EP1219781A2 - Device and method to cool a platform of a turbine blade - Google Patents
Device and method to cool a platform of a turbine blade Download PDFInfo
- Publication number
- EP1219781A2 EP1219781A2 EP01128807A EP01128807A EP1219781A2 EP 1219781 A2 EP1219781 A2 EP 1219781A2 EP 01128807 A EP01128807 A EP 01128807A EP 01128807 A EP01128807 A EP 01128807A EP 1219781 A2 EP1219781 A2 EP 1219781A2
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- EP
- European Patent Office
- Prior art keywords
- platform
- cooling
- blade
- outlet
- turbine blade
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Classifications
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- 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
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- 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
- F01D5/186—Film cooling
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- 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
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2240/00—Components
- F05B2240/80—Platforms for stationary or moving blades
- F05B2240/801—Platforms for stationary or moving blades cooled platforms
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- 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
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
Definitions
- the invention relates to a device and a method for cooling A platform of a turbine blade, which has a blade root, an airfoil a leading and trailing edge and a blade tip with a platform and which is at least partially penetrated radially by at least one cooling channel, the one with at least one emerging from the platform via an outlet opening Exit channel is connected.
- Cooling problems of the type mentioned above occur in particular Turbine blades that are used in gas turbine plants.
- the turbine blades are separated from the inside flows around the combustion chamber generated hot gases.
- Avoiding existing turbine blades plays the aspect of targeted cooling of gas turbine blades in the conception and design of such systems a major role.
- part of the cooling within the Compressor stage specifically derived and thus compressed air for cooling purposes withdrawn from the further combustion process. Rather, the cooling air passes over Cooling channel systems, both in rotating and stationary Plant components are provided in the area of the turbine stages around the there to cool the system components directly exposed to the hot gases.
- Cooling of the rotor assembly in a variety of axially one behind the other arranged rows of moving blades, have the Blades radial cooling channels through which from the side of the rotor assembly Cooling air fed in is guided longitudinally to the turbine blades, which are passed through cooling air openings correspondingly provided on the blade surface emerge and mixes with the hot gases.
- turbine blades point radially to the rotor assembly facing side platforms or so-called shrouds to Leakage flows between the turbine blade tips and the to train fixed system components.
- platforms and shrouds contribute to vibrations that occur train along the turbine blades during operation of the gas turbine, dampen effectively.
- a cooling duct system is used in US 5,482,435 for cooling such platforms described within a platform through which cooling air is conducted and thus effectively contributes to cooling the platform.
- the cooling air passes through a central cooling channel oriented radially to the turbine blade in the area of the platform, in which the cooling air escapes through two sub-channels.
- the one in the platform The partial cooling ducts provided extend in such a way that those from the platform emerging cooling air almost perpendicular to the main flow direction of the Gas turbine flowing hot gases is oriented. However, on the one hand, this causes that the flow behavior of the main flow is considerably irritated, causing the aerodynamic efficiency is permanently impaired.
- the cooling air emerging from the platform makes no contribution to the energy gain or contribute to improved energy conversion within the gas turbine.
- the invention has for its object a device and a method for Cooling a platform of a turbine blade according to the preamble of Claim 1 to develop such that, on the one hand, effective cooling of the Platform is ensured, but on the other hand it is ensured that the Main flow, which lies directly on the turbine blade, as little as possible is affected to the aerodynamic conditions within the Fluid machine not to deteriorate. Rather, it should be achieved that in addition to the above effective cooling effect, an additional energy gain can be achieved by the exit of the cooling air from the platform.
- a device for cooling a platform is a Turbine blade, which has a blade root, a blade with an attachment and Trailing edge, as well as a blade tip with a platform and the radial is at least partially penetrated by at least one cooling channel, which with at least one exiting the platform via an outlet opening Outlet channel is connected, further developed in that the outlet channel has a longitudinal channel direction adjacent to the outlet opening, which is in projection along the turbine blade largely coparallel to the direction of flow of a Exit flow immediately overflowing local flow field of a relative mass flow flowing past the turbine blade.
- the cooling device according to the invention is on all turbine blades applicable, which are provided with a platform.
- the with the invention The advantages associated with the measure are shown below using the example of Turbine guide vane explained in more detail within a gas turbine system. Of course, however, it is possible to use the cooling device according to the invention also to be used on platforms of stationary guide vanes.
- the Measure according to the invention is not based on the use of turbine blades limited within gas turbine stages of gas turbine plants, but can be used in all turbomachines in which corresponding Cooling problems occur, for example within compressors or the like Turbomachinery.
- the inventive arrangement of the outlet channel within the platform, by the cooling air exits through an outlet opening is oriented according to the invention in such a way so the cooling air that flows out of the platform is preferably the same Has flow direction with which the main flow of hot gases Turbine blade and thus also flows around the platform itself.
- the Outlet opening of the outlet channel on the turbine blade radially provided facing away from the top of the platform preferably runs the Cooling duct inclined slightly to the top of the platform.
- the Outlet opening attached to the downstream edge of the platform be so that the cooling air flowing out of the platform is coparallel to the die Hot gases flowing around the platform is oriented.
- there is Outlet opening of the cooling channel on the platform preferably downstream Leading edge of the turbine blade so that it is guaranteed that one is possible long cooling channel section runs within the platform, so that one if possible effective cooling effect can be achieved.
- Cooling arrangements within the platform which in the case of Turbine blades due to their radial spacing from the axis of rotation subjected to high centrifugal forces make an important contribution to the creep behavior of the blade material in the area of the platform increases positively influence, i.e. Material warping or deformation by softening the Materials under the influence of high centrifugal forces are effective cooling measures reduced or eliminated.
- Through the Cooling measure according to the invention within the platform can creep material be significantly restricted.
- the main advantage associated with this is the additional energy gain that comes with the targeted coparallel flow exit of the cooling air relative to the turbine blade mainstream flowing around, can be achieved. So it could be proven be that the cooling air coming from the cooling duct oriented according to the invention flows out through the outlet opening on the platform to a measurable Contributes to energy gain, which is characterized by the interaction of an additional Impulse contribution to the drive of the turbine blade and one comparatively negligible irritation or disturbance of the main flow of the Turbine blade flows around hot gases.
- a plurality of appropriately oriented cooling channels are preferred introduced within a platform, whereby the above described beneficial effects in terms of cooling effect and additional energy contribution let increase. Further details regarding possible exemplary embodiments can be found can be found in detail in the following exemplary embodiments.
- A are suitable for producing the platform designed according to the invention
- a variety of known techniques around the cooling channel or a variety bring appropriately oriented cooling channels into the platform.
- EDM processes Electro-Discharge Machining
- laser beam laser beam
- electrochemical Processes electrochemical Processes
- water jet techniques water jet techniques
- Figure 1 is a plan view of an axial arrangement consisting of a Guide vane row 1 and one downstream in the flow direction Blade row 2 shown.
- the platforms 3 are one Guide vane 4 and a moving blade 5 can be seen, the guide vane 4 or blade 5 facing away from the viewer perpendicular to the plane of the drawing extends.
- the main flow 6 through the turbine blades from the pure Redirected axial direction. So is the main flow 6 immediately after flowing through the guide vane row 1 directed upward in the circumferential direction, whereas the Main flow after flow around the blade row 2 against the direction of rotation is distracted.
- the inclination of the flow direction in relation to the axial direction becomes immediately downstream of a turbine blade row essentially due to the inclination the turbine blades relative to the main flow and the Circumferential speed conditional.
- the platforms 3 there are cooling channels 7, preferably in the region of the downstream end edge 8 of the platforms 3 arranged such that cooling air parallel to the main flow 6 from the Cooling channels 7 escapes.
- the longitudinal axes of the cooling channels 7 are parallel to Turbine airfoil in the area immediately upstream of the trailing edge 9 arranged.
- FIG 2 is the upper part of a longitudinal section through a turbine blade shown, which is designed for example as a rotor blade 5 and in its upper Area provides a platform 3.
- the rotor blade 5 has a radial direction extending main cooling duct 10, in the cooling air on the part of the shown blade root in the area of the platform 3.
- the main cooling channel 10 opens on one side a plurality of cooling channels 11, which are inclined run to the platform top 12 and there is an outlet opening 13 there provide. Cooling air through the outlet channels 11 through the respective Exit opening 13 on the platform top 3 exits is slightly oblique to Platform top 12, however, directed in the flow direction of the main flow 6.
- Further cooling channels 14 open out via corresponding further outlet openings the platform top and are appropriately provided through additional Cooling air channels 15 supplied with cooling air.
- the platform 3 of the moving blade 5 shown in FIG. 2 typically sees one trained labyrinth seal 16 before, directly below the cooling channel volume 17 with corresponding downstream outlet 18 is provided.
- FIG. 3 shows a top view of a platform 3, under which, in Extending in the longitudinal direction, a moving blade 5 is provided.
- the blade 5 has various hollow channels extending along the turbine blade, from which flows out of the hollow duct 10 cooling air in the direction of the platform.
- Immediately at the hollow channel 10 formed as a cooling channel includes Cooling air system through which the individual cooling channels 13 and 14 with appropriate cooling air is supplied. The cooling air flows along the individual Channels indicated arrow directions and occurs at the corresponding Exit openings 13, 14 on the top 12 of the platform 3.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Die Erfindung bezieht sich auf eine Vorrichtung sowie ein Verfahren zur Kühlung einer Plattform einer Turbinenschaufel, die einen Schaufelfuß, ein Schaufelblatt mit einer An- und Abströmkante sowie eine Schaufelspitze mit einer Plattform vorsieht und die radial von wenigstens einem Kühlkanal wenigstens teilweise durchsetzt ist, der mit wenigstens einem, über eine Austrittsöffnung an der Plattform austretenden Austrittskanal verbunden ist.The invention relates to a device and a method for cooling A platform of a turbine blade, which has a blade root, an airfoil a leading and trailing edge and a blade tip with a platform and which is at least partially penetrated radially by at least one cooling channel, the one with at least one emerging from the platform via an outlet opening Exit channel is connected.
Kühlprobleme der vorstehend genannten Art treten insbesondere bei Turbinenschaufeln auf, die in Gasturbinenanlagen eingesetzt werden. Insbesondere in den einzelnen Gasturbinenstufen werden die Turbinenschaufeln von den innerhalb der Brennkammer erzeugten Heißgasen umströmt. Um Überhitzungen bei in Betrieb befindlichen Turbinenschaufeln zu vermeiden spielt der Aspekt der gezielten Kühlung von Gasturbinenschaufeln bei der Konzeption und Auslegung derartiger Anlagen eine große Rolle. Üblicherweise wird zur Kühlung ein Teil der innerhalb der Verdichterstufe vorkomprimierten Luft zu Kühlzwecken gezielt abgeleitet und somit dem weiteren Verbrennungsvorgang entzogen. Vielmehr gelangt die Kühlluft über Kühlkanalsysteme, die sowohl in rotierenden als auch stationären Anlagenkomponenten vorgesehen sind, in den Bereich der Turbinenstufen um die dort, den Heißgasen unmittelbar ausgesetzten Anlagenkomponenten zu kühlen. Zur Kühlung der auf der Rotoranordnung, in einer Vielzahl von axial hintereinander angeordneten Laufschaufelreihen aufsitzenden Laufschaufeln, weisen die Laufschaufeln radiale Kühlkanäle auf, durch die von Seiten der Rotoranordnung eingespeiste Kühlluft längs zu den Turbinenschaufelblättern geführt wird, die durch entsprechend an der Laufschaufeloberfläche vorgesehene Kühlluftöffnungen austritt und sich mit den Heißgasen vermischt.Cooling problems of the type mentioned above occur in particular Turbine blades that are used in gas turbine plants. In particular In the individual gas turbine stages, the turbine blades are separated from the inside flows around the combustion chamber generated hot gases. To prevent overheating when in operation Avoiding existing turbine blades plays the aspect of targeted cooling of gas turbine blades in the conception and design of such systems a major role. Usually, part of the cooling within the Compressor stage specifically derived and thus compressed air for cooling purposes withdrawn from the further combustion process. Rather, the cooling air passes over Cooling channel systems, both in rotating and stationary Plant components are provided in the area of the turbine stages around the there to cool the system components directly exposed to the hot gases. to Cooling of the rotor assembly, in a variety of axially one behind the other arranged rows of moving blades, have the Blades radial cooling channels through which from the side of the rotor assembly Cooling air fed in is guided longitudinally to the turbine blades, which are passed through cooling air openings correspondingly provided on the blade surface emerge and mixes with the hot gases.
In einigen Fällen weisen Turbinenschaufeln an ihrer radial, der Rotoranordnung abgewandten Seite Plattformen oder sogenannte Deckbänder auf, um Leckageströme, die sich zwischen den Turbinenschaufelspitzen und den feststehenden Anlagenkomponenten ausbilden können, zu minimieren. Ebenso tragen derartige Plattformen und Deckbänder dazu bei, Vibrationen, die sich während des Betriebes der Gasturbine entlang der Turbinenschaufeln ausbilden, effektiv zu dämpfen.In some cases, turbine blades point radially to the rotor assembly facing side platforms or so-called shrouds to Leakage flows between the turbine blade tips and the to train fixed system components. As well such platforms and shrouds contribute to vibrations that occur train along the turbine blades during operation of the gas turbine, dampen effectively.
Zur Kühlung derartiger Plattformen ist in der US 5,482,435 ein Kühlkanalsystem innerhalb einer Plattform beschrieben, durch das Kühlluft, geleitet wird und somit wirksam zur Kühlung der Plattform beiträgt. Die Kühlluft gelangt über einen mittig, radialwärts zur Turbinenschaufel orientierten Kühlkanal in den Bereich der Plattform, in dem die Kühlluft über zwei Teilkanäle nach außen gelangt. Die in der Plattform vorgesehenen Teilkühlkanäle erstrecken sich derart, dass die aus der Plattform austretende Kühlluft nahezu senkrecht zur Hauptströmungsrichtung der die Gasturbine durchströmenden Heißgase orientiert ist. Dies jedoch bewirkt einerseits, dass das Strömungsverhalten der Hauptströmung erheblich irritiert wird, wodurch der aerodynamische Wirkungsgrad nachhaltig beeinträchtigt wird. Zum anderen vermag die aus der Plattform austretende Kühlluft keinen Beitrag zum Energiegewinn bzw. zur verbesserten Energieumsetzung innerhalb der Gasturbine beitragen.A cooling duct system is used in US 5,482,435 for cooling such platforms described within a platform through which cooling air is conducted and thus effectively contributes to cooling the platform. The cooling air passes through a central cooling channel oriented radially to the turbine blade in the area of the platform, in which the cooling air escapes through two sub-channels. The one in the platform The partial cooling ducts provided extend in such a way that those from the platform emerging cooling air almost perpendicular to the main flow direction of the Gas turbine flowing hot gases is oriented. However, on the one hand, this causes that the flow behavior of the main flow is considerably irritated, causing the aerodynamic efficiency is permanently impaired. On the other hand, the cooling air emerging from the platform makes no contribution to the energy gain or contribute to improved energy conversion within the gas turbine.
Der Erfindung liegt die Aufgabe zugrunde, eine Vorrichtung sowie ein Verfahren zur Kühlung einer Plattform einer Turbinenschaufel gemäß dem Oberbegriff des Anspruchs 1 derart weiterzubilden, so dass zum einen eine effektive Kühlung der Plattform sichergestellt ist, zum anderen jedoch dafür gesorgt ist, dass die Hauptströmung, die unmittelbar an der Turbinenschaufel anliegt, möglichst wenig beeinträchtigt wird, um die aerodynamischen Verhältnisse innerhalb der Strömungsmaschine nicht zu verschlechtern. Vielmehr soll erreicht werden, dass neben der vorstehenden effektiven Kühlwirkung ein zusätzlicher Energiegewinn durch den Austritt der Kühlluft aus der Plattform erzielt werden kann.The invention has for its object a device and a method for Cooling a platform of a turbine blade according to the preamble of Claim 1 to develop such that, on the one hand, effective cooling of the Platform is ensured, but on the other hand it is ensured that the Main flow, which lies directly on the turbine blade, as little as possible is affected to the aerodynamic conditions within the Fluid machine not to deteriorate. Rather, it should be achieved that in addition to the above effective cooling effect, an additional energy gain can be achieved by the exit of the cooling air from the platform.
Die Lösung der der Erfindung zugrundeliegende Aufgabe ist im Anspruch 1
angegeben, der eine erfindungsgemäße Vorrichtung beschreibt. Gegenstand des
Anspruchs 8 ist ein erfindungsgemäßes Verfahren. Den Erfindungsgedanken
vorteilhaft weiterbildende Merkmale sind Gegenstand der Unteransprüche sowie der
gesamten Beschreibung insbesondere unter Bezugnahme auf die
Ausführungsbeispiele zu entnehmen.The object underlying the invention is achieved in claim 1
specified that describes a device according to the invention. Subject of
Erfindungsgemäß ist eine Vorrichtung zur Kühlung einer Plattform einer Turbinenschaufel, die einen Schaufelfuß, ein Schaufelblatt mit einer An- und Abströmkante, sowie eine Schaufelspitze mit einer Plattform vorsieht und die radial von wenigstens einem Kühlkanal wenigstens teilweise durchsetzt ist, der mit wenigstens einem, über eine Austrittsöffnung an der Plattform austretenden Austrittskanal verbunden ist, dadurch weitergebildet, dass der Austrittskanal angrenzend zur Austrittsöffnung eine Kanallängsrichtung aufweist, die in Projektion längs zur Turbinenschaufel weitgehend koparallel zur Strömungsrichtung eines die Austrittsöffnung unmittelbar überströmenden, lokalen Strömungsfeldes eines relativ an der Turbinenschaufel vorbeiströmenden Massenflusses verläuft.According to the invention, a device for cooling a platform is a Turbine blade, which has a blade root, a blade with an attachment and Trailing edge, as well as a blade tip with a platform and the radial is at least partially penetrated by at least one cooling channel, which with at least one exiting the platform via an outlet opening Outlet channel is connected, further developed in that the outlet channel has a longitudinal channel direction adjacent to the outlet opening, which is in projection along the turbine blade largely coparallel to the direction of flow of a Exit flow immediately overflowing local flow field of a relative mass flow flowing past the turbine blade.
Grundsätzlich ist die erfindungsgemäße Kühlvorrichtung an allen Turbinenschaufeln anwendbar, die mit einer Plattform versehen sind. Die mit der erfindungsgemäßen Maßnahme verbundenen Vorteile werden nachfolgend am Beispiel der Turbinenleitschaufel innerhalb einer Gasturbinenanlage näher erläutert. Selbstverständlich ist es jedoch möglich, die erfindungsgemäße Kühlvorrichtung auch an Plattformen von stationären Leitschaufeln einzusetzen. Die erfindungsgemäße Maßnahme ist nicht auf den Einsatz von Turbinenschaufeln innerhalb von Gasturbinenstufen von Gasturbinenanlagen beschränkt, sondern kann in allen Strömungsmaschinen angewendet werden, in denen entsprechende Kühlprobleme auftreten, beispielsweise innerhalb von Kompressoren oder ähnlichen Strömungsmaschinen.Basically, the cooling device according to the invention is on all turbine blades applicable, which are provided with a platform. The with the invention The advantages associated with the measure are shown below using the example of Turbine guide vane explained in more detail within a gas turbine system. Of course, however, it is possible to use the cooling device according to the invention also to be used on platforms of stationary guide vanes. The Measure according to the invention is not based on the use of turbine blades limited within gas turbine stages of gas turbine plants, but can be used in all turbomachines in which corresponding Cooling problems occur, for example within compressors or the like Turbomachinery.
Die erfindungsgemäße Anordnung des Austrittskanals innerhalb der Plattform, durch den Kühlluft durch eine Austrittsöffnung austritt, ist erfindungsgemäß derart orientiert, so dass die Kühlluft, die aus der Plattform ausströmt vorzugsweise die gleiche Strömungsrichtung besitzt, mit der die Hauptströmung der Heißgase die Turbinenschaufel und somit auch die Plattform selbst umströmt. Ist die Austrittsöffnung des Austrittskanals an der dem Turbinenschaufelblatt radial abgewandten Plattformoberseite vorgesehen, so verläuft vorzugsweise der Kühlkanal leicht schräg geneigt zur Plattformoberseite. Alternativ kann die Austrittsöffnung an der stromabgewandten Abschlusskante der Plattform angebracht sein, so dass die aus der Plattform ausströmende Kühlluft koparallel zu den die Plattform umströmende Heißgase orientiert ist. In allen Fällen befindet sich die Austrittsöffnung des Kühlkanals an der Plattform vorzugsweise stromab zur Anströmkante der Turbinenschaufel, so das gewährleistet ist, dass ein möglichst langer Kühlkanalabschnitt innerhalb der Plattform verläuft, so dass eine möglichst effektive Kühlwirkung erzielt werden kann.The inventive arrangement of the outlet channel within the platform, by the cooling air exits through an outlet opening is oriented according to the invention in such a way so the cooling air that flows out of the platform is preferably the same Has flow direction with which the main flow of hot gases Turbine blade and thus also flows around the platform itself. Is the Outlet opening of the outlet channel on the turbine blade radially provided facing away from the top of the platform, preferably runs the Cooling duct inclined slightly to the top of the platform. Alternatively, the Outlet opening attached to the downstream edge of the platform be so that the cooling air flowing out of the platform is coparallel to the die Hot gases flowing around the platform is oriented. In all cases there is Outlet opening of the cooling channel on the platform preferably downstream Leading edge of the turbine blade so that it is guaranteed that one is possible long cooling channel section runs within the platform, so that one if possible effective cooling effect can be achieved.
Kühlungvorkehrungen innerhalb der Plattform, die im Falle von Turbinenlaufschaufeln aufgrund ihrer radialen Beabstandung zur Rotationsachse hohen Zentrifugalkräften unterworfen ist, tragen einen wichtigen Beitrag dazu bei, das Kriechverhalten des Schaufelmaterials im Bereich der Plattform positiv zu beeinflussen, d.h. Materialverwerfungen- bzw. deformationen durch Erweichen des Materials unter gleichzeitiger Einwirkung hoher Zentrifugalkräfte werden durch wirkungsvolle Kühlmaßnahmen reduziert bzw. eliminiert. Durch die erfindungsgemäße Kühlmaßnahme innerhalb der Plattform kann Materialkriechen erheblich eingeschränkt werden.Cooling arrangements within the platform, which in the case of Turbine blades due to their radial spacing from the axis of rotation subjected to high centrifugal forces make an important contribution to the creep behavior of the blade material in the area of the platform increases positively influence, i.e. Material warping or deformation by softening the Materials under the influence of high centrifugal forces are effective cooling measures reduced or eliminated. Through the Cooling measure according to the invention within the platform can creep material be significantly restricted.
Der mit dem erfindungsgemäßen Kühlkanalsystem innerhalb der Plattform verbundene Hauptvorteil ist jedoch der zusätzliche Energiegewinn, der mit dem gezielten koparallelen Strömungsaustritt der Kühlluft relativ zur, die Turbinenschaufel umströmenden Hauptströmung, erzielt werden kann. So konnte nachgewiesen werden, dass die Kühlluft, die aus dem erfindungsgemäß orientierten Kühlkanal durch die Austrittsöffnung an der Plattform ausströmt, zu einem messbaren Energiegewinn beiträgt, der sich durch das Zusammenspiel eines zusätzlichen Impulsbeitrages zum Antrieb der Turbinenschaufel und einer vergleichsweise vernachlässigbaren Irritation bzw. Störung der Hauptströmung der die Turbinenschaufel umströmenden Heißgase ergibt.The one with the cooling channel system according to the invention within the platform However, the main advantage associated with this is the additional energy gain that comes with the targeted coparallel flow exit of the cooling air relative to the turbine blade mainstream flowing around, can be achieved. So it could be proven be that the cooling air coming from the cooling duct oriented according to the invention flows out through the outlet opening on the platform to a measurable Contributes to energy gain, which is characterized by the interaction of an additional Impulse contribution to the drive of the turbine blade and one comparatively negligible irritation or disturbance of the main flow of the Turbine blade flows around hot gases.
Vorzugsweise sind eine Vielzahl von entsprechend orientierten Kühlkanälen innerhalb einer Plattform eingebracht, wodurch sich die vorstehend beschriebenen vorteilhaften Auswirkungen bezüglich Kühlwirkung und zusätzlichen Energiebeitrag steigern lassen. Weitere Details bezüglich möglicher Ausführungsbeispiele können den nachstehenden Ausführungsbeispielen detailliert entnommen werden.A plurality of appropriately oriented cooling channels are preferred introduced within a platform, whereby the above described beneficial effects in terms of cooling effect and additional energy contribution let increase. Further details regarding possible exemplary embodiments can be found can be found in detail in the following exemplary embodiments.
Zur Herstellung der erfindungsgemäß ausgebildeten Plattform eignen sich eine Vielzahl an sich bekannter Techniken um den Kühlkanal bzw. eine Vielzahl entsprechend orientierter Kühlkanäle in die Plattform einzubringen. Besonders eignen sich hierzu EDM-Verfahren (Electro-Discharge-Machining) oder auch konventionelle Bohrtechniken, unter Einsatz von Laserstrahl, elektrochemischen Verfahren sowie Wasserstrahltechniken.A are suitable for producing the platform designed according to the invention A variety of known techniques around the cooling channel or a variety bring appropriately oriented cooling channels into the platform. Especially EDM processes (Electro-Discharge Machining) are suitable for this or also conventional drilling techniques, using laser beam, electrochemical Processes and water jet techniques.
Selbstverständlich ist es auch möglich, Plattformen von Turbinenschaufeln an ihren jeweiligen Turbinenschaufelfüßen mit entsprechend orientierten Kühlkanälen zu versehen. Gleichwohl der Aspekt des zusätzlichen Energiegewinns bei Plattformen im Schaufelfußbereich eine nur untergeordnete Rolle spielt, beeinträchtigt die ausströmende Kühlluft durch die entsprechenden Austrittsöffnungen die Hauptströmung auch im Bereich der Schaufelfüße nicht bzw. nur unwesentlich.Of course, it is also possible to attach turbine blades to their platforms respective turbine blade feet with appropriately oriented cooling channels Mistake. Nevertheless, the aspect of additional energy gain from platforms plays only a minor role in the blade root area, affects the outflowing cooling air through the corresponding outlet openings Main flow in the area of the blade roots either not or only insignificantly.
Die Erfindung wird nachstehend ohne Beschränkung des allgemeinen Erfindungsgedankens anhand von Ausführungsbeispielen unter Bezugnahme auf die Zeichnung exemplarisch beschrieben. Es zeigen:
- Fig. 1
- Draufsicht auf die axiale Anordnung einer in einer Laufschaufelreihe angeordnete Turbinenlaufschaufel sowie einer entsprechend axial stromauf angeordneten Turbinenleitschaufel,
- Fig. 2
- Teildarstellung durch einen radialen Längsschnitt durch eine Turbinenschaufel mit Plattform sowie
- Fig. 3
- Draufsicht auf eine Plattform in radialer Richtung.
- Fig. 1
- Top view of the axial arrangement of a turbine blade arranged in a row of rotor blades and of a turbine guide blade arranged accordingly axially upstream,
- Fig. 2
- Partial representation through a radial longitudinal section through a turbine blade with platform and
- Fig. 3
- Top view of a platform in the radial direction.
In Figur 1 ist eine Draufsicht auf eine axiale Anordnung, bestehend aus einer
Leitschaufelreihe 1 und einer in Strömungsrichtung nachgeordneten
Laufschaufelreihe 2 dargestellt. Im einzelnen sind die Plattformen 3 einer
Leitschaufel 4 sowie einer Laufschaufel 5 zu sehen, wobei sich die Leitschaufel 4
bzw. Laufschaufel 5 senkrecht längs zur Zeichenebene vom Betrachter abgewandt
erstreckt. Durch die entsprechende Anstellung der Leit- bzw. Laufschaufeln relativ
zur Hauptströmung 6, die die Turbinenschaufelanordnung axialwärts durchströmt,
wird die Hauptströmung 6 durch die Turbinenschaufelblätter aus der reinen
Axialrichtung umgelenkt. So ist die Hauptströmung 6 unmittelbar nach Durchströmen
der Leitschaufelreihe 1 in der Umfangsrichtung nach oben gerichtet, wohingegen die
Hauptströmung nach Umströmen der Laufschaufelreihe 2 entgegen der Drehrichtung
abgelenkt wird. Die Neigung der Strömungsrichtung bezogen zur Axialrichtung wird
unmittelbar stromab einer Turbinenschaufelreihe im Wesentlichen durch die Neigung
der Turbinenschaufelblätter relativ zur Hauptströmung und der
Umfangsgeschwindigkeit bedingt. Zur Kühlung der Plattformen 3 sind Kühlkanäle 7,
vorzugsweise im Bereich der stromab gerichteten Endkante 8 der Plattformen 3
derart angeordnet, so dass Kühlluft parallel zur Hauptströmung 6 aus den
Kühlkanälen 7 entweicht. Hierzu sind die Längsachsen der Kühlkanäle 7 parallel zum
Turbinenschaufelblatt im Bereich unmittelbar stromauf zur Abströmkante 9
angeordnet.In Figure 1 is a plan view of an axial arrangement consisting of a
Guide vane row 1 and one downstream in the flow direction
Blade row 2 shown. In detail, the
In Figur 2 ist der obere Teil eines Längsschnittes durch eine Turbinenschaufel
dargestellt, die beispielsweise als Laufschaufel 5 ausgebildet ist und in ihrem oberen
Bereich eine Plattform 3 vorsieht. Die Laufschaufel 5 weist einen sich radialwärts
erstreckenden Hauptkühlkanal 10 auf, in dem Kühlluft von Seiten des nicht
dargestellten Laufschaufelfußes in den Bereich der Plattform 3 gelangt. In den
Hauptkühlkanal 10 münden einseitig eine Vielzahl von Kühlkanälen 11, die schräg
zur Plattformoberseite 12 verlaufen und an dieser jeweils eine Austrittsöffnung 13
vorsehen. Kühlluft, die durch die Austrittskanäle 11 durch die jeweilige
Austrittsöffnung 13 an der Plattformoberseite 3 austritt, ist leicht schräg zur
Plattformoberseite 12 jedoch in Strömungsrichtung der Hauptströmung 6 gerichtet.
Weitere Kühlkanäle 14 münden über entsprechende weitere Austrittsöffnungen an
der Plattformoberseite und werden über geeignet vorgesehene zusätzliche
Kühlluftkanäle 15 mit Kühlluft versorgt.In Figure 2 is the upper part of a longitudinal section through a turbine blade
shown, which is designed for example as a
Die Plattform 3 der in Figur 2 dargestellten Laufschaufel 5 sieht eine typischerweise
ausgebildete Labyrinthdichtung 16 vor, unter der unmittelbar ein Kühlkanalvolumen
17 mit entsprechend stromabwärts gerichteten Auslass 18 vorgesehen ist.The
In Figur 3 ist eine Draufsicht auf eine Plattform 3 dargestellt, unter der, sich in
Längsrichtung erstreckend, eine Laufschaufel 5 vorgesehen ist. Die Laufschaufel 5
weist diverse, sich längs zur Turbinenschaufel erstreckende Hohlkanäle auf, von
denen aus dem Hohlkanal 10 Kühlluft in Richtung der Plattform ausströmt.
Unmittelbar an den als Kühlkanal ausgebildeten Hohlkanal 10 schließt sich ein
Kühlluftsystem an, durch das die einzelnen Kühlkanäle 13 und 14 mit
entsprechender Kühlluft versorgt wird. Die Kühlluft strömt längs der in den einzelnen
Kanälen angegebenen Pfeilrichtungen und tritt an den entsprechenden
Austrittsöffnungen 13, 14 an der Oberseite 12 der Plattform 3 aus. FIG. 3 shows a top view of a
- 11
- Leitschaufelreihevane row
- 22
- LaufschaufelreiheBlade row
- 33
- Plattformplatform
- 44
- Leitschaufelvane
- 55
- Laufschaufelblade
- 66
- Hauptströmungmainstream
- 77
- Kühlkanälecooling channels
- 88th
-
stromabgewandtes Ende der Plattform 3downstream end of the
platform 3 - 99
- Abströmkantetrailing edge
- 1010
- HauptkühlkanalMain cooling channel
- 1111
- Kühlkanalcooling channel
- 1212
- PlattformoberseitePlatform top
- 1313
- Austrittsöffnungoutlet opening
- 1414
- Austrittsöffnungoutlet opening
- 1515
- NebenkühlkanalBesides cooling channel
- 1616
- Labyrinthdichtunglabyrinth seal
- 1717
- KühlkanalvolumenCooling channel volume
- 1818
- Auslasskanalexhaust port
Claims (8)
dadurch gekennzeichnet, dass der Austrittskanal (7,11) angrenzend zur Austrittsöffnung (13) eine Kanallängsrichtung aufweist, die in Projektion längs zur Turbinenschaufel weitgehend koparallel zur Strömungsrichtung eines die Austrittsöffnung unmittelbar überströmenden, lokalen Strömungsfeldes (6) eines relativ an der Turbinenschaufel vorbeiströmenden Massenflusses verläuft.Device for cooling a platform (3) of a turbine blade, which provides a blade root, an airfoil with a leading and trailing edge, and a blade tip with a platform (3) and which is at least partially penetrated radially by at least one cooling channel which is provided with at least one , is connected via an outlet opening on the platform outlet outlet,
characterized in that the outlet duct (7, 11) adjacent to the outlet opening (13) has a longitudinal duct direction which, when projected along the turbine blade, runs largely coparallel to the flow direction of a local flow field (6) directly flowing over the outlet opening and of a mass flow flowing relatively past the turbine blade ,
dadurch gekennzeichnet, dass der Austrittskanal (7,11) angrenzend zur Austrittsöffnung (13) eine Kanallängsrichtung aufweist, die in Projektion längs zur Turbinenschaufel weitgehend koparallel zum Axialschnitt des Turbinenschaufelblattes im Bereich unmittelbar stromauf zur Abströmkante verläuft.Device according to claim 1,
characterized in that the outlet duct (7, 11) adjacent to the outlet opening (13) has a longitudinal duct direction which, when projected along the turbine blade, is largely coparallel to the axial section of the turbine blade in the region immediately upstream of the trailing edge.
dadurch gekennzeichnet, dass durch den Austrittskanal (7,11) ein Kühlmedium, vorzugweise Kühlluft, strömbar ist, das die Austrittsöffnung (13) nahezu in Strömungsrichtung zum lokalen Strömungsfeld (6) verläßt.Device according to claim 1 or 2,
characterized in that a cooling medium, preferably cooling air, can flow through the outlet channel (7, 11) and leaves the outlet opening (13) almost in the direction of flow to the local flow field (6).
dadurch gekennzeichnet, dass die Turbinenschaufel in einer Strömungsmaschine, vorzugsweise in einer Gasturbine, integriert ist, durch die der Massenfluss axial hindurchgerichtet ist. Device according to one of claims 1 to 3,
characterized in that the turbine blade is integrated in a turbomachine, preferably in a gas turbine, through which the mass flow is directed axially.
dadurch gekennzeichnet, dass die Austrittsöffnung (13) nahe dem stromabgewandten Ende der Plattform (3) angeordnet ist.Device according to one of claims 1 to 4,
characterized in that the outlet opening (13) is arranged near the downstream end of the platform (3).
dadurch gekennzeichnet, dass die Plattform (3) eine dem Turbinenschaufelblatt radial abgewandte Plattformoberseite (12) aufweist, an der die Austrittsöffnung (13) vorgesehen ist.Device according to one of claims 1 to 5,
characterized in that the platform (3) has a platform upper side (12) radially facing away from the turbine airfoil, on which the outlet opening (13) is provided.
dadurch gekennzeichnet, dass die Turbinenschaufel eine Leit- vorzugsweise eine Laufschaufel innerhalb einer Gasturbine ist.Device according to one of claims 1 to 6,
characterized in that the turbine blade is a guide blade, preferably a moving blade, within a gas turbine.
dadurch gekennzeichnet, dass ein Kühlmedium, vorzugsweise Kühlluft durch den Kühlkanal und den Austrittskanal derart hindurchgeleitet wird und aus der Plattform austritt, dass das Kühlmedium nahezu strömungsparallel in Richtung zu einem die Turbinenschaufel umströmenden Massenstrom die Plattform verlässt.Method for cooling a platform of a turbine blade, which provides a blade root, an airfoil with a leading and trailing edge, and a blade tip with a platform and which is at least partially penetrated radially by at least one cooling channel which is connected to at least one via an outlet opening at the Platform emerging outlet channel is connected
characterized in that a cooling medium, preferably cooling air, is passed through the cooling duct and the outlet duct and exits the platform such that the cooling medium leaves the platform almost parallel to the flow toward the mass flow flowing around the turbine blade.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE10064265 | 2000-12-22 | ||
| DE10064265A DE10064265A1 (en) | 2000-12-22 | 2000-12-22 | Device and method for cooling a platform of a turbine blade |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| EP1219781A2 true EP1219781A2 (en) | 2002-07-03 |
| EP1219781A3 EP1219781A3 (en) | 2004-01-21 |
| EP1219781B1 EP1219781B1 (en) | 2007-05-02 |
Family
ID=7668438
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP01128807A Expired - Lifetime EP1219781B1 (en) | 2000-12-22 | 2001-12-04 | Device and method to cool a platform of a turbine blade |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US6641360B2 (en) |
| EP (1) | EP1219781B1 (en) |
| DE (2) | DE10064265A1 (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1630354A2 (en) | 2004-08-25 | 2006-03-01 | Rolls-Royce Plc | Cooled gas turbine aerofoil |
| CN101482032A (en) * | 2008-01-10 | 2009-07-15 | 通用电气公司 | Turbine blade tip shroud |
| WO2012007250A1 (en) * | 2010-07-15 | 2012-01-19 | Siemens Aktiengesellschaft | Nozzle guide vane with cooled platform for a gas turbine |
| EP2607629A1 (en) * | 2011-12-22 | 2013-06-26 | Alstom Technology Ltd | Shrouded turbine blade with cooling air outlet port on the blade tip and corresponding manufacturing method |
| RU2575260C2 (en) * | 2010-07-15 | 2016-02-20 | Сименс Акциенгезелльшафт | Nozzle blade with cooled platform for gas turbine |
| EP3163025A1 (en) * | 2015-10-27 | 2017-05-03 | General Electric Company | Turbine bucket having outlet path in shroud |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB0228443D0 (en) * | 2002-12-06 | 2003-01-08 | Rolls Royce Plc | Blade cooling |
| US6945749B2 (en) * | 2003-09-12 | 2005-09-20 | Siemens Westinghouse Power Corporation | Turbine blade platform cooling system |
| US7114339B2 (en) * | 2004-03-30 | 2006-10-03 | United Technologies Corporation | Cavity on-board injection for leakage flows |
| EP1591626A1 (en) * | 2004-04-30 | 2005-11-02 | Alstom Technology Ltd | Blade for gas turbine |
| DE102004037331A1 (en) * | 2004-07-28 | 2006-03-23 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine rotor |
| US7144215B2 (en) * | 2004-07-30 | 2006-12-05 | General Electric Company | Method and apparatus for cooling gas turbine engine rotor blades |
| US7198467B2 (en) * | 2004-07-30 | 2007-04-03 | General Electric Company | Method and apparatus for cooling gas turbine engine rotor blades |
| US7131817B2 (en) * | 2004-07-30 | 2006-11-07 | General Electric Company | Method and apparatus for cooling gas turbine engine rotor blades |
| EP1789654B1 (en) * | 2004-09-16 | 2017-08-23 | General Electric Technology GmbH | Turbine engine vane with fluid cooled shroud |
| US7186089B2 (en) * | 2004-11-04 | 2007-03-06 | Siemens Power Generation, Inc. | Cooling system for a platform of a turbine blade |
| US7708525B2 (en) * | 2005-02-17 | 2010-05-04 | United Technologies Corporation | Industrial gas turbine blade assembly |
| US7309212B2 (en) * | 2005-11-21 | 2007-12-18 | General Electric Company | Gas turbine bucket with cooled platform leading edge and method of cooling platform leading edge |
| US7416391B2 (en) * | 2006-02-24 | 2008-08-26 | General Electric Company | Bucket platform cooling circuit and method |
| CN100513630C (en) * | 2006-03-24 | 2009-07-15 | 统宝光电股份有限公司 | Mask film cradle and deposition system |
| US7686581B2 (en) * | 2006-06-07 | 2010-03-30 | General Electric Company | Serpentine cooling circuit and method for cooling tip shroud |
| US7534088B1 (en) | 2006-06-19 | 2009-05-19 | United Technologies Corporation | Fluid injection system |
| US7946816B2 (en) * | 2008-01-10 | 2011-05-24 | General Electric Company | Turbine blade tip shroud |
| US8147197B2 (en) * | 2009-03-10 | 2012-04-03 | Honeywell International, Inc. | Turbine blade platform |
| US8079814B1 (en) * | 2009-04-04 | 2011-12-20 | Florida Turbine Technologies, Inc. | Turbine blade with serpentine flow cooling |
| US8356978B2 (en) * | 2009-11-23 | 2013-01-22 | United Technologies Corporation | Turbine airfoil platform cooling core |
| US9630277B2 (en) * | 2010-03-15 | 2017-04-25 | Siemens Energy, Inc. | Airfoil having built-up surface with embedded cooling passage |
| US8356975B2 (en) * | 2010-03-23 | 2013-01-22 | United Technologies Corporation | Gas turbine engine with non-axisymmetric surface contoured vane platform |
| US9976433B2 (en) | 2010-04-02 | 2018-05-22 | United Technologies Corporation | Gas turbine engine with non-axisymmetric surface contoured rotor blade platform |
| US8636470B2 (en) | 2010-10-13 | 2014-01-28 | Honeywell International Inc. | Turbine blades and turbine rotor assemblies |
| JP5916294B2 (en) * | 2011-04-18 | 2016-05-11 | 三菱重工業株式会社 | Gas turbine blade and method for manufacturing the same |
| WO2014130244A1 (en) | 2013-02-19 | 2014-08-28 | United Technologies Corporation | Gas turbine engine airfoil platform cooling passage and core |
| US10001013B2 (en) | 2014-03-06 | 2018-06-19 | General Electric Company | Turbine rotor blades with platform cooling arrangements |
| US10184342B2 (en) * | 2016-04-14 | 2019-01-22 | General Electric Company | System for cooling seal rails of tip shroud of turbine blade |
| EP3351341A1 (en) * | 2017-01-23 | 2018-07-25 | Siemens Aktiengesellschaft | Method for producing a cavity in a blade platform |
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-
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- 2001-12-04 DE DE50112433T patent/DE50112433D1/en not_active Expired - Lifetime
- 2001-12-06 US US10/003,419 patent/US6641360B2/en not_active Expired - Lifetime
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| US5482435A (en) | 1994-10-26 | 1996-01-09 | Westinghouse Electric Corporation | Gas turbine blade having a cooled shroud |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1630354A2 (en) | 2004-08-25 | 2006-03-01 | Rolls-Royce Plc | Cooled gas turbine aerofoil |
| EP1630354A3 (en) * | 2004-08-25 | 2009-10-28 | Rolls-Royce Plc | Cooled gas turbine aerofoil |
| CN101482032A (en) * | 2008-01-10 | 2009-07-15 | 通用电气公司 | Turbine blade tip shroud |
| WO2012007250A1 (en) * | 2010-07-15 | 2012-01-19 | Siemens Aktiengesellschaft | Nozzle guide vane with cooled platform for a gas turbine |
| RU2575260C2 (en) * | 2010-07-15 | 2016-02-20 | Сименс Акциенгезелльшафт | Nozzle blade with cooled platform for gas turbine |
| US9856747B2 (en) | 2010-07-15 | 2018-01-02 | Siemens Aktiengesellschaft | Nozzle guide vane with cooled platform for a gas turbine |
| EP2607629A1 (en) * | 2011-12-22 | 2013-06-26 | Alstom Technology Ltd | Shrouded turbine blade with cooling air outlet port on the blade tip and corresponding manufacturing method |
| EP3163025A1 (en) * | 2015-10-27 | 2017-05-03 | General Electric Company | Turbine bucket having outlet path in shroud |
| CN106968718A (en) * | 2015-10-27 | 2017-07-21 | 通用电气公司 | Turbine vane with the outlet pathway in shield |
| US10508554B2 (en) | 2015-10-27 | 2019-12-17 | General Electric Company | Turbine bucket having outlet path in shroud |
| US11078797B2 (en) | 2015-10-27 | 2021-08-03 | General Electric Company | Turbine bucket having outlet path in shroud |
Also Published As
| Publication number | Publication date |
|---|---|
| US6641360B2 (en) | 2003-11-04 |
| DE50112433D1 (en) | 2007-06-14 |
| EP1219781A3 (en) | 2004-01-21 |
| EP1219781B1 (en) | 2007-05-02 |
| DE10064265A1 (en) | 2002-07-04 |
| US20020098078A1 (en) | 2002-07-25 |
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