EP2087206A1 - Turbine blade - Google Patents

Turbine blade

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Publication number
EP2087206A1
EP2087206A1 EP07820379A EP07820379A EP2087206A1 EP 2087206 A1 EP2087206 A1 EP 2087206A1 EP 07820379 A EP07820379 A EP 07820379A EP 07820379 A EP07820379 A EP 07820379A EP 2087206 A1 EP2087206 A1 EP 2087206A1
Authority
EP
European Patent Office
Prior art keywords
cooling
turbine blade
elements
wall portion
channel
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP07820379A
Other languages
German (de)
French (fr)
Other versions
EP2087206B1 (en
Inventor
Heinz-Jürgen GROSS
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 AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP07820379A priority Critical patent/EP2087206B1/en
Publication of EP2087206A1 publication Critical patent/EP2087206A1/en
Application granted granted Critical
Publication of EP2087206B1 publication Critical patent/EP2087206B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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

Definitions

  • the invention relates to a turbine blade according to the preamble of claim 1.
  • Turbine blades in particular turbine blades for gas turbines, are exposed during operation to high temperatures which rapidly exceed the limit of material stress. This applies in particular to the regions in the vicinity of the flow inlet edge at which the hot process gas flow first of all occurs on the blade profile of the turbine blade. To turbine blades even at high
  • Cooling types include convection cooling, impingement cooling and film cooling.
  • convection cooling cooling air passes through channels in the interior of the blade and uses the convective effect to dissipate the heat.
  • impingement cooling a cooling air flow impinges on the inner blade surface from the inside. In this way, a very good cooling effect is made possible at the point of impact, which, however, is limited only to the narrow area of the point of impact and the closer environment.
  • This type of cooling is therefore usually used for cooling the flow inlet edge, which is also referred to as the leading edge, a turbine blade.
  • film cooling cooling air is directed out through openings in the turbine blade from the interior of the turbine blade. This cooling air flows around the turbine blade and forms an insulating layer between the hot process gas and the blade surface.
  • the described Cooling types are suitably combined depending on the application in order to achieve the most effective blade cooling possible.
  • coolants such as turbulators, which are usually provided in the form of ribs
  • turbulators which are usually provided in the form of ribs
  • the incorporation of fins in the cooling channels causes the flow of cooling air in the boundary layers to be detached and entangled. Due to the forced disruption of the flow, the heat transfer can be increased in the presence of a temperature difference between the cooling channel wall and the cooling air.
  • the ribbing constantly causes the flow to form new "reassembly areas" in which a substantial increase in the local heat transfer coefficient can be achieved
  • the lifetime of known fins is limited due to the high operating temperatures, which is particularly due to the geometry underlying ribs.
  • the thermal stresses associated with the known rib geometries result in internal cracks which can limit the life of the rib and ultimately also the service life of the turbine blade.
  • cooling channels are often formed in turbine blades which run parallel to and close to the flow inlet edge, and cooling air is supplied thereto by further cooling channels formed in the blades.
  • the convective cooling of the flow inlet edge realized in this way is usually supplemented by impingement cooling of the inner wall of the cooling channel extending near the flow inlet edge in the case of film-sensed blades.
  • convective cooling is intensified by turbulators disposed on the inner wall of the cooling duct.
  • the invention has for its object to provide a turbine blade, which can be cooled more effectively compared to known solutions both with existing and in the absence of film cooling and has a longer service life.
  • the turbine blade has a front edge extending on one side of the turbine blade, wherein the cooling channel is delimited by a wall section relative to the front edge and has at least one cooling element which extends from this wall section into the cooling channel.
  • the cooling element does not represent a turbulizer in the conventional sense.
  • the generally thermally stressed front edge can thus be cooled very effectively.
  • the cooling elements according to the invention which extend from the wall portion into the cooling channel, and in particular cause a strong turbulence of the cooling medium, the heat transfer can be significantly increased at a temperature difference between the wall portion and the cooling medium, along with a substantial increase of the local heat transfer coefficients. Overall, in this way, the heat in the vicinity of the leading edge can be dissipated very effectively, along with a very effective cooling of the leading edge.
  • the cooling elements initially impinged by the cooling-cooling medium are designed in the form of pegs or ribs. Pine-shaped or rib-shaped cooling elements cause on the one hand an enlargement of the coolable wall surface and on the other hand after successful
  • Impact cooling a very strong turbulence of the cooling medium, for example in the form of cooling air, which are increased by the forced so strong disruption of flow at a temperature difference between a wall of the cooling channel and the cooling medium of the heat transfer, along with a significant increase of the local heat transfer coefficient.
  • the thermal stresses which form in the cooling elements during operation of the turbine blade can be kept to a minimum, so that no internal cracks can occur, in particular the thermal stresses are significantly lower than those thermal stresses that form in known turbulators. According to the invention, therefore, the entire voltage situation is improved and it can be a significant increase in the life of the cooling elements over known solutions can be achieved, with the high life of the cooling elements and a long service life and service life of the turbine blade is connected.
  • the turbine blade according to the invention can be exposed to known gas higher temperatures compared to known solutions, even if no film cooling is provided. If film cooling is provided, even higher gas temperatures are possible. This in turn gives rise to the possibility of being able to form the turbine blade according to the invention with thinner outer walls.
  • the wall section has a wall surface facing the cooling channel, wherein the at least one cooling element or the two or more Cooling elements extend orthogonal to the wall surface or orthogonal to the curved wall surface in the cooling channel inside.
  • the inventively provided extent in a direction orthogonal to the wall surface of the cooling channel causes a very effective turbulence of the cooling medium, which is accompanied by a very effective cooling, in particular the leading edge, since according to the invention a substantially perpendicular to the longitudinal extent of the cooling elements directed flow of the cooling elements with the Can be done cooling medium.
  • the cooling channel is preferably limited by a wall portion facing the cooling channel having a curved wall surface, wherein two or more cooling elements are provided, wherein the cooling elements have a longitudinal extent extending into the cooling channel, and wherein the two or more cooling elements are directed with their longitudinal extent to the center of the curvature of the wall surface.
  • cooling elements which are directed with their longitudinal extent to the center of the curvature of the wall surface, a very effective turbulence of the cooling elements flowing against the cooling medium can be achieved.
  • the convection cooling realized by means of the cooling elements can be very effectively combined with impingement cooling, such that the cooling medium flows in a manner onto the cooling elements in such a way that it impinges on the cooling elements, so that a very high cooling effect is achieved in the respective impingement point can be, which causes in conjunction with the provided convection cooling a very effective cooling of the turbine blade according to the invention.
  • the at least one cooling element or the two or more cooling elements are integrally formed with the wall portion.
  • the cooling elements have different lengths, wherein the length of the individual cooling elements is preferably adapted to a predetermined local cooling requirement.
  • Turbine blades generally have a very inhomogeneous temperature distribution during operation, which is associated with large thermal loads acting on the turbine blades, which in particular have a detrimental effect on the service life of the turbine blade.
  • an inhomogeneous temperature distribution forming along the radial direction results for the leading edge.
  • cooling elements within the preferably adjacent the leading edge extending cooling channel whose cooling capacity is adapted over its length a predetermined cooling demand, for example, for the leading edge in the vicinity of the cooling element, the temperature distribution, for example, at the leading edge, "uniform", According to the invention, correspondingly high cooling is achieved at comparatively hot places by appropriately designed cooling elements and vice versa
  • the turbine blade according to the invention can thus be cooled in a manner which counteracts an inhomogeneous temperature distribution, which is advantageous in particular with regard to effective cooling of the leading edge.
  • the cooling capacity of each individual peg-shaped cooling element over a suitably designed length is equal to the predetermined local cooling requirement in the environment of
  • Cooling element adapted. Cooling elements in the vicinity of which a high cooling requirement exists, according to the invention have a greater length than cooling elements in the environment of the cooling demand is less pronounced. Increasing the length of a single cooling element increases the "swirl area" as well as the surface to be cooled, along with a significant increase in the local heat transfer coefficient.
  • a cooling channel partially delimiting the wall portion opposite rear wall is provided in which one or more impingement cooling holes are provided. These are preferably placed and aligned in the back wall so that the cooling air jets flowing through them are directed onto the cooling elements, whereby a particularly efficient cooling of the leading edge can be achieved.
  • the distance between the cooling element tip, on the one hand, and the mouth of the impact cooling opening, on the other hand can be kept comparatively small.
  • This also applies to a comparatively large outflow cross section of the cooling channel. A disturbance of the impact cooling jets by transverse to the beams, ie along the cooling channel flowing cooling air can thus be safely avoided.
  • the invention relates generally to a turbine blade having a leading edge, a cooling channel formed in the turbine blade for carrying cooling air, which extends at least partially along the leading edge, and a number of cooling elements, which are arranged in the longitudinal direction of the cooling channel in this sequentially stationary, each individual cooling element has a cooling capacity which is adapted to a predetermined cooling requirement for the leading edge in the vicinity of the cooling element, and wherein the cooling channel preferably extends parallel to the leading edge through the turbine blade.
  • FIG. 1 is a sketch-like cross-sectional view of a turbine blade according to the invention with a Number of arranged in a cooling channel peg-shaped cooling elements and
  • FIG. 2 shows a longitudinal section through the turbine blade along a front edge.
  • FIG. 1 shows a sketch-like sectional view of a front section of an airfoil of a turbine blade 10 according to the invention, with a flat sectional surface perpendicular to its front edge 12.
  • the front edge 12 may also be referred to as a flow inlet edge.
  • a cooling channel 14 extending parallel to the front edge 12 (ie, a radially extending channel 14 in the case of axially through-flowed turbines) is formed near the front edge 12, which is delimited by a wall section 24 in relation to the front edge 12.
  • peg-shaped cooling elements 18 extend into the cooling channel 14, wherein the cooling elements 18 are directed with their longitudinal extent to the center of the curvature of the wall surface 16.
  • openings 22 are formed to supply the cooling channel 14 of further cooling channels (not shown), which are formed in the rear region of the turbine blade 10, cooling air chilling cooling.
  • FIG. 2 shows a further sectional illustration of the front section of the turbine blade 10 according to the invention, with a flat sectional surface parallel to the front edge 12.
  • the cooling elements 18 formed on the curved wall surface 16 of the cooling channel 14 extend orthogonally from the curved wall surface 16 into the cooling channel 14 2, in the radial direction R, the length of the cooling elements 18 varies. According to the invention, this counteracts the inhomogeneous temperature distribution which forms along the leading edge 12 when the turbine blade 10 is used.
  • the frusto-conical cooling elements 18 have a greater length in the middle region than in the edge regions, since, as stated above, by increasing the length of the cooling elements 18, the local heat transfer coefficient and thus the cooling capacity the cooling elements 18 can be increased.
  • the impingement cooling comprises the impact of cooling air emerging from the openings 22 on the arched wall surface 16 or the cooling elements 18 in order to locally enable a very good cooling effect there. Since it is provided according to the invention that the cooling elements 18 are directed with their longitudinal extent to the center of the curvature of the wall surface 16, a very effective impingement cooling can be provided, with which, in conjunction with the corresponding convection cooling, a very effective cooling of the turbine blade 10 is provided can be.
  • the cooling passage 14 is opened on both sides of the turbine blade 10 to flow the cooling air in two directions out of the cooling passage 14. As a result, a temperature harmonization of the turbine blade 10 is favored, since where cooling air is needed, cooling air is also provided, and the effect of the impingement cooling is not reduced by a cross-flow.
  • the cooling elements 18 may also be formed rib-shaped, which extend along the cooling channel 14, ie in the flow direction of the cooling air.
  • the surface of the wall surface 16 is significantly increased in order to improve the cooling of the then preferably convectively cooled turbine blade 10. It is conceivable that the height of the ribs due to the aforementioned locally different temperatures at the front edge 12 can be adapted to match.

Abstract

The invention relates to a turbine blade (10) comprising at least one cooling element (18) and a cooling duct (14) for conducting a cooling medium therethrough. The at least one cooling element (18) is disposed within the flow of the cooling medium and is designed in a cog-shaped manner. The invention further relates to a turbine blade comprising a leading edge (12), a cooling duct (14) which is formed within the turbine blade (10) for conducting cooling air therethrough and extends along the flow attacking edge (12) in at least some sections, and a number of cooling elements (18) that are successively arranged in a stationary manner inside the cooling duct (14) in the longitudinal direction thereof. Each individual cooling element (18) has a cooling capacity that is adapted to a predefined cooling requirement for the leading edge (12) in the surroundings of the cooling element (18).

Description

Beschreibungdescription
Turbinenschaufelturbine blade
Die Erfindung betrifft eine Turbinenschaufel gemäß dem Oberbegriff des Anspruchs 1.The invention relates to a turbine blade according to the preamble of claim 1.
Turbinenschaufeln, insbesondere Turbinenschaufeln für Gas- turbinen werden während des Betriebs hohen Temperaturen ausgesetzt, welche schnell die Grenze der Materialbeanspruchung überschreiten. Dies gilt insbesondere für die Bereiche in Umgebung der Strömungseintrittskante, an der die heiße Prozessgasströmung zu allererst auf das Schaufelprofil der Turbinen- schaufei auftritt. Um Turbinenschaufeln auch bei hohenTurbine blades, in particular turbine blades for gas turbines, are exposed during operation to high temperatures which rapidly exceed the limit of material stress. This applies in particular to the regions in the vicinity of the flow inlet edge at which the hot process gas flow first of all occurs on the blade profile of the turbine blade. To turbine blades even at high
Temperaturen einsetzen zu können, ist es schon seit langem bekannt, Turbinenschaufeln geeignet zu kühlen, so dass sie eine höhere Temperaturbeständigkeit aufweisen. Mit Turbinenschaufeln, die eine höhere Temperaturbeständigkeit aufweisen, lassen sich insbesondere höhere energetische Wirkungsgrade erzielen .To use temperatures, it has long been known to cool turbine blades suitable, so that they have a higher temperature resistance. With turbine blades, which have a higher temperature resistance, higher energy efficiencies can be achieved in particular.
Bekannte Kühlarten sind unter anderem die Konvektionskühlung, die Prallkühlung und die Filmkühlung. Bei der Konvektions- kühlung führt man Kühlluft durch Kanäle im Schaufelinneren und nutzt den konvektiven Effekt, um die Wärme abzuführen. Bei der Prallkühlung prallt ein Kühlluftstrom von innen auf die innere Schaufeloberfläche. Auf diese Weise wird im Auf- treffpunkt eine sehr gute Kühlwirkung ermöglicht, die aller- dings nur auf den engen Bereich des Auftreffpunkts und die nähere Umgebung beschränkt ist. Diese Art der Kühlung wird deshalb meist zur Kühlung der Strömungseintrittskante, welche auch als Vorderkante bezeichnet wird, einer Turbinenschaufel verwendet. Bei der Filmkühlung wird Kühlluft über Öffnungen in der Turbinenschaufel vom Inneren der Turbinenschaufel nach außen geführt. Diese Kühlluft umströmt die Turbinenschaufel und bildet eine isolierende Schicht zwischen dem heißen Prozessgas und der Schaufeloberfläche aus. Die beschriebenen Kühlarten werden je nach Anwendungsfall geeignet kombiniert, um eine möglichst wirksame Schaufelkühlung zu erzielen.Well-known types of cooling include convection cooling, impingement cooling and film cooling. In convection cooling, cooling air passes through channels in the interior of the blade and uses the convective effect to dissipate the heat. During impingement cooling, a cooling air flow impinges on the inner blade surface from the inside. In this way, a very good cooling effect is made possible at the point of impact, which, however, is limited only to the narrow area of the point of impact and the closer environment. This type of cooling is therefore usually used for cooling the flow inlet edge, which is also referred to as the leading edge, a turbine blade. In film cooling, cooling air is directed out through openings in the turbine blade from the interior of the turbine blade. This cooling air flows around the turbine blade and forms an insulating layer between the hot process gas and the blade surface. The described Cooling types are suitably combined depending on the application in order to achieve the most effective blade cooling possible.
Ergänzend zu den oben beschriebenen Kühlarten ist die Ver- wendung von Kühlmitteln, wie Turbulatoren, die meist in Form von Rippen bereitgestellt sind, sehr verbreitet. Diese sind innerhalb der für die Konvektionsströmung vorgesehenen Kühlkanäle angeordnet, die im Inneren der Turbinenschaufel verlaufen. Der Einbau von Rippen in den Kühlkanälen bewirkt, dass die Strömung der Kühlluft in den Grenzschichten abgelöst und verwirbelt wird. Durch die so erzwungene Störung der Strömung kann bei einem vorliegenden Temperaturunterschied zwischen Kühlkanalwand und Kühlluft der Wärmeübergang gesteigert werden. Durch die Berippung wird die Strömung ständig dazu veranlasst neue „Wiederanlegegebiete" zu bilden, in denen eine wesentliche Steigerung des lokalen Wärmeübergangskoeffizienten erzielt werden kann. Die Lebensdauer bekannter Rippen ist infolge der hohen Betriebstemperaturen eingeschränkt, was insbesondere eine Folge der bekannten Rippen zugrundeliegenden Geometrie ist. Die mit den bekannten Rippen-Geometrien verbundenen thermischen Spannungen haben Innenanrisse zur Folge, welche die Lebensdauer der Rippe und damit letztlich auch die Einsatzdauer der Turbinenschaufel einschränken können.In addition to the types of cooling described above, the use of coolants, such as turbulators, which are usually provided in the form of ribs, is very common. These are arranged within the cooling channels provided for the convection flow, which run in the interior of the turbine blade. The incorporation of fins in the cooling channels causes the flow of cooling air in the boundary layers to be detached and entangled. Due to the forced disruption of the flow, the heat transfer can be increased in the presence of a temperature difference between the cooling channel wall and the cooling air. The ribbing constantly causes the flow to form new "reassembly areas" in which a substantial increase in the local heat transfer coefficient can be achieved The lifetime of known fins is limited due to the high operating temperatures, which is particularly due to the geometry underlying ribs. The thermal stresses associated with the known rib geometries result in internal cracks which can limit the life of the rib and ultimately also the service life of the turbine blade.
Zur Kühlung der während des Betriebs thermisch meist sehr stark beanspruchten Strömungseintrittskante, d.h. Vorderkante, von Turbinenschaufeln sind in Turbinenschaufeln oft parallel und nahe zur Strömungseintrittskante verlaufende Kühlkanäle ausgebildet, denen durch weitere in den Schaufeln ausgebildete Kühlkanäle Kühlluft zugeführt wird. Die so realisierte konvektive Kühlung der Strömungseintrittskante wird bei filmgefühlten Schaufeln meist durch eine Prallkühlung der Innenwand des nahe der Strömungseintrittskante verlaufenden Kühlkanals ergänzt. In Anwendungen, bei denen keine Filmkühlung der Turbinenschaufeln vorgenommen wird, wird die konvektive Kühlung durch an der Innenwand des Kühlkanals angeordnete Turbulatoren intensiviert. Insgesamt betrachtet besteht gegenwärtig sowohl bei filmgekühlten als auch bei nicht filmgekühlten Schaufeln hinsichtlich der Kühlung, insbesondere in Bezug auf die Kühlung der Strömungseintrittskante, noch deutlicher Verbesserungs- bedarf. Insbesondere berücksichtigen die gegenwärtigen Kühl- Lösungen auch keine sich während des Einsatzes von Turbinenschaufeln ausbildende inhomogene Temperaturverteilung.In order to cool the flow inlet edge, ie the leading edge, of turbine blades, which is usually subjected to very high thermal stresses during operation, cooling channels are often formed in turbine blades which run parallel to and close to the flow inlet edge, and cooling air is supplied thereto by further cooling channels formed in the blades. The convective cooling of the flow inlet edge realized in this way is usually supplemented by impingement cooling of the inner wall of the cooling channel extending near the flow inlet edge in the case of film-sensed blades. In applications where film cooling of the turbine blades is not performed, convective cooling is intensified by turbulators disposed on the inner wall of the cooling duct. Overall, there is currently a clear need for improvement both in the case of film-cooled and non-film-cooled blades with regard to the cooling, in particular with regard to the cooling of the flow inlet edge. In particular, the present cooling solutions also do not consider inhomogeneous temperature distribution that forms during the use of turbine blades.
Der Erfindung liegt die Aufgabe zugrunde, eine Turbinen- schaufei anzugeben, die sowohl bei vorhandener als auch bei nicht vorhandener Filmkühlung gegenüber bekannten Lösungen wirksamer gekühlt werden kann und die eine höhere Einsatzdauer aufweist.The invention has for its object to provide a turbine blade, which can be cooled more effectively compared to known solutions both with existing and in the absence of film cooling and has a longer service life.
Diese Aufgabe ist erfindungsgemäß mit einer Turbinenschaufel gemäß den Merkmalen des Anspruchs 1 gelöst.This object is achieved with a turbine blade according to the features of claim 1.
Die Turbinenschaufel weist eine sich an einer Seite der Turbinenschaufel erstreckende Vorderkante auf, wobei der Kühl- kanal gegenüber der Vorderkante durch einen Wandabschnitt begrenzt ist und mindestens ein Kühlelement aufweist, welches sich von diesem Wandabschnitt ausgehend in den Kühlkanal hinein erstreckt. Das Kühlelement stellt dabei keine Turbu- lator im herkömmlichen Sinne dar.The turbine blade has a front edge extending on one side of the turbine blade, wherein the cooling channel is delimited by a wall section relative to the front edge and has at least one cooling element which extends from this wall section into the cooling channel. The cooling element does not represent a turbulizer in the conventional sense.
Die in der Regel thermisch stark beanspruchte Vorderkante kann somit sehr wirksam gekühlt werden. Mittels der erfindungsgemäßen Kühlelemente, die sich von dem Wandabschnitt in den Kühlkanal hinein erstrecken, und die insbesondere eine starke Verwirbelung des Kühlmediums bewirken, kann bei einem vorliegenden Temperaturunterschied zwischen dem Wandabschnitt und dem Kühlmedium der Wärmeübergang deutlich gesteigert werden, einhergehend mit einer wesentlichen Steigerung des lokalen Wärmeübergangskoeffizienten. Insgesamt betrachtet kann auf diese Weise die Wärme in Umgebung der Vorderkante sehr wirksam abgeführt werden, einhergehend mit einer sehr wirksamen Kühlung der Vorderkante. Erfindungsgemäß sind die von dem Kühlmedium zuerst prallkühl- artig angeströmten Kühlelemente zapfenförmig oder rippen- förmig ausgebildet. Zapfenförmig oder rippenförmig ausgebildete Kühlelemente bewirken einerseits eine Vergrößerung der kühlbaren Wandfläche und andererseits nach erfolgterThe generally thermally stressed front edge can thus be cooled very effectively. By means of the cooling elements according to the invention, which extend from the wall portion into the cooling channel, and in particular cause a strong turbulence of the cooling medium, the heat transfer can be significantly increased at a temperature difference between the wall portion and the cooling medium, along with a substantial increase of the local heat transfer coefficients. Overall, in this way, the heat in the vicinity of the leading edge can be dissipated very effectively, along with a very effective cooling of the leading edge. According to the invention, the cooling elements initially impinged by the cooling-cooling medium are designed in the form of pegs or ribs. Pine-shaped or rib-shaped cooling elements cause on the one hand an enlargement of the coolable wall surface and on the other hand after successful
Prallkühlung eine sehr starke Verwirbelung des Kühlmediums, beispielsweise in Form von Kühlluft, wobei durch die so erzwungene starke Störung der Strömung bei einem vorliegenden Temperaturunterschied zwischen einer Wand des Kühlkanals und dem Kühlmedium der Wärmeübergang gesteigert werden, einhergehend mit einer wesentlichen Steigerung des lokalen Wärmeübergangskoeffizienten .Impact cooling a very strong turbulence of the cooling medium, for example in the form of cooling air, which are increased by the forced so strong disruption of flow at a temperature difference between a wall of the cooling channel and the cooling medium of the heat transfer, along with a significant increase of the local heat transfer coefficient.
Ferner können mit der erfindungsgemäß vorgesehenen zapfen- förmigen oder rippenförmigen Ausbildung der Kühlelemente die sich während des Betriebs der Turbinenschaufel in den Kühlelementen ausbildenden thermischen Spannungen minimal gehalten werden, so dass es zu keinen Innenanrissen kommen kann, insbesondere sind hierbei die thermischen Spannungen deutlich geringer als die thermischen Spannungen, die sich in bekannten Turbulatoren ausbilden. Erfindungsgemäß wird also die gesamte Spannungssituation verbessert und es kann eine deutliche Erhöhung der Lebensdauer der Kühlelemente gegenüber bekannten Lösungen erzielt werden, wobei mit der hohen Lebensdauer der Kühlelemente auch eine hohe Einatzdauer bzw. Lebensdauer der Turbinenschaufel verbunden ist.Furthermore, with the conical or rib-shaped design of the cooling elements provided according to the invention, the thermal stresses which form in the cooling elements during operation of the turbine blade can be kept to a minimum, so that no internal cracks can occur, in particular the thermal stresses are significantly lower than those thermal stresses that form in known turbulators. According to the invention, therefore, the entire voltage situation is improved and it can be a significant increase in the life of the cooling elements over known solutions can be achieved, with the high life of the cooling elements and a long service life and service life of the turbine blade is connected.
Die erfindungsgemäße Turbinenschaufel kann gegenüber bekannten Lösungen höheren Gastemperaturen ausgesetzt werden, selbst wenn keine Filmkühlung vorgesehen ist. Sofern Filmkühlung vorgesehen ist, sind noch höhere Gastemperaturen möglich. Hieraus wiederum ergibt sich die Möglichkeit, die erfindungsgemäße Turbinenschaufel mit dünneren Außenwänden ausbilden zu können.The turbine blade according to the invention can be exposed to known gas higher temperatures compared to known solutions, even if no film cooling is provided. If film cooling is provided, even higher gas temperatures are possible. This in turn gives rise to the possibility of being able to form the turbine blade according to the invention with thinner outer walls.
Bei einer praktischen Weiterbildung der Erfindung weist der Wandabschnitt eine zum Kühlkanal gewandte Wandfläche auf, wobei das mindestens eine Kühlelement bzw. die zwei oder mehr Kühlelemente sich orthogonal zu der Wandfläche bzw. orthogonal zu der gewölbten Wandfläche in den Kühlkanal hinein erstrecken. Die erfindungsgemäß vorgesehene Erstreckung in einer Richtung orthogonal zur Wandfläche des Kühlkanals be- wirkt eine sehr wirksame Verwirbelung des Kühlmediums, die mit einer sehr wirksamen Kühlung, insbesondere der Vorderkante einhergeht, da erfindungsgemäß eine im Wesentlichen rechtwinkelig zur Längserstreckung der Kühlelemente gerichtete Anströmung der Kühlelemente mit dem Kühlmedium erfolgen kann.In a practical development of the invention, the wall section has a wall surface facing the cooling channel, wherein the at least one cooling element or the two or more Cooling elements extend orthogonal to the wall surface or orthogonal to the curved wall surface in the cooling channel inside. The inventively provided extent in a direction orthogonal to the wall surface of the cooling channel causes a very effective turbulence of the cooling medium, which is accompanied by a very effective cooling, in particular the leading edge, since according to the invention a substantially perpendicular to the longitudinal extent of the cooling elements directed flow of the cooling elements with the Can be done cooling medium.
Bei einer weiteren vorteilhaften Weiterbildung der Erfindung ist der Kühlkanal bevorzugt durch einen Wandabschnitt begrenzt, der zum Kühlkanal gewandt eine gewölbte Wandfläche aufweist, wobei zwei oder mehr Kühlelemente vorgesehen sind, wobei die Kühlelemente eine in den Kühlkanal sich hinein erstreckende Längserstreckung aufweisen, und wobei die zwei oder mehr Kühlelemente mit ihrer Längserstreckung auf das Zentrum der Wölbung der Wandfläche gerichtet sind.In a further advantageous embodiment of the invention, the cooling channel is preferably limited by a wall portion facing the cooling channel having a curved wall surface, wherein two or more cooling elements are provided, wherein the cooling elements have a longitudinal extent extending into the cooling channel, and wherein the two or more cooling elements are directed with their longitudinal extent to the center of the curvature of the wall surface.
Mittels Kühlelementen, die mit ihrer Längserstreckung auf das Zentrum der Wölbung der Wandfläche gerichtet sind, kann eine sehr wirksame Verwirbelung des die Kühlelemente anströmenden Kühlmediums erzielt werden. Insbesondere kann mittels dieser erfindungsgemäßen Weiterbildung die mittels der Kühlelemente realisierte Konvektionskühlung sehr wirksam mit einer Prallkühlung kombiniert werden, derart, dass das Kühlmedium auf eine Weise auf die Kühlelemente zuströmt, dass es auf die Kühlelemente aufprallt, so dass im jeweiligen Auftreffpunkt eine sehr hohe Kühlwirkung erzielt werden kann, die in Ver- bindung mit der bereitgestellten Konvektionskühlung eine sehr wirksame Kühlung der erfindungsgemäßen Turbinenschaufel bewirkt .By means of cooling elements, which are directed with their longitudinal extent to the center of the curvature of the wall surface, a very effective turbulence of the cooling elements flowing against the cooling medium can be achieved. In particular, by means of this development according to the invention, the convection cooling realized by means of the cooling elements can be very effectively combined with impingement cooling, such that the cooling medium flows in a manner onto the cooling elements in such a way that it impinges on the cooling elements, so that a very high cooling effect is achieved in the respective impingement point can be, which causes in conjunction with the provided convection cooling a very effective cooling of the turbine blade according to the invention.
Bei einer weiteren praktischen Weiterbildung der Erfindung sind das mindestens eine Kühlelement bzw. die zwei oder mehr Kühlelemente einstückig mit dem Wandabschnitt ausgebildet. Bei einer besonders praktischen Weiterbildung der Erfindung weisen die Kühlelemente unterschiedliche Längen auf, wobei die Länge der einzelnen Kühlelemente bevorzugt einem vorgegebenen örtlichen Kühlbedarf angepasst ist.In a further practical development of the invention, the at least one cooling element or the two or more cooling elements are integrally formed with the wall portion. In a particularly practical development of the invention, the cooling elements have different lengths, wherein the length of the individual cooling elements is preferably adapted to a predetermined local cooling requirement.
Turbinenschaufeln weisen im Betrieb in der Regel eine sehr inhomogene Temperaturverteilung auf, die mit großen, auf die Turbinenschaufeln einwirkenden thermischen Belastungen verbunden sind, die sich insbesondere nachteilig auf die Lebens- dauer der Turbinenschaufel auswirken. So ergibt sich beispielsweise für Turbinenschaufeln, die in axial durchströmten Turbinen zum Einsatz kommen, für die Vorderkante ein sich entlang der radialen Richtung ausbildende inhomogene Temperatur Verteilung. Durch den erfindungsgemäßen Einsatz von Kühlelementen innerhalb des vorzugsweise nahe der Vorderkante verlaufenden Kühlkanals, deren Kühlvermögen über ihre Länge einem vorgegebenen Kühlbedarf, beispielsweise für die Vorderkante in der Umgebung des Kühlelements angepasst ist, kann die Temperaturverteilung, beispielsweise an der Vorderkante, „vergleichmässigt" werden, da erfindungsgemäß an vergleichsweise heißen Stellen durch geeignet ausgebildete Kühlelemente eine entsprechend starke Kühlung erfolgt und umgekehrt. Die erfindungsgemäße Turbinenschaufel kann somit auf eine Weise gekühlt werden, die einer inhomogenen Temperaturverteilung entgegenwirkt, was insbesondere im Hinblick auf eine wirksame Kühlung der Vorderkante von Vorteil ist.Turbine blades generally have a very inhomogeneous temperature distribution during operation, which is associated with large thermal loads acting on the turbine blades, which in particular have a detrimental effect on the service life of the turbine blade. Thus, for example, for turbine blades that are used in axially through-flow turbines, an inhomogeneous temperature distribution forming along the radial direction results for the leading edge. Due to the inventive use of cooling elements within the preferably adjacent the leading edge extending cooling channel whose cooling capacity is adapted over its length a predetermined cooling demand, for example, for the leading edge in the vicinity of the cooling element, the temperature distribution, for example, at the leading edge, "uniform", According to the invention, correspondingly high cooling is achieved at comparatively hot places by appropriately designed cooling elements and vice versa The turbine blade according to the invention can thus be cooled in a manner which counteracts an inhomogeneous temperature distribution, which is advantageous in particular with regard to effective cooling of the leading edge.
Erfindungsgemäß ist das Kühlvermögen jedes einzelnen zapfen- förmigen Kühlelements über eine geeignet ausgebildete Länge dem vorgegebenen örtlichen Kühlbedarf in der Umgebung desAccording to the invention, the cooling capacity of each individual peg-shaped cooling element over a suitably designed length is equal to the predetermined local cooling requirement in the environment of
Kühlelements angepasst. Kühlelemente, in deren Umgebung ein hoher Kühlbedarf besteht, weisen erfindungsgemäß eine größere Länge auf als Kühlelemente in deren Umgebung der Kühlbedarf geringer ausgeprägt ist. Durch Erhöhung der Länge eines ein- zelnen Kühlelements wird zum einen der „Verwirbelungsbereich" als auch die zu kühlende Oberfläche vergrößert, einhergehend mit einer deutlichen Erhöhung des lokalen Wärmeübergangskoeffizienten. Bevorzugtermassen ist als Mittel zum Prallkühlen des Wandabschnittes eine den Kühlkanal teilweise begrenzende, dem Wandabschnitt gegenüberliegende Rückwand vorgesehen, in der ein oder mehrere Prallkühlöffnungen vorgesehen sind. Diese sind vorzugsweise derartig in der Rückwand platziert und ausgerichtet, dass die durch sie hindurchströmenden Kühlluftstrahlen auf die Kühlelemente geleitet werden, wodurch eine besonders effiziente Kühlung von der Vorderkante erreicht werden kann. Insbesondere aufgrund der vergleichsweise großen Längserstreckung der Kühlelemente in den Kühlkanal hinein kann der Abstand zwischen Kühlelementspitze einerseits und der Mündung der Prallkühlöffnung andererseits vergleichweise klein gehalten werden. Dies gilt auch bei einem vergleichs- weise großen Abströmquerschnitt des Kühlkanals. Eine Störung der Prallkühlstrahlen durch quer zu den Strahlen, d. h. entlang des Kühlkanals strömender Kühlluft kann somit sicher vermieden werden.Cooling element adapted. Cooling elements in the vicinity of which a high cooling requirement exists, according to the invention have a greater length than cooling elements in the environment of the cooling demand is less pronounced. Increasing the length of a single cooling element increases the "swirl area" as well as the surface to be cooled, along with a significant increase in the local heat transfer coefficient. Preferably, as a means for impingement cooling of the wall portion, a cooling channel partially delimiting, the wall portion opposite rear wall is provided in which one or more impingement cooling holes are provided. These are preferably placed and aligned in the back wall so that the cooling air jets flowing through them are directed onto the cooling elements, whereby a particularly efficient cooling of the leading edge can be achieved. In particular, due to the comparatively large longitudinal extension of the cooling elements into the cooling channel, the distance between the cooling element tip, on the one hand, and the mouth of the impact cooling opening, on the other hand, can be kept comparatively small. This also applies to a comparatively large outflow cross section of the cooling channel. A disturbance of the impact cooling jets by transverse to the beams, ie along the cooling channel flowing cooling air can thus be safely avoided.
Die Erfindung betrifft insgesamt eine Turbinenschaufel mit einer Vorderkante, einem in der Turbinenschaufel ausgebildeten Kühlkanal zur Durchführung von Kühlluft, der sich wenigstens abschnittsweise längs der Vorderkante erstreckt, und einer Anzahl von Kühlelementen, die in Längsrichtung des Kühlkanals in diesem aufeinanderfolgend ortsfest angeordnet sind, wobei jedes einzelne Kühlelement ein Kühlvermögen aufweist, welches einem vorgegebenen Kühlbedarf für die Vorderkante in der Umgebung des Kühlelements angepasst ist, und wobei sich der Kühlkanal bevorzugt parallel zur Vorderkante durchgehend durch die Turbinenschaufel erstreckt.The invention relates generally to a turbine blade having a leading edge, a cooling channel formed in the turbine blade for carrying cooling air, which extends at least partially along the leading edge, and a number of cooling elements, which are arranged in the longitudinal direction of the cooling channel in this sequentially stationary, each individual cooling element has a cooling capacity which is adapted to a predetermined cooling requirement for the leading edge in the vicinity of the cooling element, and wherein the cooling channel preferably extends parallel to the leading edge through the turbine blade.
Nachfolgend wird ein Ausführungsbeispiel einer erfindungsgemäßen Turbinenschaufel anhand der beigefügten Zeichnungen näher erläutert. Es zeigen:Hereinafter, an embodiment of a turbine blade according to the invention will be explained in more detail with reference to the accompanying drawings. Show it:
FIG 1 eine skizzenhafte Querschnittdarstellung einer erfindungsgemäßen Turbinenschaufel mit einer Anzahl von in einem Kühlkanal angeordneten zapfenförmigen Kühlelementen und1 is a sketch-like cross-sectional view of a turbine blade according to the invention with a Number of arranged in a cooling channel peg-shaped cooling elements and
FIG 2 einen Längsschnitt durch die Turbinenschaufel entlang einer Vorderkante.2 shows a longitudinal section through the turbine blade along a front edge.
FIG 1 zeigt eine skizzenhafte Schnittdarstellung eines vorderen Abschnitts eines Schaufelblattes einer erfindungsgemäßen Turbinenschaufel 10, mit einer ebenen Schnittfläche rechtwinkelig zu deren Vorderkante 12. Die Vorderkante 12 kann auch als Strömungseintrittskante bezeichnet werden. Im Inneren der Turbinenschaufel 10 ist nahe der Vorderkante 12 ein sich parallel zur Vorderkante 12 erstreckender Kühlkanal 14 ausgebildet (also ein sich radial erstreckender Kanal 14 bei axial durchströmten Turbinen) , der gegenüber der Vorderkante 12 durch einen Wandabschnitt 24 begrenzt ist. Von einer gewölbten Wandfläche 16 des Kühlkanals 14 erstrecken sich zapfenförmige Kühlelemente 18 in den Kühlkanal 14 hinein, wobei die Kühlelemente 18 mit ihrer Längserstreckung auf das Zentrum der Wölbung der Wandfläche 16 gerichtet sind.1 shows a sketch-like sectional view of a front section of an airfoil of a turbine blade 10 according to the invention, with a flat sectional surface perpendicular to its front edge 12. The front edge 12 may also be referred to as a flow inlet edge. In the interior of the turbine blade 10, a cooling channel 14 extending parallel to the front edge 12 (ie, a radially extending channel 14 in the case of axially through-flowed turbines) is formed near the front edge 12, which is delimited by a wall section 24 in relation to the front edge 12. From a curved wall surface 16 of the cooling channel 14, peg-shaped cooling elements 18 extend into the cooling channel 14, wherein the cooling elements 18 are directed with their longitudinal extent to the center of the curvature of the wall surface 16.
In einer Rückwand 20 des Kühlkanals 14 sind Öffnungen 22 ausgebildet, um dem Kühlkanal 14 von weiteren Kühlkanälen (nicht dargestellt), die im hinteren Bereich der Turbinenschaufel 10 ausgebildet sind, Kühlluft prallkühlend zuzuführen.In a rear wall 20 of the cooling channel 14 openings 22 are formed to supply the cooling channel 14 of further cooling channels (not shown), which are formed in the rear region of the turbine blade 10, cooling air chilling cooling.
FIG 2 zeigt eine weitere Schnittdarstellung des vorderen Abschnitts der erfindungsgemäßen Turbinenschaufel 10, mit einer ebenen Schnittfläche parallel zur Vorderkante 12. Die an der gewölbten Wandfläche 16 des Kühlkanals 14 ausgebildeten Kühlelemente 18 erstrecken sich orthogonal von der gewölbten Wandfläche 16 hinein in den Kühlkanal 14. Wie aus FIG 2 ersichtlich variiert in radialer Richtung R die Länge der Kühlelemente 18. Dies dient erfindungemäß dazu, der sich bei Ein- satz der Turbinenschaufel 10 entlang der Vorderkante 12 ausbildenden inhomogenen Temperaturverteilung entgegenzuwirken. So wird insbesondere zum Zentrum der Vorderkante 12 der Turbinenschaufel 10 hin diese eine höhere Betriebstemperatur aufweisen als in den Randbereichen der Vorderkante 12. Aus diesem Grund weisen die kegelstumpfförmigen Kühlelemente 18 im mittleren Bereich eine größere Länge auf als in den Randbereichen, da, wie oben dargelegt, durch eine Erhöhung der Länge der Kühlelemente 18 der lokale Wärmeübergangskoeffizient und damit das Kühlvermögen der Kühlelemente 18 erhöht werden kann.2 shows a further sectional illustration of the front section of the turbine blade 10 according to the invention, with a flat sectional surface parallel to the front edge 12. The cooling elements 18 formed on the curved wall surface 16 of the cooling channel 14 extend orthogonally from the curved wall surface 16 into the cooling channel 14 2, in the radial direction R, the length of the cooling elements 18 varies. According to the invention, this counteracts the inhomogeneous temperature distribution which forms along the leading edge 12 when the turbine blade 10 is used. Thus, in particular toward the center of the leading edge 12 of the turbine blade 10, this becomes a higher operating temperature For this reason, the frusto-conical cooling elements 18 have a greater length in the middle region than in the edge regions, since, as stated above, by increasing the length of the cooling elements 18, the local heat transfer coefficient and thus the cooling capacity the cooling elements 18 can be increased.
Die Prallkühlung umfasst vorliegend den Aufprall von aus den Öffnungen 22 austretender Kühlluft auf die gewölbte Wandfläche 16 bzw. die Kühlelemente 18, um dort lokal eine sehr gute Kühlwirkung zu ermöglichen. Da erfindungsgemäß vorgesehen ist, dass die Kühlelemente 18 mit ihrer Längserstreckung auf das Zentrum der Wölbung der Wandfläche 16 ge- richtet sind, kann eine sehr wirksame Prallkühlung bereitgestellt werden, mit der in Verbindung mit der entsprechenden Konvektionskühlung insgesamt eine sehr wirksame Kühlung der Turbinenschaufel 10 bereitgestellt werden kann. Der Kühlkanal 14 ist zu beiden Seiten der Turbinenschaufel 10 geöffnet, um die Kühlluft in zwei Richtungen aus dem Kühlkanal 14 strömen zu lassen. Dadurch wird eine Temperaturharmonisierung der Turbinenschaufel 10 begünstigt, da dort, wo Kühlluft benötigt wird, auch Kühlluft zur Verfügung gestellt wird, und die Wirkung der Prallkühlung nicht durch eine Querströmung reduziert wird.In the present case, the impingement cooling comprises the impact of cooling air emerging from the openings 22 on the arched wall surface 16 or the cooling elements 18 in order to locally enable a very good cooling effect there. Since it is provided according to the invention that the cooling elements 18 are directed with their longitudinal extent to the center of the curvature of the wall surface 16, a very effective impingement cooling can be provided, with which, in conjunction with the corresponding convection cooling, a very effective cooling of the turbine blade 10 is provided can be. The cooling passage 14 is opened on both sides of the turbine blade 10 to flow the cooling air in two directions out of the cooling passage 14. As a result, a temperature harmonization of the turbine blade 10 is favored, since where cooling air is needed, cooling air is also provided, and the effect of the impingement cooling is not reduced by a cross-flow.
Anstelle von kegelstumpfförmigen Gebilden können die Kühlelemente 18 auch rippenförmig ausgebildet sein, die sich entlang des Kühlkanals 14, also in Strömungsrichtung der Kühl- luft erstrecken. Dabei wird die Oberfläche der Wandfläche 16 signifikant erhöht, um die Kühlung der dann vorzugsweise kon- vektiv gekühlten Turbinenschaufel 10 zu verbessern. Dabei ist denkbar, dass die Höhe der Rippen aufgrund der vorgenannten lokal unterschiedlichen Temperaturen an der Vorderkante 12 dazu korrespondierend angepasst sein kann. Instead of frusto-conical structures, the cooling elements 18 may also be formed rib-shaped, which extend along the cooling channel 14, ie in the flow direction of the cooling air. In this case, the surface of the wall surface 16 is significantly increased in order to improve the cooling of the then preferably convectively cooled turbine blade 10. It is conceivable that the height of the ribs due to the aforementioned locally different temperatures at the front edge 12 can be adapted to match.

Claims

Patentansprüche claims
1. Turbinenschaufel (10), mit einem einen Kühlkanal (14) aufweisenden Schaufelblatt und einer sich entlang des Schaufelblatts erstreckendenA turbine blade (10) having an airfoil (14) having an airfoil and extending along the airfoil
Vorderkante (12), wobei der Kühlkanal (14) gegenüber der Vorderkante (12) durch einen Wandabschnitt (24) begrenzt ist, wobei Mittel zum Prallkühlen des Wandabschnittes (24) vorgesehen sind, dadurch gekennzeichnet, dass vom Wandabschnitt (24) ausgehend sich mindestens ein Kühlelement (18) in den Kühlkanal (14) hinein erstreckt und jeweils zapfenförmig oder rippenförmig ausgebildet ist.Leading edge (12), wherein the cooling channel (14) relative to the front edge (12) by a wall portion (24) is limited, wherein means for impact cooling of the wall portion (24) are provided, characterized in that starting from the wall portion (24) at least a cooling element (18) extends into the cooling channel (14) and in each case is designed in the form of a cone or rib.
2. Turbinenschaufel (10) nach Anspruch 1, bei der der Wandabschnitt (24) eine zum Kühlkanal (14) zugewandte Wandfläche (16) aufweist und bei der sich das mindestens eine Kühlelement (18) orthogonal zu der Wandfläche (16) in den Kühlkanal (14) hinein erstreckt.2. turbine blade (10) according to claim 1, wherein the wall portion (24) facing the cooling channel (14) facing wall surface (16) and wherein the at least one cooling element (18) orthogonal to the wall surface (16) in the cooling channel (14) extends into it.
3. Turbinenschaufel (10) nach Anspruch 1 oder 2, bei der der Wandabschnitt (24) eine zum Kühlkanal (14) zugewandte, gewölbte Wandfläche (16) aufweist, bei der zwei oder mehr Kühlelemente (18) vorgesehen sind, bei der die Kühlelemente (18) eine in den Kühlkanal (14) sich hinein erstreckende Längserstreckung aufweisen, und bei der die zwei oder mehr Kühlelemente (18) mit ihrer Längserstreckung auf das Zentrum der Wölbung der Wandfläche (16) gerichtet sind.3. turbine blade (10) according to claim 1 or 2, wherein the wall portion (24) facing the cooling channel (14) facing, curved wall surface (16), in which two or more cooling elements (18) are provided, wherein the cooling elements (18) have a longitudinal extent extending into the cooling channel (14), and in which the two or more cooling elements (18) are directed with their longitudinal extent to the center of the curvature of the wall surface (16).
4. Turbinenschaufel nach einem der vorangehenden Ansprüche, bei der das mindestens eine Kühlelement (18) oder zwei oder mehr Kühlelemente (18) einstückig mit dem Wandabschnitt (24) ausgebildet ist bzw. sind.4. turbine blade according to one of the preceding claims, wherein the at least one cooling element (18) or two or more cooling elements (18) is integrally formed with the wall portion (24) or are.
5. Turbinenschaufel (10) nach einem der vorangehenden Ansprüche, bei der zwei oder mehr Kühlelemente (18) vorgesehen sind, die unterschiedliche Längen aufweisen. 5. turbine blade (10) according to any one of the preceding claims, in which two or more cooling elements (18) are provided which have different lengths.
6. Turbinenschaufel (10) nach Anspruch 5, bei der die Länge der einzelnen Kühlelemente (18) einem vorgegebenen örtlichen Kühlbedarf angepasst ist.6. turbine blade (10) according to claim 5, wherein the length of the individual cooling elements (18) is adapted to a given local cooling demand.
7. Turbinenschaufel (10) nach einem der vorangehenden Ansprüche, bei der sich der Kühlkanal (14) zumindest teilweise parallel zur Vorderkante (12) durchgehend durch die Turbinenschaufel (10) erstreckt.7. turbine blade (10) according to any one of the preceding claims, wherein the cooling channel (14) extends at least partially parallel to the front edge (12) through the turbine blade (10).
8. Turbinenschaufel (10) nach einem der vorangehenden Ansprüche, bei der die Kühlelemente (18) als entlang des Kühlkanals (14) sich erstreckende Rippen oder als entlang des Kühlkanals (14) verteilte Zapfen ausgebildet sind, deren Länge an den lokalen Kühlbedarf angepasst ist.8. turbine blade (10) according to any one of the preceding claims, wherein the cooling elements (18) as along the cooling channel (14) extending ribs or along the cooling channel (14) distributed pins are formed whose length is adapted to the local cooling requirements ,
9. Turbinenschaufel (10) nach einem der vorangehenden Ansprüche, bei der das Mittel zum Prallkühlen des Wandabschnittes (24) eine den Kühlkanal (14) begrenzende, dem Wandabschnitt (24) gegenüberliegende Rückwand (20) ist, in der mehrere Prallkühlöffnungen (22) vorgesehen sind.9. turbine blade (10) according to any one of the preceding claims, wherein the means for impact cooling of the wall portion (24) is a cooling channel (14) bounding the wall portion (24) opposite the rear wall (20), in which a plurality of impingement cooling holes (22). are provided.
10. Turbinenschaufel (10) nach Anspruch 9, bei der die Prallkühlöffnungen (22) derartig angeordnet sind, dass die durch sie hindurchströmende Kühlluftstrahlen auf die Kühlelemente (18) geleitet werden. A turbine blade (10) according to claim 9, wherein the impingement cooling holes (22) are arranged such that the cooling air jets flowing therethrough are directed to the cooling members (18).
EP07820379A 2006-11-08 2007-09-20 Turbine blade Not-in-force EP2087206B1 (en)

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EP06023274A EP1921268A1 (en) 2006-11-08 2006-11-08 Turbine blade
EP07820379A EP2087206B1 (en) 2006-11-08 2007-09-20 Turbine blade
PCT/EP2007/059935 WO2008055737A1 (en) 2006-11-08 2007-09-20 Turbine blade

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EP2087206A1 true EP2087206A1 (en) 2009-08-12
EP2087206B1 EP2087206B1 (en) 2010-03-03

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EP06023274A Withdrawn EP1921268A1 (en) 2006-11-08 2006-11-08 Turbine blade
EP07820379A Not-in-force EP2087206B1 (en) 2006-11-08 2007-09-20 Turbine blade

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EP06023274A Withdrawn EP1921268A1 (en) 2006-11-08 2006-11-08 Turbine blade

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US (1) US8297926B2 (en)
EP (2) EP1921268A1 (en)
JP (2) JP2010509532A (en)
CN (1) CN101535602B (en)
AT (1) ATE459785T1 (en)
DE (1) DE502007003044D1 (en)
WO (1) WO2008055737A1 (en)

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US10364684B2 (en) 2014-05-29 2019-07-30 General Electric Company Fastback vorticor pin
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US9850762B2 (en) 2013-03-13 2017-12-26 General Electric Company Dust mitigation for turbine blade tip turns
US10364684B2 (en) 2014-05-29 2019-07-30 General Electric Company Fastback vorticor pin
US10422235B2 (en) 2014-05-29 2019-09-24 General Electric Company Angled impingement inserts with cooling features
US10280785B2 (en) 2014-10-31 2019-05-07 General Electric Company Shroud assembly for a turbine engine

Also Published As

Publication number Publication date
JP2012137089A (en) 2012-07-19
CN101535602A (en) 2009-09-16
EP1921268A1 (en) 2008-05-14
DE502007003044D1 (en) 2010-04-15
EP2087206B1 (en) 2010-03-03
CN101535602B (en) 2012-01-11
ATE459785T1 (en) 2010-03-15
US8297926B2 (en) 2012-10-30
JP5269223B2 (en) 2013-08-21
US20100143153A1 (en) 2010-06-10
WO2008055737A1 (en) 2008-05-15
JP2010509532A (en) 2010-03-25

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