EP3158168B1 - Turbine blade and turbine - Google Patents

Turbine blade and turbine Download PDF

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Publication number
EP3158168B1
EP3158168B1 EP15756631.6A EP15756631A EP3158168B1 EP 3158168 B1 EP3158168 B1 EP 3158168B1 EP 15756631 A EP15756631 A EP 15756631A EP 3158168 B1 EP3158168 B1 EP 3158168B1
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EP
European Patent Office
Prior art keywords
turbine
turbine blade
rib element
blade
wall
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.)
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Application number
EP15756631.6A
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German (de)
French (fr)
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EP3158168A1 (en
Inventor
Fathi Ahmad
Nihal Kurt
Radan RADULOVIC
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.)
Siemens Energy Global GmbH and Co KG
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Siemens Energy Global GmbH and Co KG
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Publication of EP3158168A1 publication Critical patent/EP3158168A1/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
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • the invention relates to a turbine blade with an internally cooled turbine blade blade in which a cavity is subdivided by rib elements into at least one cooling channel carrying coolant and the relevant rib element extends longitudinally to a rib element end ending freely in the cooling channel.
  • the invention also relates to a turbine, in particular a gas turbine, with at least one turbine stage comprising a large number of turbine blades.
  • a turbine blade in this regard is often equipped with an internally cooled turbine blade blade in order to be able to thermally and mechanically withstand even the high temperatures prevailing in the turbine, in particular in a hot gas turbine.
  • the turbine blades are often subject to higher thermal and mechanical loads, and it hardly matters whether the turbine blade is a guide blade or a moving blade of the turbine.
  • an internally cooled turbine blade has a cavity through which a cooling medium can be passed.
  • a rib element or a large number of rib elements is often additionally arranged in order to form at least one cooling channel in the cavity with an often meandering cooling channel course, as can be seen, for example, in FIG US 2010/0329888 A1 are known.
  • non-meandering cooling channels such rib elements are, for example, from EP 1 757 773 A1 or also from the EP 2 497 903 A2 or the US5296308A known.
  • both a relevant front side wall and a corresponding rear side wall of the turbine blade in the region of a rib element stiffening the turbine blade can be subjected to high thermo-mechanical loads.
  • the object of the invention is achieved by a turbine blade according to claim 1.
  • the targeted reduction or saving of material in an area surrounding the rib element according to the invention makes it possible, especially in transition areas between the rib element and the outer walls, i.e. the front and rear side walls, of the turbine blade, on the front side or the rear side itself, but also in the rib element per se, especially thermo-mechanically caused stresses are significantly reduced, which means that material fatigue in critical areas can be delayed accordingly.
  • the material recess is configured as at least a partial wall thickness reduction of a turbine blade wall and/or configured as at least one concave cavity on a turbine blade wall.
  • the material recess is designed in the shape of a bowl.
  • the present material recess is arranged, for example, as a concave dent in the outer wall of the turbine bucket blade.
  • the material recess is arranged axially in front of a head side of a rib element end that ends freely in the cooling channel on a turbine bucket blade wall.
  • the material recess is arranged next to the head side of the end of the rib element in such a way that the material recess is arranged in an imaginary extension of the rib element along its longitudinal extension.
  • higher critical stress states can occur, which then promote early material fatigue there.
  • thermo-mechanical stresses occurring there, in particular in the turbine bucket blade can be reduced more favorably.
  • the material recess can be arranged at different distances from the rib element, in particular from the rib element end, especially with regard to different designs of different turbine blades.
  • the material recess is less than 30 mm or preferably less than 20 mm, more preferably less than 10 mm, is spaced from the rib member on a turbine airfoil wall.
  • the material recess can reach up to the rib element or even be worked into the rib element.
  • the rib element can have the material recess at least partially.
  • the material recess is preferably arranged at a distance of more than 1 mm or more than 5 mm from the rib element.
  • thermo-mechanical stresses caused by temperature differences between the suction side and the pressure side of the turbine airfoil can be significantly reduced in critical areas of the turbine airfoil.
  • the present material recess is designed in such a way that it enables improved stress distribution within the rib element, in transition areas between the actual rib element and the front side wall of the turbine bucket blade and/or the back side wall of the turbine bucket blade, but also in the actual outer walls of the turbine bucket blade.
  • a stress reduction of at least 10% or preferably of more than 20% or 25% can be achieved in particular in critical surrounding areas or areas around the end of the rib element.
  • material fatigue covers in particular the formation of fatigue cracks, which are specifically caused by thermo-mechanical fatigue of the blade material.
  • LCF fatigue Low Cycle Fatigue
  • short-term or low load change fatigue should be mentioned in particular with regard to a low number of load changes.
  • the possible number of load cycles can be increased by more than twice, in particular by more than three times, the previous usual number of load cycles.
  • the number of achievable load changes can be significantly increased and thus specifically the risk of premature LCF fatigue can be significantly reduced if a corresponding material recess is provided according to the invention in the area surrounding the rib element. It has been shown that the material recess according to the invention can significantly increase a relevant LCF life expectancy of a turbine blade.
  • a preferred variant provides that the material recess is arranged in an area surrounding an end of the rib element ending freely in the cooling channel. Increased and/or increased thermo-mechanical stresses can occur specifically in a region surrounding a rib element end, which ends in an exposed manner in a turbine blade airfoil cavity, and can cause more rapid material fatigue there.
  • the material recess can be constructed in different ways. It is particularly advantageous if the material recess is designed as at least one concave cavity on a turbine blade wall. A concave cavity affects the aerodynamics on the turbine bucket blade only very slightly, if at all.
  • the material recess is designed on the inside of a turbine blade wall.
  • thermo-mechanical stresses in the surrounding area of the rib element can be advantageously diverted, in particular within the outer wall of the turbine airfoil.
  • it is at least noticeable in terms of flow technology on an inner side of the outer wall of the turbine bucket blade facing the cavity or the cooling channel.
  • the material recess is arranged on the rear side wall of the turbine bucket blade.
  • the present material recess can be produced with different geometric base area shapes.
  • the material recess has a circular or oval base shape.
  • differently configured base surface shapes can be advantageous.
  • the material recess has a straight, elongate or a curved, elongate base surface shape.
  • the material recess can also have a base surface shape combined therefrom or a completely different base surface shape.
  • the material recess is distinguished by a trough-shaped or bowl-shaped indentation made on the inside of the outer wall of the turbine bucket blade.
  • the turning area of the coolant channel here corresponds to a curve of the meandering course of the coolant channel.
  • the object of the invention is also achieved by a turbine, in particular a gas turbine, with at least one turbine stage comprising a multiplicity of turbine blades, the at least one turbine stage comprising a multiplicity of turbine rotor blades and/or turbine guide vanes according to a turbine blade according to one of the features described here.
  • a turbine whose turbine blades are less stressed or endangered by material fatigue can not only be operated more reliably and with less maintenance, but also has a longer service life overall and can therefore be operated more economically.
  • the turbine blade 1 shown at least partially in each case is a rotor blade 2 of a hot gas turbine, not shown here.
  • the turbine blade 1 has an internally cooled turbine blade blade 3, the inside 4 of the front side wall 5 of the turbine blade blade 3 being shown here (FIG. 1).
  • the turbine bucket blade 3 has a cavity 10, this cavity 10 being illustrated only partially by the inner side 4 with regard to FIG.
  • a multiply wound cooling channel 13 with a meandering course of the cooling channel within the cavity 10 is configured. Cooling air as a coolant can be passed through the turbine bucket blade 3 along the winding cooling duct 13 or its meandering cooling duct course in order to cool it from the inside.
  • cooling channel 13 In the partially shown cooling channel 13, the flow from a foot area and thus from the direction of an opening 14 (see only figure 2 ) of a turbine blade root 15 essentially directly through a first cooling channel section 16 facing the leading edge area 6 and a further cooling channel section 17 facing the trailing edge area 7.
  • the meandering course of the cooling channel of the winding cooling channel 13 is configured, at least in the area of the partial view shown, in particular by the two rib elements 11 and 12, with the first rib element 11 spatially separating the two cooling channel sections 16 and 17 from one another.
  • the first rib element 11 ends freely in the cooling channel 13 with its rib element end 24 defined by its head side 23, specifically in the turning region 19.
  • thermo-mechanical stress states particularly in the transition areas between the first rib element 11 and the front side wall 5 of the turbine blade blade 3 and/or the rear side wall of the turbine blade blade 3, which can cause increased material fatigue there.
  • a material recess 29 is therefore formed on the inside 4 in the surrounding area 28 of the rib element end 24 in order to achieve an advantageous stress reduction in this surrounding area 28 of the rib element end 24 .
  • the material recess 29 is arranged at a distance of less than 10 mm from the head side 23 axially in front of the rib element end 24 .
  • the material recess 29 is present as a concave, trough-shaped cavity 30 with a substantially oval base (Not explicitly numbered) worked out on the inside 4 of the front side wall 5 of the turbine bucket blade 3 .
  • the material recess 29 also embodies a partial wall thickness reduction on the front side wall 5 of the turbine bucket blade 3.
  • reinforcing and guide rib elements 37 (numbered only as an example) and reinforcing web elements 38 (numbered only as an example) which additionally stabilize the turbine bucket blade 3 in the thinner trailing edge area 7 .
  • a reinforcing rib 40 provided with bores 39 can also be provided on the front edge region 6 .

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

Description

Die Erfindung betrifft eine Turbinenschaufel mit einem innengekühlten Turbinenschaufelblatt, in welchem ein Hohlraum durch Rippenelemente in wenigstens einen Kühlmittel führenden Kühlkanal unterteilt ist und wobei das betreffende Rippenelement sich bis zu einem in dem Kühlkanal frei endenden Rippenelementende längserstreckt.The invention relates to a turbine blade with an internally cooled turbine blade blade in which a cavity is subdivided by rib elements into at least one cooling channel carrying coolant and the relevant rib element extends longitudinally to a rib element end ending freely in the cooling channel.

Die Erfindung betrifft des Weiteren eine Turbine, insbesondere eine Gasturbine, mit zumindest einer Turbinenstufe umfassend eine Vielzahl an Turbinenschaufeln.The invention also relates to a turbine, in particular a gas turbine, with at least one turbine stage comprising a large number of turbine blades.

Gattungsgemäße Turbinenschaufeln sowie Turbinen und Gasturbinen sind aus dem Stand der Technik bereits gut bekannt.Generic turbine blades as well as turbines and gas turbines are already well known from the prior art.

Oftmals ist eine diesbezügliche Turbinenschaufel mit einem innengekühlten Turbinenschaufelblatt ausgerüstet, um selbst hohen in der Turbine, insbesondere in einer Heißgasturbine, vorherrschenden Temperaturen thermisch und mechanisch standhalten zu können. Gerade in Heißgasturbinen sind die Turbinenschaufeln oftmals thermisch und mechanisch höher belastet, wobei es hierbei kaum eine Rolle spielt, ob es sich bei der Turbinenschaufel um eine Leitschaufel oder um eine Laufschaufel der Turbine handelt. Um eine verbesserte Kühlung der Turbinenschaufel zu ermöglichen, besitzt ein derartiges innengekühltes Turbinenschaufelblatt einen Hohlraum, durch welchen ein Kühlmedium hindurch geleitet werden kann. In diesem Hohlraum ist oftmals zusätzlich noch ein Rippenelement oder eine Vielzahl an Rippenelementen angeordnet, um in dem Hohlraum wenigstens einen Kühlkanal mit einem oftmals mäandrierenden Kühlkanalverlauf auszubilden, wie sie beispielsweise aus der US 2010/0329888 A1 bekannt sind. Auch bei nicht mäandernden Kühlkanälen sind derartige Rippenelemente beispielsweise aus der EP 1 757 773 A1 oder auch aus der EP 2 497 903 A2 oder der US5296308A bekannt. Insbesondere wenn die Vorderseitenfläche des Turbinenschaufelblatts und die Rückseitenfläche des Turbinenschaufelblatts thermisch weniger gut ausbalanciert sind, können sowohl eine diesbezügliche Vorderseitenwand als auch eine entsprechende Rückseitenwand des Turbinenschaufelblatts im Bereich eines das Turbinenschaufelblatt aussteifenden Rippenelements thermo-mechanisch hoch belastet sein. Hierdurch können sich an dem Turbinenschaufelblatt partiell kritische Spannungszustände einstellen, wodurch die Turbinenschaufel in manchen Gebieten besonders nachteiligen Belastungszuständen ausgesetzt ist, welche dort im Laufe der Zeit zu einer rascheren Materialermüdung führen können. Hierbei sind insbesondere auch die Übergangsbereiche zwischen dem Rippenelement und der Vorder- bzw. der Rückseitenwand des Turbinenschaufelblatts zu nennen.A turbine blade in this regard is often equipped with an internally cooled turbine blade blade in order to be able to thermally and mechanically withstand even the high temperatures prevailing in the turbine, in particular in a hot gas turbine. Especially in hot gas turbines, the turbine blades are often subject to higher thermal and mechanical loads, and it hardly matters whether the turbine blade is a guide blade or a moving blade of the turbine. In order to enable improved cooling of the turbine blade, such an internally cooled turbine blade has a cavity through which a cooling medium can be passed. In this cavity, a rib element or a large number of rib elements is often additionally arranged in order to form at least one cooling channel in the cavity with an often meandering cooling channel course, as can be seen, for example, in FIG US 2010/0329888 A1 are known. Even with non-meandering cooling channels such rib elements are, for example, from EP 1 757 773 A1 or also from the EP 2 497 903 A2 or the US5296308A known. Especially when the front surface of the turbine airfoil and the rear side surface of the turbine blade are less well thermally balanced, both a relevant front side wall and a corresponding rear side wall of the turbine blade in the region of a rib element stiffening the turbine blade can be subjected to high thermo-mechanical loads. As a result, partially critical states of stress can occur on the turbine bucket blade, as a result of which the turbine bucket is exposed to particularly disadvantageous loading conditions in some areas, which can lead to more rapid material fatigue there over the course of time. The transition areas between the rib element and the front or rear side wall of the turbine bucket blade should also be mentioned here in particular.

Es ist Aufgabe der Erfindung, gattungsgemäße Turbinenschaufeln weiterzuentwickeln, um zumindest die vorstehend genannten Nachteile zu überwinden.It is the object of the invention to further develop generic turbine blades in order to overcome at least the disadvantages mentioned above.

Die Aufgabe der Erfindung wird von einer Turbinenschaufel gemäss Anspruch 1 gelöst.The object of the invention is achieved by a turbine blade according to claim 1.

Durch die erfindungsgemäße gezielte Reduzierung bzw. Einsparung an Material in einem Umgebungsbereich des Rippenelements können speziell in Übergangsbereichen zwischen dem Rippenelement und den Außenwänden, also den Vorder- bzw. Rückseitenwänden, der Turbinenschaufel, an der Vorderseite oder der Rückseite selbst, aber auch in dem Rippenelement an sich, speziell thermo-mechanisch verursachte Spannungen signifikant reduziert werden, wodurch eine Materialermüdung in diesbezüglich kritischen Gebieten entsprechend gut verzögert werden kann.The targeted reduction or saving of material in an area surrounding the rib element according to the invention makes it possible, especially in transition areas between the rib element and the outer walls, i.e. the front and rear side walls, of the turbine blade, on the front side or the rear side itself, but also in the rib element per se, especially thermo-mechanically caused stresses are significantly reduced, which means that material fatigue in critical areas can be delayed accordingly.

Die Materialausnehmung ist als wenigstens eine partielle Wandstärkenreduzierung einer Turbinenschaufelblattwand ausgestaltet und/oder als wenigstens eine konkave Aushöhlung an einer Turbinenschaufelblattwand ausgestaltet. Beispielsweise ist die Materialausnehmung schalenförmig ausgestaltet.The material recess is configured as at least a partial wall thickness reduction of a turbine blade wall and/or configured as at least one concave cavity on a turbine blade wall. For example, the material recess is designed in the shape of a bowl.

Nach einer zweiten Variante der Erfindung ist die vorliegende Materialausnehmung beispielsweise als konkave Delle in der Turbinenschaufelblattaußenwand angeordnet.According to a second variant of the invention, the present material recess is arranged, for example, as a concave dent in the outer wall of the turbine bucket blade.

Zudem ist die Materialausnehmung axial vor einer Kopfseite eines in dem Kühlkanal frei endenden Rippenelementendes an einer Turbinenschaufelblattwand angeordnet. Mit anderen Worten: die Materialausnehmung ist derart neben der Kopfseite des Rippenelementendes angeordnet ist, dass die Materialausnehmung in einer gedachten Verlängerung des Rippenelements längs seiner Längserstreckung angeordnet ist. Speziell in einem Bereich axial vor dem Rippenelementende, welches auch eine Innenkurvenbegrenzung des Kühlkanals formuliert, können sich höhere kritische Spannungszustände einstellen, welche dort dann eine frühzeitige Materialermüdung begünstigen.In addition, the material recess is arranged axially in front of a head side of a rib element end that ends freely in the cooling channel on a turbine bucket blade wall. In other words: the material recess is arranged next to the head side of the end of the rib element in such a way that the material recess is arranged in an imaginary extension of the rib element along its longitudinal extension. Especially in an area axially in front of the end of the rib element, which also formulates an inner curve limitation of the cooling channel, higher critical stress states can occur, which then promote early material fatigue there.

Ist die Materialausnehmung axial vor der Kopfseite des Rippenelementendes platziert, lassen sich dort insbesondere in dem Turbinenschaufelblatt auftretende thermo-mechanische Spannungen günstiger reduzieren.If the material recess is placed axially in front of the head side of the end of the rib element, thermo-mechanical stresses occurring there, in particular in the turbine bucket blade, can be reduced more favorably.

Die Materialausnehmung kann in unterschiedlichen Abständen von dem Rippenelement, insbesondere von dem Rippenelementende, entfernt angeordnet sein kann, speziell im Hinblick auf unterschiedliche Designs verschiedener Turbinenschaufeln. Um Spannungen innerhalb des Turbinenschaufelblatts hinsichtlich einer Vermeidung einer schnellen Materialermüdung günstig leiten zu können, ist die Materialausnehmung weniger als 30 mm oder vorzugweise weniger als 20 mm, besonderes vorzugt weniger als 10 mm, von dem Rippenelement beabstandet an einer Turbinenschaufelblattwand angeordnet ist.The material recess can be arranged at different distances from the rib element, in particular from the rib element end, especially with regard to different designs of different turbine blades. In order to be able to conduct stresses within the turbine bucket blade in a favorable manner with a view to avoiding rapid material fatigue, the material recess is less than 30 mm or preferably less than 20 mm, more preferably less than 10 mm, is spaced from the rib member on a turbine airfoil wall.

Die Materialausnehmung kann hierbei bis an das Rippenelement heranreichen oder sogar bis in das Rippenelement hinein gearbeitet sein. Bei letzterer Version kann das Rippenelement die Materialausnehmung zumindest teilweise aufweisen. Bevorzugt ist die Materialausnehmung jedoch mehr als 1 mm oder als 5 mm von dem Rippenelement entfernt angeordnet.The material recess can reach up to the rib element or even be worked into the rib element. In the latter version, the rib element can have the material recess at least partially. However, the material recess is preferably arranged at a distance of more than 1 mm or more than 5 mm from the rib element.

Insbesondere können durch Temperaturunterschiede zwischen der Saugseite und der Druckseite des Turbinenschaufelblatts hervorgerufene thermo-mechanische Spannungen signifikant in kritischen Gebieten des Turbinenschaufelblatts reduziert werden.In particular, thermo-mechanical stresses caused by temperature differences between the suction side and the pressure side of the turbine airfoil can be significantly reduced in critical areas of the turbine airfoil.

Es versteht sich, dass vorliegend nicht nur eine einzelne Materialausnehmung, sondern mehrere Materialausnehmungen in der Umgebung des Rippenelements an einer der Schaufelblattaußenwandungen angeordnet sein können, um einer Materialermüdung besser entgegenzuwirken.It goes without saying that in the present case not just a single material recess, but rather a plurality of material recesses can be arranged in the vicinity of the rib element on one of the outer walls of the airfoil in order to better counteract material fatigue.

Vorteilhafterweise ist die vorliegende Materialausnehmung derart ausgestaltet, dass sie eine verbesserte Spannungsverteilung innerhalb des Rippenelements, in Übergangsbereichen zwischen dem eigentlichen Rippenelement und der Vorderseitenwand des Turbinenschaufelblatts und/oder der Rückseitenwand des Turbinenschaufelblatts, aber auch in den eigentlichen Außenwänden des Turbinenschaufelblatts ermöglichen. Hierdurch kann insbesondere in kritischen Umgebungsbereichen bzw. Gebieten um das Rippenelementende herum eine Spannungsreduzierung von mindestens 10% oder vorzugsweise von mehr als 20% oder 25% erzielt werden.Advantageously, the present material recess is designed in such a way that it enables improved stress distribution within the rib element, in transition areas between the actual rib element and the front side wall of the turbine bucket blade and/or the back side wall of the turbine bucket blade, but also in the actual outer walls of the turbine bucket blade. In this way, a stress reduction of at least 10% or preferably of more than 20% or 25% can be achieved in particular in critical surrounding areas or areas around the end of the rib element.

Mit dem Begriff "Materialermüdung" ist im Sinne der Erfindung insbesondere eine Ermüdungsrissbildung erfasst, welche speziell durch eine thermo-mechanische Ermüdung des Schaufelblattmaterials hervorgerufen wird.In the context of the invention, the term “material fatigue” covers in particular the formation of fatigue cracks, which are specifically caused by thermo-mechanical fatigue of the blade material.

In diesem Zusammenhang ist insbesondere die LCF-Ermüdung (Low Cycle Fatigue), also die Kurzzeit- oder Niedriglastwechselermüdung, hinsichtlich einer niedrigen Lastwechselzahl zu nennen. Vorliegend kann die mögliche Lastwechselzahl um mehr als das zweifache, insbesondere um mehr als das dreifache, bisheriger üblicher Lastwechselzahlen erhöht werden.In this context, LCF fatigue (Low Cycle Fatigue), i.e. short-term or low load change fatigue, should be mentioned in particular with regard to a low number of load changes. In the present case, the possible number of load cycles can be increased by more than twice, in particular by more than three times, the previous usual number of load cycles.

Jedenfalls kann die Anzahl der erzielbaren Lastwechsel erheblich erhöht und damit speziell die Gefahr einer vorzeitigen LCF-Ermüdung signifikant gesenkt werden, wenn in dem Umgebungsbereich des Rippenelements erfindungsgemäß eine entsprechende Materialausnehmung vorgesehen ist. Es hat sich gezeigt, dass durch die erfindungsgemäße Materialausnehmung eine diesbezügliche LCF-Lebenserwartung einer Turbinenschaufel signifikant gesteigert werden kann.In any case, the number of achievable load changes can be significantly increased and thus specifically the risk of premature LCF fatigue can be significantly reduced if a corresponding material recess is provided according to the invention in the area surrounding the rib element. It has been shown that the material recess according to the invention can significantly increase a relevant LCF life expectancy of a turbine blade.

Eine bevorzugte Ausführungsvariante sieht vor, dass die Materialausnehmung in einem Umgebungsbereich eines frei in dem Kühlkanal endenden Rippenelementendes angeordnet ist. Speziell in einem Umgebungsbereich eines Rippenelementendes, welches freiliegend in einem Turbinenschaufelblatthohlraum endet, können vermehrt und/oder erhöhte thermo-mechanische Spannungen auftreten und dort eine raschere Materialermüdung verursachen.A preferred variant provides that the material recess is arranged in an area surrounding an end of the rib element ending freely in the cooling channel. Increased and/or increased thermo-mechanical stresses can occur specifically in a region surrounding a rib element end, which ends in an exposed manner in a turbine blade airfoil cavity, and can cause more rapid material fatigue there.

Wie vorstehend bereits angedeutet kann die Materialausnehmung unterschiedlich konstruiert sein. Besonders vorteilhaft ist es, wenn die Materialausnehmung als wenigstens eine konkave Aushöhlung an einer Turbinenschaufelblattwand ausgestaltet ist. Eine konkav ausgeformte Aushöhlung beeinflusst die Aerodynamik an dem Turbinenschaufelblatt, wenn überhaupt, nur sehr gering.As already indicated above, the material recess can be constructed in different ways. It is particularly advantageous if the material recess is designed as at least one concave cavity on a turbine blade wall. A concave cavity affects the aerodynamics on the turbine bucket blade only very slightly, if at all.

Darüber hinaus ist es vorteilhaft, wenn die Materialausnehmung an der Innenseite einer Turbinenschaufelblattwand ausgestaltet ist. Speziell mittels einer konkaven Materialausnehmung können thermo-mechanische Spannungen im Umgebungsbereich des Rippenelements insbesondere innerhalb der Turbinenschaufelblattaußenwand vorteilhaft umgeleitet werden. Zudem macht sich an einer dem Hohlraum bzw. dem Kühlkanal zugewandte Innerseite der Turbinenschaufelblattaußenwand vorgesehenen Materialausnehmung strömungstechnisch am wenigstens bemerkbar.In addition, it is advantageous if the material recess is designed on the inside of a turbine blade wall. Especially by means of a concave material recess, thermo-mechanical stresses in the surrounding area of the rib element can be advantageously diverted, in particular within the outer wall of the turbine airfoil. In addition, it is at least noticeable in terms of flow technology on an inner side of the outer wall of the turbine bucket blade facing the cavity or the cooling channel.

Hinsichtlich der Temperaturverteilung an dem Turbinenschaufelblatt ist es zweckmäßig, wenn die Materialausnehmung an der Rückseitenwand des Turbinenschaufelblatts angeordnet ist.With regard to the temperature distribution on the turbine bucket blade, it is expedient if the material recess is arranged on the rear side wall of the turbine bucket blade.

Es versteht sich, dass die vorliegende Materialausnehmung mit verschiedenen geometrischen Grundflächenformen erzeugt werden kann.It goes without saying that the present material recess can be produced with different geometric base area shapes.

Vorteilhaft ist es, wenn die Materialausnehmung eine kreisrunde oder eine ovale Grundflächenform aufweist. Je nach Verlauf des Rippenelements innerhalb des Turbinenschaufelblatts können unterschiedlich ausgestaltete Grundflächenformen vorteilhaft sein.It is advantageous if the material recess has a circular or oval base shape. Depending on the course of the rib element within the turbine bucket blade, differently configured base surface shapes can be advantageous.

Somit kann es alternativ vorteilhaft sein, wenn die Materialausnehmung eine gerade längliche oder eine gekrümmte längliche Grundflächenform aufweist.It can thus alternatively be advantageous if the material recess has a straight, elongate or a curved, elongate base surface shape.

Erscheint es hinsichtlich eines Rippenelementverlaufs und/oder eines Rippenquerschnitts oder dergleichen, oder einer Turbinenschaufelblattform zweckdienlich, kann die Materialausnehmung auch eine hieraus kombinierte Grundflächenform oder eine gänzlich andere Grundflächenform besitzen.If it appears appropriate with regard to a rib element profile and/or a rib cross section or the like, or a turbine blade blade shape, the material recess can also have a base surface shape combined therefrom or a completely different base surface shape.

Beispielsweise zeichnet sich die Materialausnehmung durch eine wannenförmig bzw. schalenförmig an die Innenseite der Turbinenschaufelblattaußenwand eingebrachte Einbuchtung aus.For example, the material recess is distinguished by a trough-shaped or bowl-shaped indentation made on the inside of the outer wall of the turbine bucket blade.

Da Gebiete des Turbinenschaufelblatts mit einer erhöhten Materialermüdungsgefahr speziell in einem Umgebungsbereich des in dem Kühlkanal frei endenden Rippenelementendes vorliegen, ist es vorteilhaft, wenn die vorliegende Materialausnehmung in einem Wendebereich des Kühlmittelkanals angeordnet ist.Since areas of the turbine bucket blade with an increased risk of material fatigue are present, especially in the area surrounding the end of the rib element that ends freely in the cooling channel, it is advantageous if the present material recess is arranged in a turning area of the coolant channel.

Der Wendebereich des Kühlmittelkanals entspricht hierbei einer Kurve des mäandrierenden Kühlkanalverlaufs des Kühlmittelkanals.The turning area of the coolant channel here corresponds to a curve of the meandering course of the coolant channel.

Die Aufgabe der Erfindung wird auch von einer Turbine, insbesondere einer Gasturbine, mit zumindest einer Turbinenstufe umfassend eine Vielzahl an Turbinenschaufeln gelöst, wobei die zumindest eine Turbinenstufe mit einer Vielzahl an Turbinenlaufschaufeln und/oder Turbinenleitschaufeln gemäß einer Turbinenschaufel nach einem der hier beschriebenen Merkmale umfasst.The object of the invention is also achieved by a turbine, in particular a gas turbine, with at least one turbine stage comprising a multiplicity of turbine blades, the at least one turbine stage comprising a multiplicity of turbine rotor blades and/or turbine guide vanes according to a turbine blade according to one of the features described here.

Eine Turbine, deren Turbinenschaufeln weniger durch Materialermüdungen belastet bzw. gefährdet sind, kann nicht nur betriebssicherer und wartungsärmer betrieben werden, sondern sie besitzt darüber hinaus insgesamt auch eine höhere Lebensdauer, und kann somit wirtschaftlicher betrieben werden.A turbine whose turbine blades are less stressed or endangered by material fatigue can not only be operated more reliably and with less maintenance, but also has a longer service life overall and can therefore be operated more economically.

Mithilfe der vorliegenden Materialausnehmung kann nicht nur die Lebenserwartung einer Turbinenschaufel erhöht werden, vielmehr sind an bestehenden Gusswerkzeuge zur Herstellung einer diesbezüglichen Turbinenschaufel nicht geringe konstruktive Änderungen erforderlich, um die erfindungsgemäße Turbinenschaufel herzustellen.With the aid of the present material recess, not only can the life expectancy of a turbine blade be increased, rather, significant structural changes are required on existing casting tools for producing a relevant turbine blade in order to produce the turbine blade according to the invention.

Weitere Merkmale, Effekte und Vorteile vorliegender Erfindung werden anhand anliegender Zeichnung und nachfolgender Beschreibung erläutert, in welchen beispielhaft ein Turbinenschaufelblatt mit einer im Bereich eines Rippenelementendes eines innerhalb eines Kühlkanals befindlichen Rippenelements angeordneten Materialausnehmung dargestellt und beschrieben ist.Further features, effects and advantages of the present invention are explained with reference to the attached drawing and the following description, in which a turbine bucket blade with a material recess arranged in the region of a rib element end of a rib element located within a cooling channel is illustrated and described.

In der Zeichnung zeigen:

  • Figur 1 schematisch und gemäß vorliegender Erfindung eine Teilansicht eines längsgeschnittenen Turbinenschaufelblatts mit einem einen Kühlkanal begrenzenden Rippenelement, vor dessen Rippenelementende eine Materialausnehmung an der Innenseite des Turbinenschaufelblatts ausgebildet ist; und
  • Figur 2 schematisch einen Querschnitt der in der Figur 1 gezeigten Turbinenschaufel.
Show in the drawing:
  • figure 1 Schematically and according to the present invention, a partial view of a longitudinally sectioned turbine bucket blade with a rib element delimiting a cooling channel, in front of the rib element end of which a material recess is formed on the inside of the turbine bucket blade; and
  • figure 2 schematically shows a cross section in the figure 1 turbine blade shown.

Bei der in den Figuren 1 und 2 jeweils zumindest teilweise gezeigten Turbinenschaufel 1 handelt es sich um eine Laufschaufel 2 einer hier nicht gezeigten Heißgasturbine.At the in the Figures 1 and 2 The turbine blade 1 shown at least partially in each case is a rotor blade 2 of a hot gas turbine, not shown here.

Die Turbinenschaufel 1 besitzt ein innengekühltes Turbinenschaufelblatt 3, wobei vorliegend die Innenseite 4 der Vorderseitenwand 5 des Turbinenschaufelblatts 3 gezeigt ist (Figur 1) .The turbine blade 1 has an internally cooled turbine blade blade 3, the inside 4 of the front side wall 5 of the turbine blade blade 3 being shown here (FIG. 1).

Wie aus der Darstellung nach der Figur 1 erkennbar ist, befindet sich rechter Hand ein Vorderkantenbereich 6 des Turbinenschaufelblatts 3. Linker Hand befindet sich dementsprechend ein Hinterkantenbereich 7 des Turbinenschaufelblatts 3, an welchem eine Vielzahl an Kühlluftaustrittsbohrungen 8 (nur exemplarisch beziffert) vorhanden sind. Der Hinterkantenbereich 7 ist insbesondere in der Figur 2 nur teilweise dargestellt.As can be seen from the illustration after the figure 1 As can be seen, there is a leading edge area 6 of the turbine blade blade 3 on the right hand side. Accordingly, there is a trailing edge area 7 of the turbine blade blade 3 on the left hand side, on which a large number of cooling air outlet bores 8 (numbered only as an example) are present. The trailing edge region 7 is particularly in the figure 2 only partially shown.

Jedenfalls besitzt das Turbinenschaufelblatt 3 einen Hohlraum 10, wobei vorliegend dieser Hohlraum 10 hinsichtlich der Figur 1 nur teilweise durch die Innenseite 4 illustriert ist.In any case, the turbine bucket blade 3 has a cavity 10, this cavity 10 being illustrated only partially by the inner side 4 with regard to FIG.

In dem Hohlraum 10 befinden sich insbesondere zwei Rippenelemente 11 und 12, mittels welchen ein mehrfach gewundener Kühlkanal 13 mit einem mäandrierenden Kühlkanalverlauf innerhalb des Hohlraums 10 ausgestaltet ist. Entlang des gewundenen Kühlkanals 13 bzw. dessen mäandrierenden Kühlkanalverlauf kann Kühlluft als Kühlmittel durch das Turbinenschaufelblatt 3 hindurch geleitet werden, um dieses von innen zu kühlen.In the cavity 10 there are in particular two rib elements 11 and 12, by means of which a multiply wound cooling channel 13 with a meandering course of the cooling channel within the cavity 10 is configured. Cooling air as a coolant can be passed through the turbine bucket blade 3 along the winding cooling duct 13 or its meandering cooling duct course in order to cool it from the inside.

Bei dem teilweise gezeigten Kühlkanal 13 durchströmt die aus einem Fußbereich und somit aus Richtung einer Öffnung 14 (siehe nur Figur 2) eines Turbinenschaufelfußes 15 kommende Kühlluft im Wesentlichen direkt einen dem Vorderkantenbereich 6 zugewandten ersten Kühlkanalabschnitt 16 und einen dem Hinterkantenbereich 7 zugewandten weiteren Kühlkanalabschnitt 17.In the partially shown cooling channel 13, the flow from a foot area and thus from the direction of an opening 14 (see only figure 2 ) of a turbine blade root 15 essentially directly through a first cooling channel section 16 facing the leading edge area 6 and a further cooling channel section 17 facing the trailing edge area 7.

Der mäandrierende Kühlkanalverlauf des gewundenen Kühlkanals 13 wird zumindest im Bereich der gezeigten Teilansicht insbesondere durch die zwei Rippenelemente 11 und 12 ausgestaltet, wobei das erste Rippenelement 11 die beiden Kühlkanalabschnitte 16 und 17 räumlich voneinander trennt.The meandering course of the cooling channel of the winding cooling channel 13 is configured, at least in the area of the partial view shown, in particular by the two rib elements 11 and 12, with the first rib element 11 spatially separating the two cooling channel sections 16 and 17 from one another.

Vorliegend endet das erste Rippenelement 11 mit seinem durch seine Kopfseite 23 definierten Rippenelementende 24 frei in dem Kühlkanal 13, und zwar in dem Wendebereich 19.In the present case, the first rib element 11 ends freely in the cooling channel 13 with its rib element end 24 defined by its head side 23, specifically in the turning region 19.

Insbesondere in dem Umgebungsbereich 28 des Rippenelementendes 24 besteht die Gefahr von kritischen thermo-mechanischen Spannungszuständen insbesondere in den Übergangsbereichen zwischen dem ersten Rippenelement 11 und der Vorderseitenwand 5 des Turbinenschaufelblatts 3 und/oder der Rückseitenwand des Turbinenschaufelblatts 3, welche dort eine erhöhte Materialermüdung verursachen können.In the area surrounding the rib element end 24 in particular, there is a risk of critical thermo-mechanical stress states, particularly in the transition areas between the first rib element 11 and the front side wall 5 of the turbine blade blade 3 and/or the rear side wall of the turbine blade blade 3, which can cause increased material fatigue there.

Deshalb ist in dem Umgebungsbereich 28 des Rippenelementendes 24 eine Materialausnehmung 29 an der Innenseite 4 ausgeformt, um in diesem Umgebungsbereich 28 des Rippenelementendes 24 eine vorteilhafte Spannungsreduzierung zu erreichen.A material recess 29 is therefore formed on the inside 4 in the surrounding area 28 of the rib element end 24 in order to achieve an advantageous stress reduction in this surrounding area 28 of the rib element end 24 .

In diesem Ausführungsbeispiel ist die Materialausnehmung 29 um weniger als 10 mm beabstandet von der Kopfseite 23 axial vor dem Rippenelementende 24 angeordnet.In this exemplary embodiment, the material recess 29 is arranged at a distance of less than 10 mm from the head side 23 axially in front of the rib element end 24 .

Die Materialausnehmung 29 ist vorliegend als konkave, wannenförmige Aushöhlung 30 mit einer im Wesentlichen ovalen Grundfläche (nicht explizit beziffert) an der Innenseite 4 der Vorderseitenwand 5 des Turbinenschaufelblatts 3 ausgearbeitet.The material recess 29 is present as a concave, trough-shaped cavity 30 with a substantially oval base (Not explicitly numbered) worked out on the inside 4 of the front side wall 5 of the turbine bucket blade 3 .

Insofern verkörpert die Materialausnehmung 29 auch eine partielle Wandstärkenreduzierung an der Vorderseitenwand 5 des Turbinenschaufelblatts 3.In this respect, the material recess 29 also embodies a partial wall thickness reduction on the front side wall 5 of the turbine bucket blade 3.

Es versteht sich, dass eine diesbezügliche gleicher oder ähnliche Materialausnehmung 29 bzw. partielle Wandstärkenreduzierung kumulativ oder alternativ auch an der hier nicht gezeigten Rückseitenwand des Turbinenschaufelblatts 3 an gegenüberliegender gleicher oder versetzter Stelle vorgesehen sein kann.It goes without saying that a corresponding same or similar material recess 29 or partial wall thickness reduction can also be provided cumulatively or alternatively on the rear side wall of the turbine bucket blade 3 (not shown here) at an opposite same or offset location.

Darüber hinaus sind noch weiteren Verstärkungs- und Leitrippenelemente 37 (nur exemplarisch beziffert) sowie Verstärkungsstegelemente 38 (nur exemplarisch beziffert) vorhanden, welche das Turbinenschaufelblatt 3 im dünneren Hinterkantenbereich 7 zusätzlich stabilisieren.In addition, there are further reinforcing and guide rib elements 37 (numbered only as an example) and reinforcing web elements 38 (numbered only as an example) which additionally stabilize the turbine bucket blade 3 in the thinner trailing edge area 7 .

Am Vorderkantenbereich 6 kann noch eine mit Bohrungen 39 versehene Verstärkungsrippe 40 vorgesehen sein.A reinforcing rib 40 provided with bores 39 can also be provided on the front edge region 6 .

Obwohl die Erfindung im Detail durch das bevorzugte Ausführungsbeispiel näher illustriert und beschrieben wurde, so ist die Erfindung nicht durch dieses offenbarte Ausführungsbeispiel eingeschränkt, und andere Variationen können vom Fachmann hieraus abgeleitet werden, ohne den Schutzumfang der Erfindung zu verlassen.Although the invention has been illustrated and described in detail by the preferred embodiment, the invention is not limited by the disclosed embodiment and other variations may be devised therefrom by those skilled in the art without departing from the scope of the invention.

Claims (6)

  1. Turbine blade (1) having an internally cooled turbine blade aerofoil (3) in which a cavity (10) is subdivided into at least one cooling channel (13), which carries coolant (14), by at least one rib element (11, 12),
    wherein the respective rib element (11, 12) extends longitudinally as far as a rib element end (24) which ends freely in the cooling channel (13),
    wherein, on an inner side of a turbine blade aerofoil wall (5), a material cutout (29) arranged next to the rib element end (24) of the respective rib element (11, 12) is formed in such a way that stresses arising within the turbine blade aerofoil (3) during operation are reducible in a surrounding region (28) of the at least one rib element (11, 12),
    wherein the material cutout (29) is in the form of at least one partial wall-thickness reduction of a turbine blade aerofoil wall (5), and/or
    is in the form of at least one concave hollow (30) in a turbine blade aerofoil wall (5),
    wherein the rib element end (24) comprises a head side (23) and the material cutout (29) is arranged next to the head side (23) in a turning region (19) of the cooling channel (13) in such a way that the material cutout (29) is arranged in an imaginary extension of the rib element (11) along the longitudinal extent thereof,
    characterized in that
    the material cutout (29) is arranged in a turbine blade aerofoil wall (5) so as to be spaced less than 30 mm apart from the at least one rib element (11, 12).
  2. Turbine blade (1) according to Claim 1, wherein the material cutout (29) is arranged in a turbine blade aerofoil wall (5) so as to be spaced less than 20 mm, preferably less than 10 mm, apart from the at least one rib element (11, 12).
  3. Turbine blade (1) according to either of Claims 1 and 2, wherein the material cutout (29) is arranged in the front side wall (5) of the turbine blade aerofoil (3).
  4. Turbine blade (1) according to one of Claims 1 to 3, wherein the material cutout (29) has a circular or an oval base shape.
  5. Turbine blade (1) according to one of Claims 1 to 4, wherein the material cutout (29) has a rectilinear elongate or a curved elongate base shape.
  6. Turbine, in particular gas turbine, having at least one turbine stage comprising a multiplicity of turbine blades (1), characterized in that at least one turbine stage comprises a multiplicity of turbine rotor blades and/or turbine guide blades according to a turbine blade (1) according to one of the preceding claims.
EP15756631.6A 2014-08-27 2015-08-27 Turbine blade and turbine Active EP3158168B1 (en)

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EP14182462.3A EP2990598A1 (en) 2014-08-27 2014-08-27 Turbine blade and turbine
PCT/EP2015/069615 WO2016030449A1 (en) 2014-08-27 2015-08-27 Turbine blade and turbine

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US6390775B1 (en) * 2000-12-27 2002-05-21 General Electric Company Gas turbine blade with platform undercut
US6607355B2 (en) * 2001-10-09 2003-08-19 United Technologies Corporation Turbine airfoil with enhanced heat transfer
DE10217390A1 (en) * 2002-04-18 2003-10-30 Siemens Ag turbine blade
DE50306044D1 (en) * 2003-09-05 2007-02-01 Siemens Ag Shovel of a turbine
EP1757773B1 (en) * 2005-08-26 2008-03-19 Siemens Aktiengesellschaft Hollow turbine airfoil
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FR2924156B1 (en) * 2007-11-26 2014-02-14 Snecma TURBINE DAWN
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US20040094287A1 (en) * 2002-11-15 2004-05-20 General Electric Company Elliptical core support and plug for a turbine bucket

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CN106795770B (en) 2018-12-11
WO2016030449A1 (en) 2016-03-03
CN106795770A (en) 2017-05-31
EP3158168A1 (en) 2017-04-26
US20170234136A1 (en) 2017-08-17

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