EP1329593A1 - Turbine-blade - Google Patents
Turbine-blade Download PDFInfo
- Publication number
- EP1329593A1 EP1329593A1 EP02001267A EP02001267A EP1329593A1 EP 1329593 A1 EP1329593 A1 EP 1329593A1 EP 02001267 A EP02001267 A EP 02001267A EP 02001267 A EP02001267 A EP 02001267A EP 1329593 A1 EP1329593 A1 EP 1329593A1
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- EP
- European Patent Office
- Prior art keywords
- platform
- blade
- turbine
- load
- load platform
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
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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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
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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
Definitions
- the invention relates to a turbine blade a profiled, extending along a blade axis Airfoil.
- Gas turbines are used to drive generators in many areas or used by work machines.
- the Energy content of a fuel to generate a rotational movement a turbine shaft used.
- the fuel will To do this, burned in a combustion chamber, using an air compressor compressed air is supplied. That in the combustion chamber generated by the combustion of the fuel, under high Pressure and high temperature working medium is via a turbine unit downstream of the combustion chamber managed where it relaxes while working.
- the turbine shaft To generate the rotational movement of the turbine shaft are a number of them usually in groups of blades or rows of blades grouped together arranged via a pulse transfer from the flow medium drive the turbine shaft.
- For guiding the flow medium are also common in the turbine unit between adjacent rows of blades with the turbine housing connected rows of vanes arranged.
- the turbine blades, in particular, the guide vanes usually have a profiled, suitable guide for the working medium Blade extending along a blade axis on the end of which is used to attach the turbine blade on the respective support body a cross to Blade axis extending in at least one end region as Hook base formed on the platform.
- Coolant channels are thus an act on the thermally particularly stressed areas of the respective Airfoil with coolant allows.
- a particularly cheap one Cooling effect and therefore a particularly high level of operational reliability can be reached by using the coolant channels a comparatively large area of space inside each Take the airfoil and add the coolant as close as possible to the respective hot gas Surface is guided.
- adequate mechanical stability and resilience can ensure the respective turbine blade be flowed through multiple channels, being inside the Blade profile a plurality of coolant-loaded from each other by comparatively thin partitions separate coolant channels are provided.
- Turbine blade for a comparatively low consumption of coolant may be desirable.
- the turbine blade with comparatively hot Working medium is with a limited consumption of coolant reliable cooling of the individual components of the turbine blade often only with a comparatively thin wall Execution of the individual components with comparative low material requirement achievable.
- This can be an actually undesirable use by comparison require thick-walled structural parts, for which then one correspondingly complex cooling with a correspondingly expanded Supply of coolant is to be provided.
- the invention is therefore based on the object of a turbine blade of the type mentioned above, on the one hand is thermally and mechanically highly resilient and on the other hand ensures a comparatively economical consumption of coolant.
- the airfoil in one end area is transverse to the airfoil axis extending hot gas platform and above a load platform are molded, a mechanical Connection of the load platform with the hot gas platform only via the airfoil.
- the invention is based on the consideration that also a thermally highly resilient turbine blade for reliable cooling necessary consumption of coolant can be kept comparatively low by the structural parts are kept largely thin-walled. To do this in With regard to the comparatively strong mechanical stress the turbine blade without any noteworthy danger To allow material damage, the thermal Load pickup on the turbine blade consistently by the mechanical The load suspension must be kept separate. For this are on Blade formed on two platform segments, one of which one, namely the hot gas platform, for recording only the thermal load and another, namely the Load platform, only to accommodate the mechanical Load is designed.
- the hot gas platform can be kept particularly thin-walled just because they are designed with almost no mechanical Load is applied.
- the load platform that sufficiently thick-walled to absorb the mechanical load should be carried out, however, is by means of the hot gas platform of direct thermal exposure shielded by the working medium and thus also in comparison massive design without significant consumption coolant can be kept at a safe operating temperature.
- a high level of operational reliability with such an arrangement can be achieved by using the comparatively thin-walled Executed hot gas platform consistently free from occurring Thermal stress is maintained.
- a such a freely expandable design of the hot gas platform can be achieved mechanically as far as possible from the Load platform is kept decoupled.
- the hot gas platform is essentially kept free of mechanical stress.
- the load platform especially with regard to their dimensioning advantageously designed such that they are for a full inclusion of the one Airfoil flowing around working medium Forces is suitable.
- the turbine blade is particularly low in manufacturing and
- the cost of materials can be provided by being more advantageous Design the load platform in terms of its shape to the one adapted to the given boundary conditions mechanical fixation required structural Components is limited.
- Such a minimalist design Design is favored by the load platform advantageously on one with respect to a working medium downstream edge of the airfoil is formed. This is seen in the flow direction of the working medium rear edge of the airfoil in the suspension area Load platform expanded, being in the direction of flow of the Working fluid seen front area of the airfoil an extensive waiver of material-intensive, the load platform structural components to be assigned can.
- the mechanical Fixation of the turbine blade on the load platform Minimum of those required for static certainty Fixation points limited.
- the load platform points to this advantageously a molded rib for radial hooking and a rib attached to this for axial hooking. With such a configuration, it is sufficient for complete Establishment of the static certainty on the inside of the Turbine blade a single contact point in the axial direction. If necessary, an anti-rotation lock can also be added Radial direction and / or a circumferential fixation on the outside the turbine blade may be provided; these can by suitable means molded onto the respective rib such as grooves or lugs can be realized.
- the turbine blade is preferably used as a guide blade for a gas turbine, especially for a stationary gas turbine, educated.
- the advantages achieved with the invention are in particular in that by reducing the mechanical connection the load platform with the hot gas platform on a connection a consistent only via the airfoil Separation of the to absorb the thermal load provided structural part from to accommodate the mechanical Load provided structural part is enabled.
- the respective Structural parts namely the hot gas platform on the one hand and the load platform, on the other hand, can thus be specific designed for their actual purpose be, in particular the hot gas platform freely expandable and can be designed comparatively thin-walled.
- the Hot gas platform on the one hand and the load platform on the other can also be completely independent in their design be executed from each other, in particular the Hot gas platform different from the load platform May have width and shape.
- the load platform can in the form of a minimal solution in its design completely geared to the needs of power transmission be, in this sense superfluous structural areas can be saved. This is in addition to one too high thermal load capacity favored by the hot gas platform also a particularly low manufacturing cost achievable with low material consumption.
- An embodiment of the invention is based on a Drawing explained in more detail.
- the figure shows in Angled view of a turbine blade.
- the turbine blade 1 according to the figure has a profiled Blade 2 that extends along a blade axis 4 extends.
- the airfoil 2 is suitable for influencing one flowing in an associated turbine unit Working medium curved and / or curved.
- the turbine blade 1 is used as a guide blade for a gas turbine educated. To use the turbine blades 1 even at comparatively high temperatures of the working medium The turbine blade is able to enable temperatures of around 1200 ° C to 1300 ° C 1 designed to be coolable. This is the shovel blade 2 in the manner of an inner profile with a cavity 6 executed via which a coolant, for example cooling steam, is feasible.
- a coolant for example cooling steam
- a platform system is located at an end region 8 of the airfoil 2 10 molded onto this.
- the platform system 10 is there both to absorb the thermal load from the Working medium as well as to absorb the mechanical load trained by the working medium. In order to do so at high thermal load with comparatively low Coolant consumption high mechanical reliability of the To enable the entire system is the platform system 10 for a consequent structural separation of thermally stressed Components formed by mechanically loaded components.
- the platform system 10 comprises a hot gas platform 12 and on the other hand one of these largely independently held load platform 14.
- the hot gas platform 12 is provided to absorb the thermal load.
- the load platform 14 is on the of the flow space for side of the hot gas platform 12 facing away from the working medium and thus arranged above this, so that the hot gas platform 12 in the manner of a heat shield for the load platform 14 acts. This means that there is no thermal stress the load platform 14 by entrained in the working medium Warmth.
- Both the hot gas platform 12 and the load platform 14 are mechanically connected only to the airfoil 2; a direct mechanical connection of the load platform 14 with the hot gas platform 12, for example via cross struts or support plates is not provided.
- the hot gas platform 12 is thus on its peripheral edge 16, which for a self-supporting construction is suitably thickened, largely freely expandable without this Limitations due to the load platform 14 could occur. With changing thermal exposure to the hot gas platform 12 and thereby induced lateral expansion or Contractions are thus induced thermal stresses kept particularly low.
- the load platform 14 is in order to form a radial hook pulled out a rib 22 on which a rib 24 for axial hooking is put on.
- a fixing pin 26 attached, another Specifies contact point in the axial direction.
- the rib 24 provided for axial hooking is a groove 28 released to form a circumferential fixation with a structural element molded onto the associated turbine housing can be brought into engagement.
- To complete the hooking in the radial direction can also in the embodiment only indicated radial ribbing 30 is provided his.
- the turbine blade 1 thus points mechanically from one another largely decoupled hot gas and load platforms 12 or 14 on. This allows the load platform 14 to be shaped specifically adapted to the given requirements be without thereby disadvantages in the thermal range in Purchase.
- the thermal load is completely intercepted by the hot gas platform 12 which again completely independent of the shape Load platform 14 can be executed.
Abstract
Description
Die Erfindung bezieht sich auf eine Turbinenschaufel mit einem profilierten, entlang einer Schaufelachse erstreckten Schaufelblatt.The invention relates to a turbine blade a profiled, extending along a blade axis Airfoil.
Gasturbinen werden in vielen Bereichen zum Antrieb von Generatoren oder von Arbeitsmaschinen eingesetzt. Dabei wird der Energieinhalt eines Brennstoffs zur Erzeugung einer Rotationsbewegung einer Turbinenwelle benutzt. Der Brennstoff wird dazu in einer Brennkammer verbrannt, wobei von einem Luftverdichter verdichtete Luft zugeführt wird. Das in der Brennkammer durch die Verbrennung des Brennstoffs erzeugte, unter hohem Druck und unter hoher Temperatur stehende Arbeitsmedium wird dabei über eine der Brennkammer nachgeschaltete Turbineneinheit geführt, wo es sich arbeitsleistend entspannt.Gas turbines are used to drive generators in many areas or used by work machines. The Energy content of a fuel to generate a rotational movement a turbine shaft used. The fuel will To do this, burned in a combustion chamber, using an air compressor compressed air is supplied. That in the combustion chamber generated by the combustion of the fuel, under high Pressure and high temperature working medium is via a turbine unit downstream of the combustion chamber managed where it relaxes while working.
Zur Erzeugung der Rotationsbewegung der Turbinenwelle sind dabei an dieser eine Anzahl von üblicherweise in Schaufelgruppen oder Schaufelreihen zusammengefaßten Laufschaufeln angeordnet, die über einen Impulsübertrag aus dem Strömungsmedium die Turbinenwelle antreiben. Zur Führung des Strömungsmediums in der Turbineneinheit sind zudem üblicherweise zwischen benachbarten Laufschaufelreihen mit dem Turbinengehäuse verbundene Leitschaufelreihen angeordnet. Die Turbinenschaufeln, insbesondere die Leitschaufeln, weisen dabei üblicherweise zur geeigneten Führung des Arbeitsmediums ein profiliertes, entlang einer Schaufelachse erstrecktes Schaufelblatt auf, an das sich endseitig zur Befestigung der Turbinenschaufel am jeweiligen Trägerkörper eine sich quer zur Schaufelachse erstreckende, in zumindest einem Endbereich als Hakensockel ausgebildete Plattform angeformt ist.To generate the rotational movement of the turbine shaft are a number of them usually in groups of blades or rows of blades grouped together arranged via a pulse transfer from the flow medium drive the turbine shaft. For guiding the flow medium are also common in the turbine unit between adjacent rows of blades with the turbine housing connected rows of vanes arranged. The turbine blades, in particular, the guide vanes usually have a profiled, suitable guide for the working medium Blade extending along a blade axis on the end of which is used to attach the turbine blade on the respective support body a cross to Blade axis extending in at least one end region as Hook base formed on the platform.
Zur Erreichung eines besonders günstigen Wirkungsgrads sind derartige Gasturbinen aus thermodynamischen Gründen üblicherweise für besonders hohe Austrittstemperaturen des aus der Brennkammer ab- und die in die in die Turbineneinheit einströmenden Arbeitsmediums von etwa 1200 °C bis etwa 1300 °C ausgelegt. Bei derartig hohen Temperaturen sind die Komponenten der Gasturbine, insbesondere die Turbinenschaufeln, vergleichsweise hohen thermischen Belastungen ausgesetzt. Um auch bei derartigen Betriebsbedingungen eine hohe Zuverlässigkeit und eine lange Lebensdauer der jeweiligen Komponenten zu gewährleisten, sind die betroffenen Bauteile üblicherweise kühlbar ausgebildet.To achieve a particularly favorable efficiency such gas turbines usually for thermodynamic reasons for particularly high outlet temperatures of the Exhaust combustion chamber and those flowing into the turbine unit Working medium from about 1200 ° C to about 1300 ° C designed. The components are at such high temperatures the gas turbine, in particular the turbine blades, comparatively exposed to high thermal loads. Around high reliability even under such operating conditions and a long service life of the respective components to ensure, the affected components are usually coolable trained.
Daher sind in modernen Gasturbinen die Turbinenschaufeln üblicherweise als sogenanntes Hohlprofil ausgebildet. Das profilierte Schaufelblatt weist dazu in seinem Innenbereich auch als Schaufelkern bezeichnete Hohlräume auf, in denen ein Kühlmedium geführt werden kann. Durch die solchermaßen gebildeten Kühlmittelkanäle ist somit eine Beaufschlagung der thermisch besonders beanspruchten Bereiche des jeweiligen Schaufelblatts mit Kühlmittel ermöglicht. Eine besonders günstige Kühlwirkung und somit eine besonders hohe Betriebssicherheit ist dabei erreichbar, indem die Kühlmittelkanäle einen vergleichsweise großen Raumbereich im Inneren des jeweiligen Schaufelblatts einnehmen, und indem das Kühlmittel möglichst nah an der jeweiligen, dem Heißgas ausgesetzten Oberfläche geführt ist. Um bei einer derartigen Auslegung andererseits eine ausreichende mechanische Stabilität und Belastbarkeit sicherzustellen, kann die jeweilige Turbinenschaufel mehrkanalig durchströmt sein, wobei im Inneren des Schaufelprofils eine Mehrzahl von mit Kühlmittel beaufschlagbaren, jeweils voneinander durch vergleichsweise dünne Trennwände getrennte Kühlmittelkanäle vorgesehen sind.Therefore, turbine blades are common in modern gas turbines designed as a so-called hollow profile. The profiled To this end, the airfoil also points in its interior cavities referred to as blade core, in which a Coolant can be performed. Through the educated in this way Coolant channels is thus an act on the thermally particularly stressed areas of the respective Airfoil with coolant allows. A particularly cheap one Cooling effect and therefore a particularly high level of operational reliability can be reached by using the coolant channels a comparatively large area of space inside each Take the airfoil and add the coolant as close as possible to the respective hot gas Surface is guided. On the other hand, with such an interpretation adequate mechanical stability and resilience can ensure the respective turbine blade be flowed through multiple channels, being inside the Blade profile a plurality of coolant-loaded from each other by comparatively thin partitions separate coolant channels are provided.
Aus Wirkungsgradgründen kann die Auslegung einer derartigen Turbinenschaufel für einen vergleichsweise geringen Verbrauch an Kühlmittel wünschenswert sein. Gerade bei einer Beaufschlagung der Turbinenschaufel mit vergleichsweise heißem Arbeitsmedium ist bei nur begrenztem Verbrauch an Kühlmittel eine zuverlässige Kühlung der einzelnen Komponenten der Turbinenschaufel oftmals nur über eine vergleichsweise dünnwandige Ausführung der einzelnen Komponenten mit vergleichsweise geringem Materialbedarf erreichbar. Gerade durch die beim Betrieb der Gasturbine in einzelnen Komponenten der Turbinenschaufel entstehenden thermischen Spannungen und die ebenfalls auftretenden erheblichen mechanischen Belastungen können zur Materialermüdung oder sogar zum Materialbruch führen. Dies kann eine eigentlich unerwünschte Verwendung vergleichsweise dickwandiger Strukturteile erfordern, für die dann eine entsprechend aufwendige Kühlung mit entsprechend erweitertem Angebot an Kühlmittel bereitzustellen ist.For reasons of efficiency, the interpretation of such Turbine blade for a comparatively low consumption of coolant may be desirable. Especially with an application the turbine blade with comparatively hot Working medium is with a limited consumption of coolant reliable cooling of the individual components of the turbine blade often only with a comparatively thin wall Execution of the individual components with comparative low material requirement achievable. Especially because of the operation of the gas turbine in individual components of the turbine blade arising thermal stresses and the likewise considerable mechanical loads can occur lead to material fatigue or even breakage. This can be an actually undesirable use by comparison require thick-walled structural parts, for which then one correspondingly complex cooling with a correspondingly expanded Supply of coolant is to be provided.
Der Erfindung liegt daher die Aufgabe zugrunde, eine Turbinenschaufel der oben genannten Art anzugeben, die einerseits thermisch und mechanisch hoch belastbar ist und andererseits einen vergleichsweise sparsamen Verbrauch an Kühlmittel gewährleistet.The invention is therefore based on the object of a turbine blade of the type mentioned above, on the one hand is thermally and mechanically highly resilient and on the other hand ensures a comparatively economical consumption of coolant.
Diese Aufgabe wird erfindungsgemäß gelöst, indem an das Schaufelblatt in einem Endbereich eine sich quer zur Schaufelachse erstreckende Heißgasplattform und darüberliegend eine Lastplattform angeformt sind, wobei eine mechanische Verbindung der Lastplattform mit der Heißgasplattform ausschließlich über das Schaufelblatt erfolgt.This object is achieved by the The airfoil in one end area is transverse to the airfoil axis extending hot gas platform and above a load platform are molded, a mechanical Connection of the load platform with the hot gas platform only via the airfoil.
Die Erfindung geht dabei von der Überlegung aus, daß auch bei einer thermisch hoch belastbaren Turbinenschaufel der für eine zuverlässige Kühlung notwendige Verbrauch an Kühlmittel vergleichsweise gering gehalten werden kann, indem die Strukturteile weitgehend dünnwandig gehalten sind. Um dies auch im Hinblick auf die vergleichsweise starke mechanische Beanspruchung der Turbinenschaufel ohne nennenswerte Gefahr einer Materialbeschädigung zu ermöglichen, sollte die thermische Lastaufnahme an der Turbinenschaufel konsequent von der mechanischen Lastaufnahme getrennt gehalten sein. Dazu sind am Schaufelblatt zwei Plattformsegmente angeformt, von denen eines, nämlich die Heißgasplattform, ausschließlich zur Aufnahme der thermischen Belastung und ein anderes, nämlich die Lastplattform, ausschließlich zur Aufnahme der mechanischen Belastung ausgelegt ist.The invention is based on the consideration that also a thermally highly resilient turbine blade for reliable cooling necessary consumption of coolant can be kept comparatively low by the structural parts are kept largely thin-walled. To do this in With regard to the comparatively strong mechanical stress the turbine blade without any noteworthy danger To allow material damage, the thermal Load pickup on the turbine blade consistently by the mechanical The load suspension must be kept separate. For this are on Blade formed on two platform segments, one of which one, namely the hot gas platform, for recording only the thermal load and another, namely the Load platform, only to accommodate the mechanical Load is designed.
Die Heißgasplattform kann dabei besonders dünnwandig gehalten sein, gerade weil sie auslegungsgemäß mit nahezu keiner mechanischen Belastung beaufschlagt ist. Die Lastplattform, die zur Aufnahme der mechanischen Belastung ausreichend dickwandig ausgeführt sein sollte, ist hingegen mittels der Heißgasplattform von einer direkten thermischen Beaufschlagung durch das Arbeitsmedium abgeschirmt und somit auch bei vergleichsweise massiver Ausführung ohne nennenswerten Verbrauch an Kühlmittel auf einer sicheren Betriebstemperatur haltbar. Eine hohe Betriebssicherheit bei einer derartigen Anordnung ist erreichbar, indem gerade die vergleichsweise dünnwandig ausgeführte Heißgasplattform konsequent frei von auftretender Wärmespannung gehalten wird. Um das Auftreten von Wärmespännungen zu verhindern, sollte die Heißgasplattform weitestgehend frei ausdehnbar sein, so daß auch bei wechselnder thermischer Beaufschlagung infolge thermisch induzierter Ausdehnung oder Kontraktion keine Spannungen auftreten können. Eine derartig frei ausdehnbare Ausgestaltung der Heißgasplattform ist erreichbar, indem diese mechanisch weitestgehend von der Lastplattform entkoppelt gehalten ist.The hot gas platform can be kept particularly thin-walled just because they are designed with almost no mechanical Load is applied. The load platform that sufficiently thick-walled to absorb the mechanical load should be carried out, however, is by means of the hot gas platform of direct thermal exposure shielded by the working medium and thus also in comparison massive design without significant consumption coolant can be kept at a safe operating temperature. A high level of operational reliability with such an arrangement can be achieved by using the comparatively thin-walled Executed hot gas platform consistently free from occurring Thermal stress is maintained. To the occurrence of thermal stress to prevent the hot gas platform as much as possible be freely expandable so that even with changing thermal Exposure due to thermally induced expansion or contraction no tension can occur. A such a freely expandable design of the hot gas platform can be achieved mechanically as far as possible from the Load platform is kept decoupled.
Auslegungsgemäß ist die Heißgasplattform dabei im wesentlichen frei von mechanischer Belastung gehalten. Um dies zu ermöglichen, ist die Lastplattform insbesondere hinsichtlich ihrer Dimensionierung vorteilhafterweise derart ausgelegt, daß sie für eine vollständige Aufnahme der durch ein das Schaufelblatt umströmendes Arbeitsmedium hervorgerufenen Kräfte geeignet ist.By design, the hot gas platform is essentially kept free of mechanical stress. In order to make this possible, is the load platform especially with regard to their dimensioning advantageously designed such that they are for a full inclusion of the one Airfoil flowing around working medium Forces is suitable.
Die Turbinenschaufel ist mit besonders geringem Herstellungsund Materialaufwand bereitstellbar, indem in vorteilhafter Ausgestaltung die Lastplattform hinsichtlich ihrer Formgebung auf die zu einer auf die vorgegebenen Randbedingungen angepaßten mechanischen Fixierung erforderlichen strukturellen Komponenten beschränkt ist. Eine derartig minimalisiert ausgeführte Ausgestaltung ist begünstigt, indem die Lastplattform vorteilhafterweise an einer bezüglich eines Arbeitsmediums abströmseitigen Kante des Schaufelblatts angeformt ist. Dabei ist die in Strömungsrichtung des Arbeitsmediums gesehen hintere Kante des Schaufelblatts im Aufhängungsbereich zur Lastplattform erweitert, wobei im in Strömungsrichtung des Arbeitsmediums gesehen vorderen Bereich des Schaufelblatts ein weitgehender Verzicht auf materialaufwendige, der Lastplattform zuzuordnende strukturelle Komponenten erfolgen kann.The turbine blade is particularly low in manufacturing and The cost of materials can be provided by being more advantageous Design the load platform in terms of its shape to the one adapted to the given boundary conditions mechanical fixation required structural Components is limited. Such a minimalist design Design is favored by the load platform advantageously on one with respect to a working medium downstream edge of the airfoil is formed. This is seen in the flow direction of the working medium rear edge of the airfoil in the suspension area Load platform expanded, being in the direction of flow of the Working fluid seen front area of the airfoil an extensive waiver of material-intensive, the load platform structural components to be assigned can.
In besonders vorteilhafter Ausgestaltung ist die mechanische Fixierung der Turbinenschaufel über die Lastplattform auf ein Minimum der für eine statische Bestimmtheit erforderlichen Fixierungspunkte beschränkt. Dazu weist die Lastplattform vorteilhafterweise eine angeformte Rippe zur Radialverhakung und eine auf dieser aufgesetzte Rippe zur Axialverhakung auf. Bei einer derartigen Ausgestaltung genügt zur vollständigen Herstellung der statischen Bestimmtheit an der Innenseite der Turbinenschaufel ein einziger Anlagepunkt in axialer Richtung. Bedarfsweise kann zudem noch eine Verdrehsicherung in Radialrichtung und/oder eine Umfangsfixierung an der Außenseite der Turbinenschaufel vorgesehen sein; diese können durch geeignete, an der jeweiligen Rippe angeformte Mittel wie beispielsweise Nuten oder Nasen, realisiert sein.In a particularly advantageous embodiment, the mechanical Fixation of the turbine blade on the load platform Minimum of those required for static certainty Fixation points limited. The load platform points to this advantageously a molded rib for radial hooking and a rib attached to this for axial hooking. With such a configuration, it is sufficient for complete Establishment of the static certainty on the inside of the Turbine blade a single contact point in the axial direction. If necessary, an anti-rotation lock can also be added Radial direction and / or a circumferential fixation on the outside the turbine blade may be provided; these can by suitable means molded onto the respective rib such as grooves or lugs can be realized.
Die Turbinenschaufel ist vorzugsweise als Leitschaufel für eine Gasturbine, insbesondere für eine stationäre Gasturbine, ausgebildet.The turbine blade is preferably used as a guide blade for a gas turbine, especially for a stationary gas turbine, educated.
Die mit der Erfindung erzielten Vorteile bestehen insbesondere darin, daß durch die Reduktion der mechanischen Verbindung der Lastplattform mit der Heißgasplattform auf eine Verbindung ausschließlich über das Schaufelblatt eine konsequente Trennung des zur Aufnahme der thermischen Belastung vorgesehenen Strukturteils vom zur Aufnahme der mechanischen Belastung vorgesehenen Strukturteil ermöglicht ist. Die jeweiligen Strukturteile, nämlich die Heißgasplattform einerseits und die Lastplattform andererseits, können somit spezifisch auf ihren eigentlichen Anwendungszweck hin ausgestaltet sein, wobei insbesondere die Heißgasplattform frei ausdehnbar und vergleichsweise dünnwandig ausgestaltet sein kann. Die Heißgasplattform einerseits und die Lastplattform andererseits können zudem auch in ihrer Formgebung vollständig unabhängig voneinander ausgeführt sein, wobei insbesondere die Heißgasplattform eine von der Lastplattform unterschiedliche Breite und Form aufweisen kann. Die Lastplattform kann dabei in der Art einer Minimallösung in ihrer Formgebung vollständig auf die Notwendigkeiten der Kraftübertragung ausgerichtet sein, wobei in diesem Sinne überflüssige Strukturbereiche eingespart sein können. Damit ist zusätzlich zu einer auch durch die Heißgasplattform begünstigten hohen thermischen Belastbarkeit auch ein besonders geringer Herstellungsaufwand bei nur geringem Materialverbrauch erreichbar.The advantages achieved with the invention are in particular in that by reducing the mechanical connection the load platform with the hot gas platform on a connection a consistent only via the airfoil Separation of the to absorb the thermal load provided structural part from to accommodate the mechanical Load provided structural part is enabled. The respective Structural parts, namely the hot gas platform on the one hand and the load platform, on the other hand, can thus be specific designed for their actual purpose be, in particular the hot gas platform freely expandable and can be designed comparatively thin-walled. The Hot gas platform on the one hand and the load platform on the other can also be completely independent in their design be executed from each other, in particular the Hot gas platform different from the load platform May have width and shape. The load platform can in the form of a minimal solution in its design completely geared to the needs of power transmission be, in this sense superfluous structural areas can be saved. This is in addition to one too high thermal load capacity favored by the hot gas platform also a particularly low manufacturing cost achievable with low material consumption.
Ein Ausführungsbeispiel der Erfindung wird anhand einer Zeichnung näher erläutert. Darin zeigt die Figur in Schrägsicht eine Turbinenschaufel.An embodiment of the invention is based on a Drawing explained in more detail. The figure shows in Angled view of a turbine blade.
Die Turbinenschaufel 1 gemäß der Figur weist ein profiliertes
Schaufelblatt 2 auf, das sich entlang einer Schaufelachse 4
erstreckt. Das Schaufelblatt 2 ist dabei zur geeigneten Beeinflussung
eines in einer zugeordneten Turbineneinheit strömenden
Arbeitsmediums gewölbt und/oder gekrümmt.The turbine blade 1 according to the figure has a profiled
Die Turbinenschaufel 1 ist als Leitschaufel für eine Gasturbine
ausgebildet. Um einen Einsatz der Turbinenschaüfel 1
auch bei vergleichsweise hohen Temperaturen des Arbeitsmediums
von etwa 1200°C bis 1300°C zu ermöglichen, ist die Turbinenschaufel
1 kühlbar ausgebildet. Dazu ist das Schaufelblatt
2 in der Art einer Innenprofilierung mit einem Hohlraum 6
ausgeführt, über den ein Kühlmittel, beispielsweise Kühldampf,
führbar ist.The turbine blade 1 is used as a guide blade for a gas turbine
educated. To use the turbine blades 1
even at comparatively high temperatures of the working medium
The turbine blade is able to enable temperatures of around 1200 ° C to 1300 ° C
1 designed to be coolable. This is the
An einem Endbereich 8 des Schaufelblatts 2 ist ein Plattformsystem
10 an dieses angeformt. Das Plattformsystem 10 ist dabei
sowohl zur Aufnahme der thermischen Belastung durch das
Arbeitsmedium als auch zur Aufnahme der mechanischen Belastung
durch das Arbeitsmedium ausgebildet. Um dabei auch bei
hoher thermischer Belastung bei vergleichsweise geringem
Kühlmittelverbrauch eine hohe mechanische Zuverlässigkeit des
Gesamtsystems zu ermöglichen, ist das Plattformsystem 10 für
ein konsequente strukturelle Trennung thermisch belasteter
Bauteile von mechanisch belasteten Bauteilen ausgebildet.A platform system is located at an
Dazu umfaßt das Plattformsystem 10 einerseits eine Heißgasplattform
12 und andererseits eine von dieser weitgehend
unabhängig gehaltene Lastplattform 14. Die Heißgasplattform
12 ist dabei zur Aufnahme der thermischen Belastung vorgesehen.
Die Lastplattform 14 ist auf der vom Strömungsraum für
das Arbeitsmedium abgewandten Seite der Heißgasplattform 12
und somit über dieser liegend angeordnet, so daß die Heißgasplattform
12 in der Art eines Wärmeschilds für die Lastplattform
14 wirkt. Damit erfolgt keine thermische Beaufschlagung
der Lastplattform 14 durch im Arbeitsmedium mitgeführte
Wärme.For this purpose, the
Sowohl die Heißgasplattform 12 als auch die Lastplattform 14
sind mechanisch ausschließlich mit dem Schaufelblatt 2 verbunden;
eine direkte mechanische Verbindung der Lastplattform
14 mit der Heißgasplattform 12 beispielsweise über Querstreben
oder Stützbleche ist nicht vorgesehen. Die Heißgasplattform
12 ist somit an ihrem umlaufenden Rand 16, der für eine
selbsttragende Konstruktion geeignet verdickt ausgeführt ist,
weitgehend frei ausdehnbar ausgeführt, ohne daß diesbezüglich
Einschränkungen durch die Lastplattform 14 auftreten könnten.
Bei wechselnder thermischer Beaufschlagung der Heißgasplattform
12 und dadurch induzierte laterale Ausdehnungen oder
Kontraktionen sind dadurch induzierte Wärmespannungen somit
besonders gering gehalten.Both the
Die Lastplattform 14, die aufgrund der thermischen Abschirmung
durch die Heißgasplattform 12 thermisch nur vergleichsweise
gering belastet ist und somit vergleichsweise einfach
auf eine zuverlässige Betriebstemperatur kühlbar ist, ist zur
vollständigen Aufnahme der durch das Arbeitsmedium auf das
Schäufelblatt 2 einwirkenden Kräfte ausgelegt und dazu vergleichsweise
dickwandig ausgeführt. In ihrer Formgebung ist
die Lastplattform 14 jedoch in der Art einer minimalisierten
Ausführung auf eine vergleichsweise geringe Anzahl mechanischer
Fixpunkte unter weitgehendem Verzicht auf darüber hinausgehende
strukturelle Komponenten ausgelegt. Dazu ist die
Lastplattform 14 lediglich an der bezüglich der Strömungsrichtung
des Arbeitsmediums in der zugeordneten Turbineneinheit
gesehen abströmseitigen Kante 18 des Schaufelblatts 2
angeformt; an der in Strömungsrichtung des Arbeitsmediums gesehen
vorderen Kante 20 des Schaufelblatts 2 ist hingegen an
seinem oberen Ende 8 keine durchgehende Fortsetzung zur Bildung
eines zur Lastplattform 14 gehörigen Strukturelements
vorgesehen.The
Zur Bildung einer Radialverhakung ist die Lastplattform 14 in
eine Rippe 22 ausgezogen, auf die eine Rippe 24 zur Axialverhakung
aufgesetzt ist. Zur Vervollständigung der Verhakung in
axialer Richtung ist weiterhin auf der Innenseite der Turbinenschaufel
1 ein Fixierstift 26 angesetzt, der einen weiteren
Anlagepunkt in axialer Richtung vorgibt. In der zur Bildung
der Axialverhakung vorgesehenen Rippe 24 ist eine Nut 28
freigelassen, die zur Bildung einer Umfangsfixierung mit
einem am zugehörigen Turbinengehäüse angeformten Strukturelement
in Eingriff bringbar ist. Zur Vervollständigung der Verhakung
in radialer Richtung kann zudem eine im Ausführungsbeispiel
lediglich angedeutete Radialverrippung 30 vorgesehen
sein. The
Die Turbinenschaufel 1 weist somit mechanisch voneinander
weitestgehend entkoppelte Heißgas- und Lastplattformen 12
bzw. 14 auf. Dadurch kann die Lastplattform 14 in ihrer Formgebung
spezifisch an die vorgegebenen Anforderungen angepaßt
sein, ohne daß dadurch Nachteile im thermischen Bereich in
Kauf zu nehmen sind. Die thermische Beaufschlagung wird hingegen
vollständig von der Heißgasplattform 12 abgefangen, die
wiederum in ihrer Formgebung vollständig unabhängig von der
Lastplattform 14 ausgeführt sein kann.The turbine blade 1 thus points mechanically from one another
largely decoupled hot gas and
Claims (5)
Priority Applications (6)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE50202538T DE50202538D1 (en) | 2002-01-17 | 2002-01-17 | Turbine blade with a hot gas platform and a load platform |
| AT02001267T ATE291677T1 (en) | 2002-01-17 | 2002-01-17 | TURBINE BLADE WITH A HOT GAS PLATFORM AND A LOAD PLATFORM |
| EP02001267A EP1329593B1 (en) | 2002-01-17 | 2002-01-17 | Turbine blade with a hot gas suporting platform and a mechanical load suporting platform |
| JP2003007396A JP4249990B2 (en) | 2002-01-17 | 2003-01-15 | Turbine blade |
| US10/345,967 US6887040B2 (en) | 2001-09-12 | 2003-01-17 | Turbine blade/vane |
| CNB031207006A CN1313707C (en) | 2002-01-17 | 2003-01-17 | Turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP02001267A EP1329593B1 (en) | 2002-01-17 | 2002-01-17 | Turbine blade with a hot gas suporting platform and a mechanical load suporting platform |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1329593A1 true EP1329593A1 (en) | 2003-07-23 |
| EP1329593B1 EP1329593B1 (en) | 2005-03-23 |
Family
ID=8185296
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP02001267A Expired - Lifetime EP1329593B1 (en) | 2001-09-12 | 2002-01-17 | Turbine blade with a hot gas suporting platform and a mechanical load suporting platform |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US6887040B2 (en) |
| EP (1) | EP1329593B1 (en) |
| JP (1) | JP4249990B2 (en) |
| CN (1) | CN1313707C (en) |
| AT (1) | ATE291677T1 (en) |
| DE (1) | DE50202538D1 (en) |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7604456B2 (en) * | 2006-04-11 | 2009-10-20 | Siemens Energy, Inc. | Vane shroud through-flow platform cover |
| FR2953252B1 (en) * | 2009-11-30 | 2012-11-02 | Snecma | DISTRIBUTOR SECTOR FOR A TURBOMACHINE |
| US20110200430A1 (en) * | 2010-02-16 | 2011-08-18 | General Electric Company | Steam turbine nozzle segment having arcuate interface |
| 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 |
| US8920117B2 (en) | 2011-10-07 | 2014-12-30 | Pratt & Whitney Canada Corp. | Fabricated gas turbine duct |
| US9546557B2 (en) * | 2012-06-29 | 2017-01-17 | General Electric Company | Nozzle, a nozzle hanger, and a ceramic to metal attachment system |
| US20140023517A1 (en) * | 2012-07-23 | 2014-01-23 | General Electric Company | Nozzle for turbine system |
| US9289826B2 (en) * | 2012-09-17 | 2016-03-22 | Honeywell International Inc. | Turbine stator airfoil assemblies and methods for their manufacture |
| US9506362B2 (en) | 2013-11-20 | 2016-11-29 | General Electric Company | Steam turbine nozzle segment having transitional interface, and nozzle assembly and steam turbine including such nozzle segment |
| US11346234B2 (en) | 2020-01-02 | 2022-05-31 | Rolls-Royce Plc | Turbine vane assembly incorporating ceramic matrix composite materials |
| US11732596B2 (en) | 2021-12-22 | 2023-08-22 | Rolls-Royce Plc | Ceramic matrix composite turbine vane assembly having minimalistic support spars |
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|---|---|---|---|---|
| US3610769A (en) * | 1970-06-08 | 1971-10-05 | Gen Motors Corp | Porous facing attachment |
| GB1516757A (en) * | 1975-10-14 | 1978-07-05 | United Technologies Corp | Turbomachinery vane or blade with cooled platforms |
| GB1605219A (en) * | 1975-10-02 | 1984-08-30 | Rolls Royce | Stator vane for a gas turbine engine |
| US5249418A (en) * | 1991-09-16 | 1993-10-05 | General Electric Company | Gas turbine engine polygonal structural frame with axially curved panels |
| WO1999054597A1 (en) * | 1998-04-21 | 1999-10-28 | Siemens Aktiengesellschaft | Turbine blade |
| US20010018020A1 (en) * | 1998-08-31 | 2001-08-30 | Peter Tiemann | Turbine guide blade |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2500745A (en) | 1944-09-21 | 1950-03-14 | Gen Electric | Bucket structure for high-temperature turbomachines |
| BE794195A (en) | 1972-01-18 | 1973-07-18 | Bbc Sulzer Turbomaschinen | COOLED STEERING VANE FOR GAS TURBINES |
| GB1605309A (en) | 1975-03-14 | 1989-02-01 | Rolls Royce | Stator blade for a gas turbine engine |
| IT1079131B (en) | 1975-06-30 | 1985-05-08 | Gen Electric | IMPROVED COOLING APPLICABLE IN PARTICULAR TO ELEMENTS OF GAS TURBO ENGINES |
| US4283822A (en) | 1979-12-26 | 1981-08-18 | General Electric Company | Method of fabricating composite nozzles for water cooled gas turbines |
| DE3244255A1 (en) * | 1982-11-30 | 1984-06-14 | Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn | RAIL SURVEYING AND MONITORING SYSTEM |
| US4987736A (en) | 1988-12-14 | 1991-01-29 | General Electric Company | Lightweight gas turbine engine frame with free-floating heat shield |
| US5076049A (en) | 1990-04-02 | 1991-12-31 | General Electric Company | Pretensioned frame |
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| FR2707698B1 (en) | 1993-07-15 | 1995-08-25 | Snecma | Turbomachine provided with an air blowing means on a rotor element. |
| US5396763A (en) | 1994-04-25 | 1995-03-14 | General Electric Company | Cooled spraybar and flameholder assembly including a perforated hollow inner air baffle for impingement cooling an outer heat shield |
| JPH08135402A (en) | 1994-11-11 | 1996-05-28 | Mitsubishi Heavy Ind Ltd | Gas turbine stationary blade structure |
| US5797725A (en) * | 1997-05-23 | 1998-08-25 | Allison Advanced Development Company | Gas turbine engine vane and method of manufacture |
| US6375415B1 (en) * | 2000-04-25 | 2002-04-23 | General Electric Company | Hook support for a closed circuit fluid cooled gas turbine nozzle stage segment |
-
2002
- 2002-01-17 DE DE50202538T patent/DE50202538D1/en not_active Expired - Lifetime
- 2002-01-17 AT AT02001267T patent/ATE291677T1/en not_active IP Right Cessation
- 2002-01-17 EP EP02001267A patent/EP1329593B1/en not_active Expired - Lifetime
-
2003
- 2003-01-15 JP JP2003007396A patent/JP4249990B2/en not_active Expired - Fee Related
- 2003-01-17 CN CNB031207006A patent/CN1313707C/en not_active Expired - Fee Related
- 2003-01-17 US US10/345,967 patent/US6887040B2/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3610769A (en) * | 1970-06-08 | 1971-10-05 | Gen Motors Corp | Porous facing attachment |
| GB1605219A (en) * | 1975-10-02 | 1984-08-30 | Rolls Royce | Stator vane for a gas turbine engine |
| GB1516757A (en) * | 1975-10-14 | 1978-07-05 | United Technologies Corp | Turbomachinery vane or blade with cooled platforms |
| US5249418A (en) * | 1991-09-16 | 1993-10-05 | General Electric Company | Gas turbine engine polygonal structural frame with axially curved panels |
| WO1999054597A1 (en) * | 1998-04-21 | 1999-10-28 | Siemens Aktiengesellschaft | Turbine blade |
| US20010018020A1 (en) * | 1998-08-31 | 2001-08-30 | Peter Tiemann | Turbine guide blade |
Also Published As
| Publication number | Publication date |
|---|---|
| DE50202538D1 (en) | 2005-04-28 |
| EP1329593B1 (en) | 2005-03-23 |
| US6887040B2 (en) | 2005-05-03 |
| ATE291677T1 (en) | 2005-04-15 |
| US20030133802A1 (en) | 2003-07-17 |
| CN1313707C (en) | 2007-05-02 |
| CN1436920A (en) | 2003-08-20 |
| JP2003214109A (en) | 2003-07-30 |
| JP4249990B2 (en) | 2009-04-08 |
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