a particularly long service life of the turbine blade is a design target with which the disposal period of a gas turbine equipped with it can be further increased. The object of the invention is to provide a turbine blade for a gas turbine where the fatigue life is prolonged. In addition, it is an object of the invention to provide the use of such a turbine blade.

Die auf die Turbinenschaufel gerichtete Aufgabe wird mit einer gattungsgemäßen Turbinenschaufel gelöst, welche nach den Merkmalen des Anspruchs 1 ausgestaltet ist.The task directed to the turbine blade is achieved with a generic turbine blade, which is designed according to the features of claim 1.

Der Erfindung liegt die Erkenntnis zugrunde, dass der Verschleiß und die Rissentstehung sowie das anschließende Risswachstum thermisch bedingt sind. Das Material der Turbinenschaufel ist thermischen Spannungen ausgesetzt, die durch die äußere Beaufschlagung mit Heißgas und die im Inneren stattfindende Kühlung entstehen. Es hat sich herausgestellt, dass beim Betrieb der Gasturbine in dem hohlkehlartigen Übergangsbereich zwischen Schaufelprofil und Plattform lokal vergleichsweise geringe heißgasseitige Temperaturen auftreten, verglichen mit denen im Bereich des Schaufelprofils. Daher wurde die innen gekühlte Turbinenschaufel mit an den Innenwänden angeordneten Turbulatoren im Bereich der Plattform bisher in lokal begrenzten Gebieten zu stark gekühlt. Dadurch traten lokal vergleichsweise große Temperaturunterschiede im Schaufelmaterial und dementsprechend große thermische Spannungen auf, die den Verschleiß verursachen konnten. Dieser Effekt tritt insbesondere nicht im vorderstenThe invention is based on the finding that the wear and the crack formation and the subsequent crack growth are thermally induced. The material of the turbine blade is exposed to thermal stresses caused by the external application of hot gas and the internal cooling. It has been found that during operation of the gas turbine in the trough-like transition region between the blade profile and the platform, locally comparatively low hot gas side temperatures occur compared to those in the area of the blade profile. Therefore, the internally cooled turbine blade with turbulators arranged on the inner walls in the area of the platform has hitherto been over-cooled in localized areas. As a result, locally comparatively large temperature differences in the blade material and correspondingly large thermal stresses occurred, which could cause the wear. This effect does not occur in the forefront in particular

Die Erfindung schlägt vor, diese lokalen thermischen Spannungen im Übergangsbereich wesentlich zu verringern, indem lediglich dieser nicht so stark gekühlt wird wie das Schaufelprofil. Um dies zu erreichen, ist bei einer gattungsgemäßen Turbinenschaufel vorgesehen, dass ein zumindest im Schaufelprofil liegender und an den Plattformbereich angrenzender Abschnitt der Oberfläche der Innenwand frei von Strukturelementen ist.The invention proposes to substantially reduce these local thermal stresses in the transition region merely by not cooling them as much as the blade profile. To achieve this, it is provided in a generic turbine blade that a section of the surface of the inner wall lying at least in the blade profile and adjacent to the platform region is free of structural elements.

Infolgedessen verringert sich lokal der Wärmeübergang aus dem Schaufelmaterial in das vorbeiströmende Kühlmittel im Bereich des Übergangsradius, um so gezielt den thermischen Gradienten an dieser Stelle zu reduzieren. Diese Reduzierung führt zu einem lokal wärmeren Übergangsbereich, bezogen auf den Stand der Technik. Demzufolge bilden sich geringere thermische Spannungen im Übergangradius zwischen der Plattform und dem Schaufelprofil aus, wodurch an dieser Stelle die Rissentstehung gesenkt und das Risswachstum verzögert werden kann. Der Verschleiß wird dadurch verringert.As a result, locally the heat transfer from the blade material decreases in the passing coolant in the area the transition radius, so as to purposefully reduce the thermal gradient at this point. This reduction leads to a locally warmer transition region, based on the prior art. As a result, lower thermal stresses form in the transition radius between the platform and the blade profile, which can reduce crack initiation and retard crack growth at this point. The wear is thereby reduced.

Gleichzeitig wird im Abschnitt zwischen dem Rand der Plattform und dem Hohlraum das Temperaturgefälle im Schaufelmaterial aufgrund des wärmeren Übergangsbereichs gesenkt, was die Lebensdauer der Turbinenschaufel verlängert.At the same time, in the portion between the edge of the platform and the cavity, the temperature gradient in the blade material is lowered due to the warmer transition region, which prolongs the life of the turbine blade.

Durch die vorgeschlagene Maßnahme wird die Lebensdauer, insbesondere die Ermüdungslebensdauer (Low Cycle Fatigue = LCF) für die Plattform und deren Übergang in das Schaufelprofil, d. h. im Fillet, verlängert.The proposed measure extends the life, in particular the low cycle fatigue (LCF) for the platform and its transition into the blade profile, ie. H. in the fillet, extended.

Vorteilhafte Ausgestaltungen werden in den abhängigen Ansprüchen angegeben.Advantageous embodiments are given in the dependent claims.

Besonders vorteilhaft ist die Ausgestaltung, bei der die Oberfläche der Innenwand in Höhe des Plattformbereichs und die Oberfläche der Innenwand des daran angrenzenden Abschnitts im Inneren des Schaufelprofils flach sind. Aufgrund der in diesem Abschnitt nicht verwirbelten Kühlmittelströmung ist der Wärmeübergang aus dem Schaufelmaterial in das Kühlmittel, verglichen mit dem Wärmeübergang im Schaufelprofil, verringert, sodass der Temperaturunterschied zwischen einer heißgasbeaufschlagten Außenfläche der Turbinenschaufel, der Heißseite, und der kühlmittelbeaufschlagten Innenwand der Turbinenschaufel, der Kaltseite, durch eine zulässige Anhebung der Materialtemperatur signifikant verringert werden kann. Die Verringerung führt zu reduzierten thermischen Spannungen, besonders im Bereich des Übergangs zwischen dem Schaufelprofil und der Plattform, also im Fillet.Particularly advantageous is the embodiment in which the surface of the inner wall at the level of the platform portion and the surface of the inner wall of the adjoining portion in the interior of the blade profile are flat. Due to the flow of coolant not swirled in this section, the heat transfer from the blade material into the coolant is reduced compared to the heat transfer in the airfoil profile, so that the temperature difference between a hot gas-charged outer surface of the turbine blade, the hot side, and the coolant-charged inner wall of the turbine blade, the cold side, can be significantly reduced by a permissible increase in the material temperature. The reduction leads to reduced thermal stresses, especially in the area of the transition between the blade profile and the platform, ie in the fillet.

Da die Strukturelemente auf der Innenwand des Schaufelprofil in der Regel zwar flächig, jedoch - in Radialrichtung betrachtet - unter Bildung eines mittleren minimalen Abstandes zueinander beabstandet sind, sieht eine vorteilhafte Weitergestaltung vor, dass eine zwischen der Plattformoberfläche und - ebenfalls in Radialrichtung gesehen - dem dazu nächstliegend benachbarten Strukturelement bestimmte Distanz größer ist als der mittlere, minimale Abstand zwischen zwei benachbarten Strukturelementen. Dabei beträgt vorzugsweise die Distanz mindestens das 1,1-fache des mittleren minimalen Abstandes.Since the structural elements on the inner wall of the blade profile are generally flat, but - viewed in the radial direction - spaced to form a mean minimum distance from each other, provides an advantageous further development that between the platform surface and - also in the radial direction - the next adjacent structural element determined distance is greater than the average, minimum distance between two adjacent structural elements. In this case, the distance is preferably at least 1.1 times the mean minimum distance.

Als weiter vorteilhaft hat sich herausgestellt, dass der Abschnitt eine Höhe von 5% der Profilhöhe des Schaufelprofils bis zur Profilspitze aufweist, gerechnet ab der Plattformoberfläche. Insbesondere vorteilhaft ist die Ausgestaltung, bei der ein die Strukturelemente aufweisender Bereich der im Schaufelprofil liegenden Innenwand erst ab einer Höhe von 10% der Profilhöhe, gerechnet ab der Plattformoberfläche in Richtung der Profilspitze, beginnt.As further advantageous has been found that the section has a height of 5% of the profile height of the blade profile to the profile peak, calculated from the platform surface. Particularly advantageous is the embodiment in which an area of the inner wall lying in the blade profile, the structural elements exhibiting only from a height of 10% of the profile height, calculated from the platform surface in the direction of the profile tip begins.

Durch diese Maßnahmen lässt sich eine besonders vorteilhafte Absenkung des Temperaturunterschieds zwischen der Heißseite und der Kaltseite, insbesondere im sonst besonders verschleißbehafteten Übergangsbereich herbeiführen.By means of these measures, a particularly advantageous lowering of the temperature difference between the hot side and the cold side, in particular in the otherwise particularly wear-prone transition region, can be brought about.

In einer vorteilhaften Ausgestaltung sind die Strukturelemente als Turbulatoren in Form von Rippen, Sockelfelder, Dimpels und/oder Nippel ausgebildet.In an advantageous embodiment, the structural elements are designed as turbulators in the form of ribs, base fields, dimples and / or nipples.

Da der den Verschleiß hervorrufende lokale Temperaturunterschied zwischen der Heißseite und der Kaltseite besonders in einem mittleren Bereich des Übergangsbereichs zwischen einer Vorderkante des Schaufelprofils und einer Hinterkante des Schaufelprofils auftritt, ist es besonders vorteilhaft, wenn die Oberfläche der im mittleren Bereich zwischen der Vorderkante und der Hinterkante liegenden Innenwand frei von Strukturelementen ist. Dabei kann die Turbinenschaufel mehrere, sich durch die Turbinenschaufel hindurch in Radialrichtung erstreckende und durch Stützrippen getrennte Hohlräume aufweisen, bei der lediglich der zwischen der Vorderkante und der Hinterkante des Schaufelprofils, im mittleren Bereich liegende Hohlraum den Abschnitt der Innenwand aufweist, dessen Oberfläche der Innenwand im Schaufelprofil frei von Strukturelementen ist.Since the wear-causing local temperature difference between the hot side and the cold side occurs particularly in a middle region of the transitional region between a leading edge of the airfoil and a trailing edge of the airfoil, it is particularly advantageous if the surface of the intermediate region between the leading edge and the trailing edge lying inner wall is free of structural elements. In this case, the turbine blade several, extending through the turbine blade radially extending and separated by support ribs cavities, in which only lying between the leading edge and the trailing edge of the blade profile, in the central region cavity has the portion of the inner wall whose surface of the inner wall in the blade profile is free of structural elements.

Dies geht auf die Erkenntnis zurück, dass sich entlang der Plattformlängskante - von Vorderkante zur Hinterkante betrachtet - ein Temperaturverlauf im Schaufelmaterial einstellt, der im Bereich der Vorderkante und der Hinterkante jeweils ein relatives Maximum und dazwischen, im mittleren Bereich, ein lokales Minimum aufweist. Dieses Temperaturminimum kann durch die vorgeschlagenen Maßnahmen angehoben werden. Dadurch werden gezielt nur die Bereiche lokal geringer gekühlt, in denen bisher besonders hohe Temperaturgradienten, d. h. Temperaturunterschiede zwischen der Heißseite und der Kaltseite aufgrund einer übermäßigen Kühlung auftraten. Dagegen können die im Bereich der Vorderkante und im Bereich der Hinterkante sich daran entlang erstreckenden Hohlräume wie bisher mit Strukturelementen versehen sein, die bis an die Plattform heranreichen.This is due to the knowledge that along the platform longitudinal edge - viewed from the leading edge to the trailing edge - sets a temperature profile in the blade material having a relative maximum in the region of the leading edge and the trailing edge and in between, in the middle region, a local minimum. This temperature minimum can be raised by the proposed measures. As a result, only the areas locally cooled lower, in which particularly high temperature gradients, d. H. Temperature differences between the hot side and the cold side due to excessive cooling occurred. By contrast, the cavities extending in the region of the leading edge and in the region of the trailing edge can, as hitherto, be provided with structural elements which reach as far as the platform.

Die im mittleren Bereich zwischen der Vorderkante und Hinterkante auf der Druckseite angeordnete Plattform ist strukturbedingt besonders breit, so dass bisher das lokale Temperaturminimum im Schaufelmaterial an dieser Stelle auftrat. Das Temperaturminimum kann unter Verminderung der thermischen Spannung angehoben werden, wenn insbesondere die Oberfläche der Innenwand, welche Innenwand von der saugseitigen Profilwand des Schaufelprofils gebildet ist, frei von Strukturelementen ist. Dadurch kann eine besonders lange Lebensdauerverlängerung der zweckmäßigerweise gegossenen Turbinenschaufel herbeigeführt werden.The arranged in the central region between the leading edge and trailing edge on the pressure side platform is structurally particularly wide, so far the local temperature minimum occurred in the blade material at this point. The temperature minimum can be increased while reducing the thermal stress, in particular if the surface of the inner wall, which inner wall is formed by the suction-side profile wall of the blade profile, is free of structural elements. As a result, a particularly long service life extension of the expediently cast turbine blade can be brought about.

Zudem wird zur Lösung der zweitgenannten Aufgabe die Verwendung einer Turbinenschaufel nach einem der Ansprüche 1 bis 11 in einer vorzugsweise stationären Gasturbine vorgeschlagen.In addition, the use of a turbine blade according to one of claims 1 to 11 in a preferably stationary gas turbine is proposed to solve the second-mentioned object.

Die Erfindung wird anhand von Figuren erläutert. Es zeigen:

FIG 1
eine Gasturbine in einem Längsteilschnitt,
FIG 2
eine Turbinenschaufel in perspektivischer Ansicht mit überhängenden Plattformbereichen,
FIG 3
die erfindungsgemäße Turbinenschaufel im Quer- schnitt mit unterschiedlichen Kühlkonfigurationen und
FIG 4
eine erfindungsgemäße Turbinenschaufel im Längs- schnitt mit in unterschiedlicher radialer Höhe be- ginnenden Turbulatoren.
The invention will be explained with reference to figures. Show it:
FIG. 1
a gas turbine in a longitudinal section,
FIG. 2
a turbine blade in perspective view with overhanging platform areas,
FIG. 3
the turbine blade according to the invention in cross-section with different cooling configurations and
FIG. 4
a turbine blade according to the invention in longitudinal section with starting at different radial height turbulators.

FIG 1 zeigt eine Gasturbine 1 in einem Längsteilschnitt. Sie weist im Inneren einen um eine Rotationsachse 2 drehgelagerten Rotor 3 auf, der auch als Turbinenläufer bezeichnet wird. Entlang des Rotors 3 folgen aufeinander ein Ansauggehäuse 4, ein Verdichter 5, eine torusartige Ringbrennkammer 6 mit mehreren rotationssymmetrisch zueinander angeordneten Brennern 7, eine Turbineneinheit 8 und ein Abgasgehäuse 9. Die Ringbrennkammer 6 bildet einen Verbrennungsraum 17, der mit einem ringförmigen Heißgaskanal 18 kommuniziert. Dort bilden vier hintereinander geschaltete Turbinenstufen 10 die Turbineneinheit 8. Jede Turbinenstufe 10 ist aus zwei Schaufelringen gebildet. In Strömungsrichtung eines in der Ringbrennkammer 6 erzeugten Heißgases 11 gesehen, folgt im Heißgaskanal 18 jeweils einer Leitschaufelreihe 13 eine aus Laufschaufeln 15 gebildete Reihe 14. Die Leitschaufeln 12 sind am Stator befestigt, wohingegen die Laufschaufeln 15 einer Reihe 14 mittels einer Turbinenscheibe 19 am Rotor 3 angebracht sind. An dem Rotor 3 ist ein Generator oder eine Arbeitsmaschine (nicht dargestellt) angekoppelt. FIG. 1 shows a gas turbine 1 in a longitudinal partial section. It has inside a rotatably mounted about a rotation axis 2 rotor 3, which is also referred to as a turbine runner. Along the rotor 3 successive an intake 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of rotationally symmetrical to each other arranged burners 7, a turbine unit 8 and an exhaust housing 9. The annular combustion chamber 6 forms a combustion chamber 17 which communicates with an annular hot gas channel 18. There four successive turbine stages 10 form the turbine unit 8. Each turbine stage 10 is formed of two blade rings. Viewed in the flow direction of a hot gas 11 produced in the annular combustion chamber 6, follows in the hot gas channel 18 in each case one row of guide blades 13 formed by a rotor blades 15 row 14 The vanes 12 are attached to the stator, whereas the blades 15 a row 14 by means of a turbine disk 19 on the rotor are attached. At the rotor 3 is a generator or a working machine (not shown) coupled.

Eine erfindungsgemäße hohle Turbinenschaufel 50 zeigt FIG 2 in perspektivische Ansicht. Die vorzugsweise gegossene Turbinenschaufel 50 umfasst einen Schaufelfuß 52, auf dem entlang einer Schaufelachse eine Plattform 54 und daran ein nicht in vollständiger Höhe, sondern verkürzt dargestelltes Schaufelprofil 56 angeordnet ist.A hollow turbine blade 50 according to the invention shows FIG. 2 in perspective view. The preferably cast turbine blade 50 comprises a blade root 52 on which a platform 54 is arranged along a blade axis and a blade profile 56, which is not shown in its entirety but shortened.

Das Schaufelprofil 56 weist eine druckseitige Profilwand 62 sowie eine saugseitige Profilwand 64 auf, die sich von einer Vorderkante 66 des Schaufelprofils 56 zu einer Hinterkante 68 erstrecken. Beim Betrieb der Gasturbine 1 strömt das Heißgas 11 entlang der Profilwände 62, 64, von der Vorderkante 66 in Richtung der Hinterkante 68.The blade profile 56 has a pressure-side profile wall 62 and a suction-side profile wall 64, which extend from a front edge 66 of the blade profile 56 to a trailing edge 68. During operation of the gas turbine 1, the hot gas 11 flows along the profile walls 62, 64, from the front edge 66 in the direction of the trailing edge 68.

Zwischen der Plattform 54 und dem Schaufelprofil 56 ist ein hohlkehlartiger Übergangsbereich 48 ausgebildet.Between the platform 54 and the blade profile 56, a hollow throat-like transition region 48 is formed.

Vom Schaufelfuß 52 bis in das Schaufelprofil 56 erstrecken sich durch die Turbinenschaufel 50 hindurch drei Teilhohlräume 58, in denen jeweils ein zur Kühlung vorgesehenes Kühlmittel K strömen kann. Der erste Teilhohlraum 58a verläuft parallel zur und im Bereich der Vorderkante. Ein zweiter Teilhohlraum 58b folgt - in Strömungsrichtung des Heißgases gesehen, dahinter.From the blade root 52 into the blade profile 56, three partial cavities 58 extend through the turbine blade 50, in each of which a coolant K provided for cooling can flow. The first partial cavity 58a runs parallel to and in the region of the front edge. A second partial cavity 58b follows - seen in the flow direction of the hot gas, behind it.

Die Teilhohlräume 58 erstrecken sich in Radialrichtung, bezogen auf die Einbaulage der Turbinenschaufel 50 in der Gasturbine 1, und sind durch Stützrippen 70 voneinander getrennt. Zur Versteifung des Schaufelprofils 56 verbinden die Stützrippen 70 die druckseitige Profilwand 62 mit der saugseitigen Profilwand 64.The partial cavities 58 extend in the radial direction, relative to the installation position of the turbine blade 50 in the gas turbine 1, and are separated from one another by support ribs 70. For stiffening the blade profile 56, the support ribs 70 connect the pressure-side profile wall 62 with the suction-side profile wall 64.

Aufgrund der in Axialrichtung geradlinigen Plattformlängskanten 63, des geradlinigen Schaufelfußes 52 und des in gleicher Richtung gewölbten Schaufelprofils 56 weist die Plattformoberfläche 61 druckseitig im Bereich des mittleren Teilhohlraums 58 eine sich quer zur Axialrichtung erstreckende Breite B auf, die größer ist als die im druckseitigen Bereich der Vorderkante 66 oder Hinterkante 68 vorgesehene Breite der Plattformoberfläche 61.Due to the axially rectilinear platform longitudinal edges 63, the rectilinear blade root 52 and the curved in the same direction blade profile 56, the platform surface 61 on the pressure side in the region of the central part cavity 58, a width B extending transversely to the axial direction, which width is greater than the width of the platform surface 61 provided in the pressure-side region of the leading edge 66 or trailing edge 68.

Aus Gründen der Übersichtlichkeit sind in den Teilhohlräumen 58 der in FIG 2 dargestellten Turbinenschaufel 50 keine Strukturelemente gezeigt.For reasons of clarity, the partial cavities 58 in FIG FIG. 2 shown turbine blade 50 no structural elements shown.

FIG 3 zeigt die erfindungsgemäße als Laufschaufel oder Leitschaufel ausgebildete Turbinenschaufel 50 gemäß des Querschnittes III-III der FIG 2. Dem Schaufelfuß 52 folgt in Radialrichtung, bezogen auf die Einbaulage in der Gasturbine 1, die Plattform 54 und das Schaufelprofil 56. Sowohl die Außenseite des Schaufelprofils 56 als auch die dem Schaufelprofil 56 zugewandte Oberfläche 61 der Plattform 54 sind dem die Gasturbine 1 durchströmenden Heißgas 11 ausgesetzt und werden als Heißseite bezeichnet. FIG. 3 shows the inventive designed as a blade or vane turbine blade 50 according to the cross section III-III of FIG. 2 , The blade root 52 follows in the radial direction, based on the installation position in the gas turbine 1, the platform 54 and the blade profile 56. Both the outside of the blade profile 56 and the blade profile 56 facing surface 61 of the platform 54 are the gas turbine 1 flowing through the hot gas 11th exposed and are referred to as a hot side.

Die Schnittebene des Querschnittes III-III verläuft durch den zweiten der drei jeweils fußseitig offenen Teilhohlräume 58. Das fußseitig zuführbare Kühlmittel K, beispielsweise Kühlluft, kühlt die Turbinenschaufel 50, damit diese den beim Betrieb der Gasturbine auftretenden Temperaturen widerstehen kann.The sectional plane of the cross section III-III extends through the second of the three side open partial cavities 58. The foot side supplied coolant K, such as cooling air, cools the turbine blade 50, so that they can withstand the temperatures occurring during operation of the gas turbine.

Der zweite Teilhohlraum 58b wird von einer Innenwand 59 umgeben, die teilweise von der druckseitigen Profilwand 62 und der saugseitigen Profilwand 64 gebildet ist. An den inneren Oberflächen der Profilwände 62, 64 bzw. der Innenwände 59 sind zur Steigerung des Wärmeübergangs des vom Heißgas 11 aufgeheizten Schaufelmaterials in das im Inneren strömende Kühlmittel K Strukturelemente 72 in Form von Turbulatoren vorgesehen, die als Rippen, Sockelfelder, Dimpels und/oder Nippel ausgebildet sein können. In der gezeigten Ausgestaltung handelt es sich um quer zur Kühlmittelströmungsrichtung verlaufende Rippen.The second partial cavity 58b is surrounded by an inner wall 59 which is partially formed by the pressure-side profile wall 62 and the suction-side profile wall 64. On the inner surfaces of the profile walls 62, 64 and the inner walls 59 are provided to increase the heat transfer of heated by the hot gas 11 blade material in the interior flowing coolant K structural elements 72 in the form of turbulators, as ribs, base fields, dimples and / or Nipples can be formed. In the embodiment shown, it is transverse to the coolant flow direction ribs.

Bisher war es üblich, die Turbulatoren bzw. die Strukturelemente 72 annähernd über eine gesamte Profilhöhe H von der Plattform 54 bis zur Schaufelspitze 74 (FIG 4) an den Oberflächen der Innenwände 59 vorzusehen, so wie es an der druckseitigen Profilwand 62 in einem ersten Abschnitt gezeigt ist. Mit der Erfindung wird nun ein neuer Weg beschritten. Wie an der inneren Oberfläche der saugseitigen Profilwand 64 dargestellt, beginnen die Strukturelemente 72 nicht mehr im Bereich der Plattformoberfläche 61, sondern erst ab einer vorbestimmten Höhe im Schaufelprofil 56. Somit ist ein im Schaufelprofil 56 liegender und an dem Plattformbereich angrenzender zweiter Abschnitt A der Oberfläche der saugseitigen Innenwand 59 frei von Strukturelementen 72. Obwohl der an dem Plattformbereich angrenzende zweite Abschnitt A bereits im Schaufelprofil 56 liegt, ist die in diesem Bereich befindliche Oberfläche der Innenwand 59 demgemäß flach und nicht durch Strukturelemente profiliert.So far, it has been customary, the turbulators or the structural elements 72 approximately over an entire profile height H from the platform 54 to the blade tip 74 (FIG. FIG. 4 ) on the surfaces of the inner walls 59, as shown on the pressure-side profile wall 62 in a first section. With the invention, a new path is now taken. As shown on the inner surface of the suction-side profile wall 64, the structural elements 72 no longer begin in the region of the platform surface 61, but only from a predetermined height in the blade profile 56. Thus, a second section A lying in the blade profile 56 and adjacent to the platform region is the surface Although the second section A adjoining the platform region is already located in the blade profile 56, the surface of the inner wall 59 located in this region is accordingly flat and not profiled by structural elements.

An den zweiten Anschnitt A grenzt in Richtung der Profilspitze 74 ein Bereich C der Oberfläche der Innenwand 59 an, in dem Turbulatoren bzw. Strukturelemente 72 zueinander einen mittleren, minimalen Abstand m aufweisen, der in Radialrichtung bestimmt ist.Adjacent to the second gate A in the direction of the profile tip 74 is a region C of the surface of the inner wall 59, in which turbulators or structural elements 72 have an average, minimum distance m from each other, which is determined in the radial direction.

An der inneren Oberfläche der saugseitigen Profilwand 64, die im plattformnahen zweiten Abschnitt A frei von Strukturelementen 72 ist, ist die in Radialrichtung gemessene Distanz D zwischen dem untersten bzw. zur Plattformoberfläche 61 benachbarten Strukturelement 73 und der Plattformoberfläche 61 größer als der mittlere, minimale Abstand m, Das fußseitig einströmende Kühlmittel K strömt zuerst im zweiten Abschnitt A aufgrund des lokal ebenen Untergrundes laminar und kühlt währenddessen das Schaufelmaterial konvektiv. Anschließend wird das im Bereich C strömende Kühlmittel K aufgrund der Strukturelemente 72, 73 verwirbelt, was zu einem verbesserten Wärmeübergang führt. Dadurch wird gewährleistet, dass der Übergansbereich 48 lokal geringer gekühlt wird als der Rest des Schaufelprofils 56 und so die thermischen Spannungen an dieser Stelle vermindert werden, wodurch nur noch selten Risse entstehen. Risswachstum läuft verzögert ab, verglichen mit einer Turbinenschaufel aus dem Stand der Technik. Folglich wird Lebensdauer der Turbinenschaufel 50 durch die vorgeschlagenen Maßnahmen verlängert.On the inner surface of the suction-side profile wall 64, which is free of structural elements 72 in the second section A close to the platform, the radially measured distance D between the lowest structural element 73 adjacent to the platform surface 61 and the platform surface 61 is greater than the average, minimum distance m, The inflowing coolant K flows first laminar in the second section A due to the locally flat surface and meanwhile cools the blade material convectively. Subsequently, the coolant K flowing in region C is swirled due to the structural elements 72, 73, which leads to an improved heat transfer. This ensures that the transition area 48 is local Less cooled than the rest of the blade profile 56 and so the thermal stresses are reduced at this point, which only rarely cause cracks. Crack growth is delayed as compared to a prior art turbine blade. As a result, the life of the turbine blade 50 is prolonged by the proposed measures.

FIG 4 zeigt eine weitere erfindungsgemäße Turbinenschaufel 50 im Längsschnitt mit einen Schaufelfuß 52, einer Plattform 54 und einem Schaufelprofil 56. Der profilierte Schaufelfuß 52 kann im Querschnitt tannenbaumförmig oder schwalbenschwanzförmig geformt sein. Die Turbinenschaufel 50 ist ebenfalls hohl ausgebildet und weist vier in Radialrichtung verlaufende Teilhohlräume 58 auf, die voneinander durch Stützrippen 70 getrennt sind, welche die druckseitige Profilwand 62 mit der saugseitigen Profilwand 64 verbinden. FIG. 4 shows a further turbine blade according to the invention 50 in longitudinal section with a blade root 52, a platform 54 and a blade profile 56. The profiled blade root 52 may be formed in the shape of a fir tree or dovetail in cross section. The turbine blade 50 is also hollow and has four radially extending part cavities 58, which are separated from each other by support ribs 70 which connect the pressure side profile wall 62 with the suction side profile wall 64.

Es tritt beim Betrieb der Gasturbine 1 zwischen dem vorderen Bereich und dem hinteren Bereich des Übergangsbereichs 48 aufgrund der an dieser Stelle besonders breiten Plattform 54 (siehe FIG 2) ein lokales Temperaturminimum im Schaufelmaterial auf, welches erfindungsgemäß geringer gekühlt wird, indem in den beiden mittleren Teilhohlräumen 58 die Strukturelemente 72 nicht im Bereich der Plattformoberfläche 61 beginnen, sondern erst ab einer vorbestimmten Höhe im Schaufelprofil 56. Deshalb ist der im Schaufelprofil 56 liegende und an dem Plattformbereich angrenzende Abschnitt A der Oberfläche der von der saugseitigen Profilwand 64 gebildeten Innenwände 59 frei von Strukturelementen 72.It occurs during operation of the gas turbine 1 between the front region and the rear region of the transition region 48 due to the particularly wide platform 54 at this point (see FIG. 2 ) to a local temperature minimum in the blade material, which is cooled according to the invention by the structural elements 72 do not begin in the area of the platform surface 61 in the two central part cavities 58, but only from a predetermined height in the blade profile 56. Therefore, the lying in the blade profile 56 and Section A of the surface of the inner walls 59 formed by the suction-side profile wall 64, which is adjacent to the platform region, is free of structural elements 72.

Obwohl der an dem Plattformbereich angrenzende zweiten Abschnitt A bereits im Schaufelprofil 56 liegt, ist die in diesem Bereich befindliche Oberfläche der Innenwand 59 flach und nicht durch Strukturelemente profiliert. Der zweite Abschnitt A weist beispielsweise eine Höhe von 5% der Profilhöhe H auf, gerechnet ab der Plattformoberfläche 61. Vorzugsweise beginnt der die Strukturelemente 72 aufweisende Bereich C der im Schaufelprofil 56 liegenden Innenwand 59 erst ab einer Höhe von 10% der Profilhöhe H, gerechnet ab der Plattformoberfläche 61 in Richtung einer Profilspitze 74.Although the second section A adjoining the platform region is already located in the blade profile 56, the surface of the inner wall 59 located in this region is flat and not profiled by structural elements. The second section A, for example, has a height of 5% of the profile height H, calculated from the platform surface 61. Preferably, the structure elements 72 having starting Region C of lying in the blade profile 56 inner wall 59 only from a height of 10% of the profile height H, calculated from the platform surface 61 in the direction of a profile peak 74th

Mit der Erfindung ist es möglich, den Übergangsradius bzw. - bereich 48 zwischen dem Schaufelprofil 56 und der Plattform 54 und insbesondere lokal im mittleren Bereich zwischen Vorderkante 66 und Hinterkante 68 weniger intensiv zu kühlen, sodass der Übergangsbereich lokal geringeren Temperaturunterschieden zwischen der Heißseite, d. h. Außenseite der Turbinenschaufel, und der Kaltseite, d. h. Innenseite der Turbinenschaufel, ausgesetzt ist. Die geringeren Temperaturunterschiede reduzieren die thermischen Spannungen im Schaufelmaterial im Übergangsbereich, so dass an dieser Stelle die Rissentstehung vermindert und das Risswachstum verzögert wird, was die Ermüdungslebensdauer der Turbinenschaufel 50 signifikant erhöht.With the invention, it is possible to cool less intensively the transition radius or area 48 between the blade profile 56 and the platform 54 and in particular locally in the middle region between the leading edge 66 and the trailing edge 68, so that the transition region has locally lower temperature differences between the hot side, ie , H. Outside of the turbine blade, and the cold side, d. H. Inside the turbine blade is exposed. The lower temperature differences reduce the thermal stresses in the blade material in the transition region, thereby reducing crack initiation and retarding crack growth, significantly increasing the fatigue life of the turbine blade 50.

Eine mit einer derartigen Turbineschaufel 50 ausgestattete Gasturbine kann demnach länger betrieben werden; die eingesetzten Turbineschaufeln 50 müssen seltener auf Defekte wie Risse kontrolliert werden müssen. Dadurch erhöht sich signifikant die Verfügbarkeit der Gasturbine 1.Accordingly, a gas turbine equipped with such a turbine blade 50 can be operated longer; the turbine blades 50 used must less frequently be checked for defects such as cracks. This significantly increases the availability of the gas turbine 1.

Claims (12)

  1. Turbine blade (50) for a gas turbine,
    with a blade root (52), to which a platform region, with a transversely extending platform (54), and upon it a curved blade airfoil (56), are connected in succession,
    with a platform surface (61) which is provided on the platform (54) and exposable to impingement by hot gas, from which surface the blade airfoil (56) extends to a blade tip with an airfoil height (H),
    with at least one cavity (58), which is open on the root side and exposable to throughflow of cooling medium (60), and which extends through the blade root (52) and the platform region into the blade airfoil (56), and which is divided at least into a first sub-cavity, which is adjacent to the leading edge, and a second sub-cavity, which is adjacent to the first sub-cavity, wherein the sub-cavities are partially enclosed by inner walls (59), upon the surface of which structural elements (72, 73), which influence the cooling medium (60), are provided,
    wherein a first section (A) of the surface of the inner wall (59) of the first sub-cavity, which section lies within the blade airfoil (56) and adjoins the platform region, has at least one structural element,
    characterized in that
    a second section (A) of the surface of the inner wall (59) of the second sub-cavity, which section at least lies within the blade airfoil (56) and adjoins the platform region, is free of structural elements (72, 73).
  2. Turbine blade (50) according to Claim 1,
    in which the surface of the inner wall (59) of the second sub-cavity at the level of the platform region, and the surface of the inner wall (59) of the second section (A) which adjoins it within the blade airfoil (56), are flat.
  3. Turbine blade (50) according to Claim 1 or 2,
    in which in the second sub-cavity the platform surface (60) and the adjacent structural element (73) which is closest to it, as seen in the radial direction, have a distance (D) which is greater than a mean minimum spacing (m) between two directly adjacent structural elements (72, 73) which are provided within the blade airfoil (56).
  4. Turbine blade (50) according to Claim 3,
    in which the distance (D) is at least 1.1 times the mean minimum spacing (m) between two structural elements (72, 73) which are provided within the blade airfoil (56).
  5. Turbine blade (50) according to one of Claims 1 to 4, in which the second section (A) has a height of 5% of the airfoil height (H), calculated from the platform surface (61).
  6. Turbine blade (50) according to one of Claims 1 to 5, in which a region (B), which has the structural elements (72, 73), of the inner wall (59), which lies within the blade airfoil (56), of the second sub-cavity, starts only from a height of 10% of the airfoil height (H), calculated from the platform surface (61) in the direction of the blade tip (74).
  7. Turbine blade (50) according to one of Claims 1 to 6, in which the structural elements (72, 73) are formed as turbulators in the form of ribs, block fields, dimples and/or nipples.
  8. Turbine blade (50) according to one of Claims 1 to 7,
    in which the sub-cavities are separated from each other by means of support ribs (70), and in which the second sub-cavity lies in the center region between the leading edge (66) and the trailing edge (68) of the blade airfoil (56).
  9. Turbine blade (50) according to Claim 8,
    in which the blade airfoil (56) has a suction-side airfoil wall (62) which partially delimits the cavity (58), and on the inner side of which, which faces the cavity (58), lies the second section (A) of the surface of the inner walls (59).
  10. Turbine blade (50) according to Claim 9,
    in which the blade airfoil (56) has a pressure-side airfoil wall (62) which partially delimits the cavity (58), and on the inner side of which, which faces the cavity (58), lies the first section (A) of the surface of the inner walls (59).
  11. Cast turbine blade (50) according to one of Claims 1 to 10.
  12. Use of a turbine blade (50) according to one of Claims 1 to 11, in a preferably stationary gas turbine (1).
EP06764215A 2005-07-27 2006-07-19 Cooled turbine blade for a gas turbine and use of such a turbine blade Active EP1907670B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP06764215A EP1907670B1 (en) 2005-07-27 2006-07-19 Cooled turbine blade for a gas turbine and use of such a turbine blade
PL06764215T PL1907670T3 (en) 2005-07-27 2006-07-19 Cooled turbine blade for a gas turbine and use of such a turbine blade

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP05016328 2005-07-27
EP06764215A EP1907670B1 (en) 2005-07-27 2006-07-19 Cooled turbine blade for a gas turbine and use of such a turbine blade
PCT/EP2006/064414 WO2007012592A1 (en) 2005-07-27 2006-07-19 Cooled turbine blade for a gas turbine and use of such a turbine blade

Publications (2)

Publication Number Publication Date
EP1907670A1 EP1907670A1 (en) 2008-04-09
EP1907670B1 true EP1907670B1 (en) 2008-11-05

Family

ID=35448370

Family Applications (1)

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EP06764215A Active EP1907670B1 (en) 2005-07-27 2006-07-19 Cooled turbine blade for a gas turbine and use of such a turbine blade

Country Status (9)

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US (1) US8545169B2 (en)
EP (1) EP1907670B1 (en)
JP (1) JP4689720B2 (en)
CN (1) CN101627182B (en)
AT (1) ATE413514T1 (en)
DE (1) DE502006002030D1 (en)
ES (1) ES2314928T3 (en)
PL (1) PL1907670T3 (en)
WO (1) WO2007012592A1 (en)

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Also Published As

Publication number Publication date
CN101627182A (en) 2010-01-13
ATE413514T1 (en) 2008-11-15
EP1907670A1 (en) 2008-04-09
PL1907670T3 (en) 2009-04-30
JP2009517574A (en) 2009-04-30
JP4689720B2 (en) 2011-05-25
US20090035128A1 (en) 2009-02-05
DE502006002030D1 (en) 2008-12-18
US8545169B2 (en) 2013-10-01
WO2007012592A1 (en) 2007-02-01
CN101627182B (en) 2013-02-27
ES2314928T3 (en) 2009-03-16

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