EP1329593B1 - Turbine blade with a hot gas suporting platform and a mechanical load suporting platform - Google Patents
Turbine blade with a hot gas suporting platform and a mechanical load suporting platform Download PDFInfo
- Publication number
- EP1329593B1 EP1329593B1 EP02001267A EP02001267A EP1329593B1 EP 1329593 B1 EP1329593 B1 EP 1329593B1 EP 02001267 A EP02001267 A EP 02001267A EP 02001267 A EP02001267 A EP 02001267A EP 1329593 B1 EP1329593 B1 EP 1329593B1
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- EP
- European Patent Office
- Prior art keywords
- platform
- blade
- vane
- turbine
- turbine blade
- 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.)
- Expired - Lifetime
Links
- 239000002826 coolant Substances 0.000 description 15
- 238000001816 cooling Methods 0.000 description 7
- 239000000463 material Substances 0.000 description 6
- 238000002485 combustion reaction Methods 0.000 description 4
- 230000035882 stress Effects 0.000 description 4
- 239000000446 fuel Substances 0.000 description 3
- 230000008646 thermal stress Effects 0.000 description 3
- 230000008602 contraction Effects 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 230000008642 heat stress Effects 0.000 description 1
- 210000001331 nose Anatomy 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 238000004513 sizing Methods 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
Images
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
-
- 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 with a profiled, along a blade axis extended Airfoil.
- a vane for a Gas turbine which consists of two components is composed.
- the first component has that Shovel profile extending through a platform extends through.
- a second component is for recording of the blade profile in a rectangular, as An impeller cooling plate serving an opening on the, which Profile of the bucket corresponds. It is on the plate one provided circumferential edge, which encompasses the platform and supports.
- At the side facing away from the platform Plate are mechanical for attachment of the vane provided resilient flanges, which partially from Shovel profile are penetrated.
- the second component serves to fix the blade profile and to form an impingement cooling element for the H thoroughlygasbeetzyerte Platform.
- the turbine blades in particular the guide vanes, usually have for the suitable guidance of the working medium a profiled, along a blade axis extended blade on, at the end for attachment of the turbine blade on the respective support body a transverse to Blade axis extending, in at least one end as Hook base trained platform is formed.
- Such gas turbines for thermodynamic reasons usually for particularly high outlet temperatures of the Combustion off and in the flowing into the turbine unit Working medium from about 1200 ° C to about 1300 ° C. designed.
- the components are the gas turbine, in particular the turbine blades, comparatively exposed to high thermal loads.
- a high reliability and a long life of the respective components to ensure the affected components are common cooled formed.
- the turbine blades are common designed as a so-called hollow profile.
- the profiled Airfoil features in its interior too referred to as vane core cavities in which a Cooling medium can be performed.
- Coolant channels By the thus formed Coolant channels is thus an admission of the thermally stressed areas of the respective Blade with coolant allowed.
- a particularly cheap Cooling effect and thus a particularly high level of operational safety is achievable by the coolant channels a comparatively large area of space inside each of them Occupy the airfoil and adding the coolant as close as possible to the respective, the hot gas exposed Surface is guided.
- sufficient mechanical stability and resilience can ensure the particular turbine blade flowed through several channels, wherein inside the Blade profiles a plurality of acted upon by coolant, each other by comparatively thin partitions separate coolant channels are provided.
- Turbine blade for a comparatively low consumption be desirable to coolant.
- the turbine blade with comparatively hot Working medium is with only limited consumption of coolant a reliable cooling of the individual components of the turbine blade often only over a relatively thin-walled Execution of the individual components with comparatively low material requirement achievable.
- the gas turbine in individual components of the turbine blade resulting thermal stresses and also occurring considerable mechanical stress lead to material fatigue or even material breakage. This can be a relatively unwanted use comparatively thick-walled structural parts require, for the then one correspondingly complex cooling with correspondingly extended Supply of coolant is to provide.
- the invention is therefore based on the object, a turbine blade of the type mentioned above, on the one hand thermally and mechanically highly resilient and on the other hand Ensures a comparatively economical consumption of coolant.
- Airfoil in an end region one transverse to the blade axis extending hot gas platform and overlying a load platform are formed, wherein a mechanical Connection of the load platform with the hot gas platform exclusively takes place over the blade.
- the invention is based on the consideration that even at a thermally highly resilient turbine blade for a reliable cooling necessary consumption of coolant can be kept comparatively low by the structural parts are kept largely thin-walled. To do this in the In view of the comparatively strong mechanical stress the turbine blade without significant risk of To allow material damage, the thermal should Load absorption at the turbine blade consistently from the mechanical Lifting be kept separate. These are on Airfoil formed two platform segments, of which one, namely the hot gas platform, exclusively for receiving the thermal load and another, namely the Load platform, exclusively for the reception of 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, the sufficiently thick-walled to absorb the mechanical load should be executed, however, is by means of the hot gas platform from a direct thermal load shielded by the working medium and thus also in comparatively massive version without significant consumption conservees coolant to a safe operating temperature.
- a high level of operational reliability in such an arrangement is achievable by just the comparatively thin-walled executed hot gas platform consistently free from occurring Heat stress is maintained.
- the hot gas platform should as far 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 freely expandable design of the hot gas platform is achievable by these mechanically as far as possible from the Load platform is kept decoupled.
- the load platform in particular as regards their sizing advantageously designed in such a way that they are looking for a complete reception by the one Airfoil evolved around working fluid Forces is suitable.
- the turbine blade is with particularly low manufacturing and Material expenditure available by in advantageous Design the load platform in terms of their design on the one adapted to the given boundary conditions mechanical fixation required structural Components is limited.
- Such a minimalist running Design is favored by the load platform advantageously at one with respect to a working medium formed downstream edge of the airfoil. It is seen in the flow direction of the working medium rear edge of the airfoil in the suspension area to Extended loading platform, wherein in the flow direction of the Working fluid seen front area of the airfoil a major waiver of material-consuming, the load platform attributable structural components take place can.
- the load platform advantageously a molded rib for Radialverhakung and on this patch rib for Axialverhakung on.
- the static determination on the inside of the Turbine blade a single point of contact in the axial direction.
- a rotation in Radial direction and / or a peripheral fixation on the outside be provided the turbine blade; these can by suitable means formed on the respective rib such as grooves or noses, be realized.
- the turbine blade is preferably as a guide vane for a gas turbine, in particular for a stationary gas turbine, educated.
- the advantages achieved by the invention are in particular in that by the reduction of the mechanical connection the load platform with the hot gas platform on a connection exclusively on the blade a consistent Separation of to absorb the thermal load provided structural part of the for receiving the mechanical Load provided structural part is enabled.
- the respective ones Structural parts, namely the hot gas platform on the one hand and the load platform, on the other hand, can thus be specific designed to their actual purpose be, in particular, the hot gas platform freely expandable and can be made comparatively thin-walled.
- the Hot gas platform on the one hand and the load platform on the other are completely independent in their design be executed from each other, in particular the Hot gas platform one different from the load platform Can have width and shape.
- the load platform can do this in the manner of a minimal solution in its shape 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 favored by the hot gas platform high thermal capacity also a particularly low production cost achievable with only low material consumption.
- the turbine blade 1 according to the figure has a profiled Airfoil 2, which extends along a blade axis. 4 extends.
- the blade 2 is suitable for influencing a flowing in an associated turbine unit Working medium arched and / or curved.
- the turbine blade 1 is used as a guide vane for a gas turbine educated. To use the turbine blades 1 even at relatively high temperatures of the working medium from about 1200 ° C to 1300 ° C, is the turbine blade 1 formed coolable. This is the blade 2 in the manner of an internal profiling with a cavity. 6 executed, via which a coolant, such as cooling steam, is feasible.
- a coolant such as cooling steam
- a platform system 10 molded to this.
- the platform system 10 is included both to absorb the thermal load through the Working medium as well as to absorb the mechanical stress formed by the working medium.
- high thermal reliability of the To enable complete system is the platform system 10 for a consistent structural separation thermally contaminated Components of mechanically loaded components formed.
- the platform system 10 on the one hand comprises a hot gas platform 12 and on the other hand one of this largely independently held load platform 14.
- the hot gas platform 12 is provided for receiving the thermal load.
- the load platform 14 is on the from the flow space for the working medium side facing away from the hot gas platform 12th and thus arranged over this lying, so that the hot gas platform 12 in the manner of a heat shield for the load platform 14 acts. This is no thermal impact the load platform 14 carried by in the working medium Warmth.
- Both the hot gas platform 12 and the load platform 14 are mechanically connected exclusively to the blade 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 at its peripheral edge 16, for a Self-supporting construction is designed to be suitably thickened largely executed freely expandable, without regard to this Restrictions could occur through the load platform 14. With changing thermal loading of the hot gas platform 12 and thereby induced lateral expansions or Contractions are thus induced thermal stresses thus kept very low.
- the load platform 14 due to the thermal shielding by the hot gas platform 12 thermally only comparatively is slightly loaded and thus comparatively easy is coolable to a reliable operating temperature is to completely absorbed by the working medium on the Shuufelblatt 2 acting forces and comparatively thick-walled.
- the load platform 14 In its shape is the load platform 14, however, in the manner of a minimized Execution on a comparatively small number of mechanical Fixed points, largely renouncing beyond designed structural components. This is the Load platform 14 only at the respect to the flow direction the working medium in the associated turbine unit seen downstream edge 18 of the airfoil. 2 molded; seen at the flow direction of the working medium front edge 20 of the airfoil 2, however, is on its upper end 8 no continuous continuation of education a structural element belonging to the load platform 14 intended.
- the turbine blade 1 thus has mechanically from each other largely decoupled hot gas and load platforms 12 or 14 on.
- This allows the load platform 14 in its shape specifically adapted to the given requirements be without causing disadvantages in the thermal range in Buy are to take.
- the thermal impact is, however, completely intercepted by the hot gas platform 12, the again in their shape completely independent of the Load platform 14 may be executed.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
Description
Die Erfindung bezieht sich auf eine Turbinenschaufel mit einem profilierten, entlang einer Schaufelachse erstreckten Schaufelblatt.The invention relates to a turbine blade with a profiled, along a blade axis extended Airfoil.
Aus der GB 1 605 219 ist eine Leitschaufel für eine
Gasturbine bekannt, welche aus zwei Komponenten
zusammengesetzt ist. Die erste Komponente weist das
Schaufelprofil auf, welches sich durch eine Plattform
hindurch erstreckt. Eine zweite Komponente weist zur Aufnahme
des Schaufelprofils in einer rechteckförmigen, als
Prallkühlelement dienenden Platte eine Öffnung auf, die dem
Profil der Schaufel entspricht. Dabei ist an der Platte eine
umlaufende Kante vorgesehen, welche die Plattform umgreift
und abstützt. An der der Plattform abgewandten Seite der
Platte sind zur Befestigung der Leitschaufel mechanisch
belastbare Flansche vorgesehen, welche teilweise vom
Schaufelprofil durchdringt werden. Die zweite Komponente
dient zur Befestigung des Schaufelprofils und zur Bildung
eines Prallkühlelementes für die heißgasbeaufschlagte
Plattform.From
Ferner ist bekannt, dass Gasturbinen in vielen Bereichen zum Antrieb von Generatoren oder von Arbeitsmaschinen eingesetzt werden. 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. 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.Furthermore, it is known that gas turbines in many areas for Drive of generators or working machines used become. In this case, the energy content of a fuel to Generation of a rotational movement of a turbine shaft used. The fuel is in a combustion chamber burned, with compressed air from an air compressor is supplied. That in the combustion chamber through the combustion of the fuel produced under high pressure and under high pressure Temperature standing working medium is doing one of Burning chamber downstream turbine unit led where it relaxed work performance. To generate the rotational movement of the turbine shaft are in this case a number of usually in blade groups or blade rows of combined blades arranged, via a momentum transfer from the flow medium drive the turbine shaft. For guiding the flow medium in the turbine unit are also usually between adjacent blade rows with the turbine housing connected Leitschaufelreihen arranged. The turbine blades, in particular the guide vanes, usually have for the suitable guidance of the working medium a profiled, along a blade axis extended blade on, at the end for attachment of the turbine blade on the respective support body a transverse to Blade axis extending, in at least one end as Hook base trained platform is formed.
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 for thermodynamic reasons usually for particularly high outlet temperatures of the Combustion off and in the flowing into the turbine unit Working medium from about 1200 ° C to about 1300 ° C. designed. At such high temperatures, the components are the gas turbine, in particular the turbine blades, comparatively exposed to high thermal loads. Around Even with such operating conditions a high reliability and a long life of the respective components to ensure the affected components are common cooled formed.
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, in modern gas turbines, the turbine blades are common designed as a so-called hollow profile. The profiled Airfoil features in its interior too referred to as vane core cavities in which a Cooling medium can be performed. By the thus formed Coolant channels is thus an admission of the thermally stressed areas of the respective Blade with coolant allowed. A particularly cheap Cooling effect and thus a particularly high level of operational safety is achievable by the coolant channels a comparatively large area of space inside each of them Occupy the airfoil and adding the coolant as close as possible to the respective, the hot gas exposed Surface is guided. On the other hand, in such a design sufficient mechanical stability and resilience can ensure the particular turbine blade flowed through several channels, wherein inside the Blade profiles a plurality of acted upon by coolant, 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 efficiency reasons, the interpretation of such Turbine blade for a comparatively low consumption be desirable to coolant. Especially at an admission the turbine blade with comparatively hot Working medium is with only limited consumption of coolant a reliable cooling of the individual components of the turbine blade often only over a relatively thin-walled Execution of the individual components with comparatively low material requirement achievable. Especially by the operation the gas turbine in individual components of the turbine blade resulting thermal stresses and also occurring considerable mechanical stress lead to material fatigue or even material breakage. This can be a relatively unwanted use comparatively thick-walled structural parts require, for the then one correspondingly complex cooling with correspondingly extended Supply of coolant is to provide.
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, a turbine blade of the type mentioned above, on the one hand 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 according to the invention Airfoil in an end region one transverse to the blade axis extending hot gas platform and overlying a load platform are formed, wherein a mechanical Connection of the load platform with the hot gas platform exclusively takes place over the blade.
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 even at a thermally highly resilient turbine blade for a reliable cooling necessary consumption of coolant can be kept comparatively low by the structural parts are kept largely thin-walled. To do this in the In view of the comparatively strong mechanical stress the turbine blade without significant risk of To allow material damage, the thermal should Load absorption at the turbine blade consistently from the mechanical Lifting be kept separate. These are on Airfoil formed two platform segments, of which one, namely the hot gas platform, exclusively for receiving the thermal load and another, namely the Load platform, exclusively for the reception of 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, the sufficiently thick-walled to absorb the mechanical load should be executed, however, is by means of the hot gas platform from a direct thermal load shielded by the working medium and thus also in comparatively massive version without significant consumption Conserves coolant to a safe operating temperature. A high level of operational reliability in such an arrangement is achievable by just the comparatively thin-walled executed hot gas platform consistently free from occurring Heat stress is maintained. To the occurrence of thermal stress To prevent, the hot gas platform should as far 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 freely expandable design of the hot gas platform is achievable by these 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.According to the design of the hot gas platform is essentially kept free from mechanical stress. In order to make this possible, is the load platform in particular as regards their sizing advantageously designed in such a way that they are looking for a complete reception by the one Airfoil evolved around working fluid 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 with particularly low manufacturing and Material expenditure available by in advantageous Design the load platform in terms of their design on the one adapted to the given boundary conditions mechanical fixation required structural Components is limited. Such a minimalist running Design is favored by the load platform advantageously at one with respect to a working medium formed downstream edge of the airfoil. It is seen in the flow direction of the working medium rear edge of the airfoil in the suspension area to Extended loading platform, wherein in the flow direction of the Working fluid seen front area of the airfoil a major waiver of material-consuming, the load platform attributable structural components take place 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 Fix the turbine blade over the load platform on a Minimum required for a static determination Restriction points limited. This is indicated by the load platform advantageously a molded rib for Radialverhakung and on this patch rib for Axialverhakung on. In such an embodiment is sufficient for complete Making the static determination on the inside of the Turbine blade a single point of contact in the axial direction. If necessary, in addition, a rotation in Radial direction and / or a peripheral fixation on the outside be provided the turbine blade; these can by suitable means formed on the respective rib such as grooves or noses, be realized.
Die Turbinenschaufel ist vorzugsweise als Leitschaufel für eine Gasturbine, insbesondere für eine stationäre Gasturbine, ausgebildet.The turbine blade is preferably as a guide vane for a gas turbine, in particular 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 by the invention are in particular in that by the reduction of the mechanical connection the load platform with the hot gas platform on a connection exclusively on the blade a consistent Separation of to absorb the thermal load provided structural part of the for receiving the mechanical Load provided structural part is enabled. The respective ones Structural parts, namely the hot gas platform on the one hand and the load platform, on the other hand, can thus be specific designed to their actual purpose be, in particular, the hot gas platform freely expandable and can be made comparatively thin-walled. The Hot gas platform on the one hand and the load platform on the other In addition, they are completely independent in their design be executed from each other, in particular the Hot gas platform one different from the load platform Can have width and shape. The load platform can do this in the manner of a minimal solution in its shape 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 favored by the hot gas platform high thermal capacity also a particularly low production cost achievable with only 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 will be described with reference to a Drawing explained in more detail. In it shows the figure in Oblique 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
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
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.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. To form a Radialverhakung 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
Claims (5)
- Turbine blade/vane (1), having a profiled blade/vane aerofoil (2), which extends along a blade/vane axis (4) and on which are integrally formed, in an end region (8), a hot-gas platform (12) extending transversely to the blade/vane axis (4) and, above it, a load platform (14), characterized in that a mechanical connection between the load platform (14) and the hot-gas platform (12) takes place exclusively by means of the blade/vane aerofoil (2).
- Turbine blade/vane (1) according to Claim 1, characterized in that the load platform (14) is designed to absorb forces which are caused by a working medium flowing around the blade/vane aerofoil (2).
- Turbine blade/vane (1) according to Claim 1 or 2, characterized in that the load platform (14) is integrally formed in an attachment region on an edge (18) of the blade/vane aerofoil (2), which edge (18) is at the outlet flow end with respect to a working medium flowing around the blade/vane aerofoil (2).
- Turbine blade/vane (1) according to one of Claims 1 to 3, characterized in that the load platform (14) has a rib (22) integrally formed on it for a radial engagement with respect to the rotational axis of a turbine shaft and a rib (24) placed on the first rib (22) for axial engagement.
- Turbine blade/vane (1) according to one of Claims 1 to 4, characterized in that it is embodied as a guide vane for a gas turbine, in particular for a stationary gas turbine.
Priority Applications (6)
| 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 |
| AT02001267T ATE291677T1 (en) | 2002-01-17 | 2002-01-17 | TURBINE BLADE WITH A HOT GAS PLATFORM AND A LOAD PLATFORM |
| DE50202538T DE50202538D1 (en) | 2002-01-17 | 2002-01-17 | Turbine blade with a hot gas platform and a load 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 EP1329593A1 (en) | 2003-07-23 |
| EP1329593B1 true 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 |
Family Cites Families (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2500745A (en) | 1944-09-21 | 1950-03-14 | Gen Electric | Bucket structure for high-temperature turbomachines |
| US3610769A (en) * | 1970-06-08 | 1971-10-05 | Gen Motors Corp | Porous facing attachment |
| 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 |
| GB1605219A (en) * | 1975-10-02 | 1984-08-30 | Rolls Royce | Stator vane for a gas turbine engine |
| DE2643049A1 (en) * | 1975-10-14 | 1977-04-21 | United Technologies Corp | SHOVEL WITH COOLED PLATFORM FOR A FLOW MACHINE |
| 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 |
| US5249418A (en) * | 1991-09-16 | 1993-10-05 | General Electric Company | Gas turbine engine polygonal structural frame with axially curved panels |
| EP0550126A1 (en) | 1992-01-02 | 1993-07-07 | General Electric Company | Thrust augmentor heat shield |
| 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 |
| JP2002512334A (en) * | 1998-04-21 | 2002-04-23 | シーメンス アクチエンゲゼルシヤフト | Turbine blade |
| JP4339518B2 (en) * | 1998-08-31 | 2009-10-07 | シーメンス アクチエンゲゼルシヤフト | Turbine vane |
| 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 EP EP02001267A patent/EP1329593B1/en not_active Expired - Lifetime
- 2002-01-17 AT AT02001267T patent/ATE291677T1/en not_active IP Right Cessation
-
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
Also Published As
| Publication number | Publication date |
|---|---|
| EP1329593A1 (en) | 2003-07-23 |
| US20030133802A1 (en) | 2003-07-17 |
| ATE291677T1 (en) | 2005-04-15 |
| JP4249990B2 (en) | 2009-04-08 |
| US6887040B2 (en) | 2005-05-03 |
| CN1436920A (en) | 2003-08-20 |
| CN1313707C (en) | 2007-05-02 |
| DE50202538D1 (en) | 2005-04-28 |
| JP2003214109A (en) | 2003-07-30 |
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