EP2002085B1 - Guide blade segment of a thermal turbomachine, associated production method and thermal turbomachine - Google Patents
Guide blade segment of a thermal turbomachine, associated production method and thermal turbomachine Download PDFInfo
- Publication number
- EP2002085B1 EP2002085B1 EP07704682A EP07704682A EP2002085B1 EP 2002085 B1 EP2002085 B1 EP 2002085B1 EP 07704682 A EP07704682 A EP 07704682A EP 07704682 A EP07704682 A EP 07704682A EP 2002085 B1 EP2002085 B1 EP 2002085B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- platform
- blade segment
- stator blade
- fastening
- segment
- 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.)
- Not-in-force
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
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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
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
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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
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- F05D2230/238—Soldering
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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
- F05D2240/10—Stators
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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
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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
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
- Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles
Definitions
- the invention relates to a vane segment of a thermal turbomachine, in particular a gas turbine, with at least one profiled airfoil arranged on a platform, wherein a number of fastening elements for fastening the vane segment to an associated vane support is arranged on the substantially flat side of the platform facing away from the airfoil ,
- Gas turbines are used in many areas to drive generators or work machines.
- the energy content of a fuel is used to generate a rotational movement of a turbine shaft.
- the fuel is burned in a combustion chamber, compressed air being supplied by an air compressor.
- the working medium produced in the combustion chamber by the combustion of the fuel, under high pressure and at high temperature, is guided via a turbine unit connected downstream of the combustion chambers, where it relaxes in a work-performing manner.
- a number of rotor blades which are usually combined into groups of blades or rows of blades, are arranged thereon and drive the turbine shaft via a momentum transfer from the flow medium.
- To guide the flow medium in the turbine unit also commonly associated guide blade rows are arranged between adjacent blade rows with the turbine housing.
- the turbine blades, in particular the guide vanes usually have a profiled airfoil extending along a blade axis for suitable guidance of the working medium, at the end for attachment of the turbine blade to the respective one Carrier body is formed transversely to the blade axis extending platform. The top of the platform facing the airfoil forms an outer boundary surface for the hot gas flow channel of the gas turbine.
- the platform of the respective vane usually has a number of hook-like fastening elements on its underside or rear side facing away from the vane blade.
- a similar hook fastening of the axial gap of two vanes of adjacent turbine stages bridging guide ring is for example from the EP 1 505 259 A1 known, which is considered as the state of the art.
- the guide vane is inserted with its fastening elements or fastening hooks into corresponding receiving grooves of a Leitechaufelierin, aligned and then fixed in a suitable manner, eg with the help of Stemmblechen.
- the aforementioned guide ring is according to the EP 1 505 259 A1 nor provided an additional fastener, by means of which the hook of the guide ring in the vane support can be further tightened.
- the vane includes an inner platform to which a transversely extending flange is welded.
- the flange provided with a bore is fastened non-positively to a support structure by means of a screw extending through the bore.
- a plurality of guide vane blades which are adjacent to one another in the circumferential direction of the gas turbine, of a row of guide vanes may also be arranged on a common platform, so that the complete, hereinafter referred to as, vane segment designated blade unit by means of the platform-side mounting hook axially or circumferentially in the associated vane carrier is inserted.
- vane segment in the following, and in particular in the claims, always include the case of a single vane with only one blade, unless this is expressly excluded.
- the vane or the entire vane segment is made by a casting process so that the platform and platform-side fasteners are integral, co-molded components of the vane or vane segment.
- a so-called wax model of the blade or the blade segment is manufactured, which is then provided by repeated immersion in a ceramic material with a ceramic coating. Once this has a sufficient thickness, the model provided with the ceramic coating wax is burned out, whereby the ceramic solidifies and the liquefied or evaporated wax is removed.
- the ceramic negative mold obtained in this way is finally filled with the metallic blade material. After the solidification of the melt and the removal of the shell-like outer casting mold, ceramic core elements still remaining in the blade body, which were previously introduced to form cavities or cooling channels integrated in the blade body, are removed by leaching with caustic soda or the like.
- the hook-like protruding from the platform fasteners cause in the manufacturing process in several respects difficulties.
- the production of the wax model is relatively cumbersome because the formation of the fastening hook comparatively complex wax tools with a variety of so-called mask elements or slide are required.
- the attachment hooks are problem areas, since the undercuts in the construction of the shell mold can be sanded poorly and in the subsequent casting process due to their exposed position always to form Lunkerfeldern, d. H. tend to material defects caused by heat shrinkage in the cooling component.
- the invention is therefore an object of the invention to provide a vane segment of the type mentioned above, which is designed for simple and cost-effective production while avoiding casting problem zones for a particularly reliable and secure attachment to an associated vane carrier. Furthermore, a method suitable for the production of the vane segment should be specified.
- the object is achieved in that at least one section of at least one of the fastening elements is a separately manufactured component connected fixedly to the side of the platform facing away from the airfoil.
- the invention is based on the consideration that the casting material for the vane segment should usually be optimized for a high high-temperature strength, so as to achieve a high operational safety and structural stability and the longest possible life of the directly exposed to the hot working medium sections, in particular the to ensure the flow channel of the gas turbine in the projecting blades and the flow channel facing the top of the platform.
- the casting material for the vane segment should usually be optimized for a high high-temperature strength, so as to achieve a high operational safety and structural stability and the longest possible life of the directly exposed to the hot working medium sections, in particular the to ensure the flow channel of the gas turbine in the projecting blades and the flow channel facing the top of the platform.
- the functionally and structurally decoupled from the rest of the blade segment fasteners including the hook which are exposed on the one hand by the upstream platform only comparatively low thermal stress, however
- relatively high mechanical loads and bearing or holding forces must absorb.
- the respective fastening element comprises a connecting element provided with a bearing surface.
- the connecting element is expediently designed in the manner of a flat connecting plate with a flat bearing surface.
- the connecting element or the connecting plate is sunk in a corresponding recess of the platform, in particular by this a simple to produce Leitschaufelsegment can be specified, since the difficult to access the Gußher ein geometry of the Leitschaufelsegmenthaken has been eliminated.
- the respective fastening element comprises a protruding from the platform, angularly bent fastening hook, which is adapted in its shape and contour to the associated receiving groove of a vane carrier.
- a possible alternative to this is a substantially straight profile piece, which is insertable into a polygonal receptacle in the turbine housing.
- the connecting element is positively fixed in a matched to the shape of the connecting element depression or groove of the platform.
- a positive connection for example, given by the fact that the platform in the edge region of the recess or the groove has a number of projections which engage around the connecting element in each case on its side facing away from the support surface.
- the connecting element is laterally inserted into the recess or the receiving groove of the platform and then fixed in a suitable manner, for example, positive, non-positive and / or cohesive against lateral slipping. Because the connection forces are essentially by the projections positively embracing the connecting element are received, the additional fixation must be designed only for relatively low loads.
- a cohesive connection preferably by soldering or welding, may be provided.
- the respective fastener for a high mechanical strength is made integrally from a one-component workpiece.
- the attachment hook can be milled or extruded as a straight profile piece and bent in a second operation in the required radius.
- the fastening element is preferably produced from a material which is less resistant to high temperatures but tougher than the rest of the stator blade segment.
- the guide vane or vane segment has a plurality of fasteners for secure attachment to the vane support, and preferably each of the fastener elements is a separately fabricated and configured component as described above.
- a gas turbine typically includes a plurality of turbine stages, each of the turbine stages including a plurality of stator vanes circumferentially disposed around the flow passage on the turbine housing, which in their entirety form a row of vanes.
- a plurality of adjacent guide vanes can be combined to form a vane segment or a "multiple".
- Each of the guide vanes or each vane segment expediently has a platform with hook-like fastening elements, wherein the specifications for the hooking profile in terms of bending angle and / or bending radius usually vary with the mounting position, ie in particular depend on the turbine stage or the guide vane row.
- Particularly advantageous in this context is a standardized or standardized design of the connecting elements and the corresponding platform-side receptacles or depressions, by means of which the fastening elements are connected to the respective platform.
- the respective profile piece, from which arises by bending the fastening hooks can look the same in the original "raw state" for all fasteners.
- One and the same fastener can thus be used in principle for all turbine stages of a turbine; only the bending radius and / or the bending angle of the fastening hook must be adapted to the respective place of use or to the respective intended use.
- the bending of the profile piece takes place before the connection of the connecting element with the platform of the vane segment, because this facilitates the handling and the implementation of the bending process.
- vane 2 comprises a extending in the direction of the blade axis 4 profiled airfoil 6, to which in the region of the blade root a substantially transverse to the blade axis 4 oriented platform 8 is formed.
- the "upper side 10" of the platform 8, which is oriented toward the blade leaf 6, forms an outer boundary of a hot gas-carrying flow channel in a gas turbine (not shown).
- substantially flat "bottom” 12 or back of the platform 8 is a number of hook-like fasteners 14, by means of which the guide vane 2 in an associated vane support (not shown) mounted on the turbine housing / is attached.
- the fasteners 14 visible, which is mounted with respect to the axial direction 16 near the trailing edge of the airfoil 6; another fastener is disposed in the vicinity of the leading edge not shown here.
- the fastener 14 is specifically adapted to the associated with the entanglement in the vane support mechanical loads in simple and inexpensive held.
- the fastening element 14 is designed as a separate, independent of the remaining guide blade 2 and only subsequently connected to her component, wherein the material used for the fastener 14 is less resistant to high temperatures, but is more tough than the material from which the blade 6 and the Platform 8 are made.
- the fastening element 14 comprises in addition to a projecting from the back 12 of the platform 8, approximately at right angles angled mounting hook 18 thereon a molded connection plate 20 with a rectangular base.
- the connecting plate 20 is positively fixed in an associated recess 21 of the platform 8. With its flat bearing surface 22, the connecting plate 20 is flat on the base of the recess 21.
- the depth of the recess 21 corresponds to the thickness of the connecting plate 20, so that there is an offset-free transition in the edge region to the platform surface.
- two opposite longitudinal edges 24 of the connecting plate 20 are chamfered such that they are encompassed or surrounded by complementary thereto, parallel to the longitudinal edges 24 extending projections 26 at the edge of the platform-side recess 21.
- the projections 26 thus form a perpendicular to the plane extending guide and mounting rail into which the connecting plate 20 for mounting the fastener 14th is inserted.
- additional fixing means not shown here may be provided. A shift in the other two spatial directions, so on the one hand parallel to the blade axis 4 and the other in the axial direction 16 is excluded by the positive attachment.
- fastener 14 is analogous to the fastener 14 after FIG. 1 arranged with its connecting plate 20 sunk in an associated recess 21 of the platform 8, but not fixed in contrast to this form fit. Rather, the connecting plate 20 is connected by a number of solder pads or solder joints 28 between the bearing surfaces 22 cohesively with the platform 8. For the required Hochtemperaturlötung a large number of solders / heat treatments are commercially available, the geometry of the solder joints should be carried out expediently full-scale. The selection of the soldering process is essentially influenced by the operating conditions at the soldering, the material pairing and the compatibility with other heat treatment requirements.
- FIG. 3 an alternative to the invention variant in which only an outer portion 30 of the fastener 14 is a separately manufactured component, the rest of the part, however, integrally molded to the platform 8 and is cast together with her.
- the effectively as an "adapter" effective outer section 30 has Similar to a closure cap for a bottle or tube, a skirt 32 enclosing the platform-side component of the fastener 14 at its outer end.
- the dimensions are chosen such that prior to the introduction of a joining agent results in a loose, play-afflicted seat, which can be adapted to the present on the respective site geometric requirements and thereby compensates for manufacturing tolerances and fluctuations.
- the two components of the fastening element 14 are connected to one another by a soldering compound 36 introduced into the intermediate space 34 and subsequently solidified.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
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Abstract
Description
Leitschaufelsegment einer thermischen Strömungsmaschine, zugehöriges Herstellungsverfahren sowie thermische StrömungsmaschineGuide vane segment of a thermal turbomachine, associated production method and thermal turbomachine
Die Erfindung betrifft ein Leitschaufelsegment einer thermischen Strömungsmaschine, insbesondere einer Gasturbine, mit mindestens einem auf einer Plattform angeordneten profilierten Schaufelblatt, wobei an der im wesentlichen ebenen, dem Schaufelblatt abgewandten Seite der Plattform eine Anzahl von Befestigungselementen zur Befestigung des Leitschaufelsegmentes an einem zugeordneten Leitschaufelträger angeordnet ist.The invention relates to a vane segment of a thermal turbomachine, in particular a gas turbine, with at least one profiled airfoil arranged on a platform, wherein a number of fastening elements for fastening the vane segment to an associated vane support is arranged on the substantially flat side of the platform facing away from the 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 über eine der Brennkammern nachgeschaltete Turbineneinheit geführt, wo es sich arbeitsleistend entspannt.Gas turbines are used in many areas to drive generators or work machines. In this case, the energy content of a fuel is used to generate a rotational movement of a turbine shaft. For this purpose, the fuel is burned in a combustion chamber, compressed air being supplied by an air compressor. The working medium produced in the combustion chamber by the combustion of the fuel, under high pressure and at high temperature, is guided via a turbine unit connected downstream of the combustion chambers, where it relaxes in a work-performing manner.
Zur Erzeugung der Rotationsbewegung der Turbinenwelle sind an diese eine Anzahl von üblicherweise zu 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 üblicherweise zur geeigneten Führung des Arbeitsmediums ein profiliertes, entlang einer Schaufelachse erstrecktes Schaufelblatt auf, an das endseitig zur Befestigung der Turbinenschaufel am jeweiligen Trägerkörper eine sich quer zur Schaufelachse erstreckende Plattform angeformt ist. Die dem Schaufelblatt zugewandte Oberseite der Plattform bildet eine äußere Begrenzungsfläche für den Heißgas führenden Strömungskanal der Gasturbine.In order to generate the rotational movement of the turbine shaft, a number of rotor blades, which are usually combined into groups of blades or rows of blades, are arranged thereon and drive the turbine shaft via a momentum transfer from the flow medium. To guide the flow medium in the turbine unit also commonly associated guide blade rows are arranged between adjacent blade rows with the turbine housing. The turbine blades, in particular the guide vanes, usually have a profiled airfoil extending along a blade axis for suitable guidance of the working medium, at the end for attachment of the turbine blade to the respective one Carrier body is formed transversely to the blade axis extending platform. The top of the platform facing the airfoil forms an outer boundary surface for the hot gas flow channel of the gas turbine.
Zur einfachen und sicheren Montage und Fixierung an einem mit dem Turbinengehäuse verbundenen Leitschaufelträger weist die Plattform der jeweiligen Leitschaufel üblicherweise an ihrer vom Schaufelblatt abgewandten Unterseite oder Rückseite eine Anzahl von hakenartigen Befestigungselementen auf. Eine gleichartige Hakenbefestigung eines den axialen Zwischenraum von zwei Leitschaufeln benachbarter Turbinenatufen überbrückenden Führungsrings ist beispielsweise aus der
Zudem ist aus der
Zur Verringerung des Herstellungs- oder Montageaufwandes können auch mehrere von in Umfangsrichtung der Gasturbine, zueinander benachbarten Leitschaufelblättern einer Leitschaufelreihe auf einer gemeinsamen Plattform angeordnet sein, so dass die komplette, im Folgenden als Leitschaufelsegment bezeichnete Schaufeleinheit mit Hilfe der plattformseitigen Befestigungehaken axial oder in Umfangsrichtung in den zugehörigen Leitschaufelträger einschiebbar ist. Zur Vereinfachung der Sprechweise soll der Begriff "Leitschaufelsegment" im Folgenden, insbesondere auch in den Ansprüchen, immer auch den Fall einer einzelnen Leitschaufel mit nur einem schaufelblatt beinhalten, sofern dies nicht ausdrücklich ausgeschlossen ist.In order to reduce the manufacturing or assembly costs, a plurality of guide vane blades, which are adjacent to one another in the circumferential direction of the gas turbine, of a row of guide vanes may also be arranged on a common platform, so that the complete, hereinafter referred to as, vane segment designated blade unit by means of the platform-side mounting hook axially or circumferentially in the associated vane carrier is inserted. To simplify the manner of speaking, the term "vane segment" in the following, and in particular in the claims, always include the case of a single vane with only one blade, unless this is expressly excluded.
Üblicherweise wird die Leitschaufel oder das komplette Leitschaufelsegment im Rahmen eines Gießverfahrens hergestellt, so dass die Plattform und die plattformseitigen Befestigungselemente integrale, mitgegossene Bestandteile der Leitschaufel oder des Leitschaufelsegmentes sind. Dazu wird in einem ersten Schritt ein so genanntes Wachsmodell der Schaufel oder des Schaufelsegmentes gefertigt, das anschließend durch wiederholtes Eintauchen in eine Keramikmasse mit einem Keramiküberzug versehen wird. Sobald dieser eine ausreichende Dicke aufweist, wird das mit dem Keramiküberzug versehene Wachsmodell ausgebrannt, wobei sich die Keramik verfestigt und das verflüssigte oder verdampfte Wachs entfernt wird. Die auf diese Weise erhaltene Negativ-Gießform aus Keramik wird schließlich mit dem metallischen Schaufelwerkstoff ausgegossen. Nach dem Erstarren der Schmelze und dem Entfernen der schalenartigen äußeren Gießform werden gegebenenfalls noch im Schaufelkörper verbliebene keramische Kernelemente, welche zuvor zur Ausbildung von in den Schaufelkörper integrierten Hohlräumen oder Kühlkanälen eingebracht waren, durch Auslaugen mit Natronlauge oder dergleichen entfernt.Typically, the vane or the entire vane segment is made by a casting process so that the platform and platform-side fasteners are integral, co-molded components of the vane or vane segment. For this purpose, in a first step, a so-called wax model of the blade or the blade segment is manufactured, which is then provided by repeated immersion in a ceramic material with a ceramic coating. Once this has a sufficient thickness, the model provided with the ceramic coating wax is burned out, whereby the ceramic solidifies and the liquefied or evaporated wax is removed. The ceramic negative mold obtained in this way is finally filled with the metallic blade material. After the solidification of the melt and the removal of the shell-like outer casting mold, ceramic core elements still remaining in the blade body, which were previously introduced to form cavities or cooling channels integrated in the blade body, are removed by leaching with caustic soda or the like.
Die hakenartig von der Plattform abstehenden Befestigungselemente verursachen im Rahmen des Fertigungsprozesses in mehrfacher Hinsicht Schwierigkeiten. Bereits die Herstellung des Wachsmodells ist relativ umständlich, da zur Ausbildung der Befestigungshaken vergleichsweise komplexe Wachswerkzeuge mit einer Vielzahl so genannter Maskenelemente oder Schieber erforderlich sind. Auch in gießtechnischer Hinsicht stellen die Befestigungshaken Problembereiche dar, da die Hinterschnitte beim Aufbau der Formschale nur schlecht besandet werden können und beim anschließenden Gießvorgang aufgrund ihrer exponierten Lage immer zur Ausbildung von Lunkerfeldern, d. h. zu durch Wärmeschrumpfung im auskühlenden Bauteil verursachten Materialfehlern, neigen.The hook-like protruding from the platform fasteners cause in the manufacturing process in several respects difficulties. Already the production of the wax model is relatively cumbersome because the formation of the fastening hook comparatively complex wax tools with a variety of so-called mask elements or slide are required. Also in terms of casting technology, the attachment hooks are problem areas, since the undercuts in the construction of the shell mold can be sanded poorly and in the subsequent casting process due to their exposed position always to form Lunkerfeldern, d. H. tend to material defects caused by heat shrinkage in the cooling component.
Zudem ist es häufig schwierig, die für einen passgenauen Sitz des Befestigungshakens in der zugehörigen Aufnahmenut erforderlichen Toleranzen einzuhalten, insbesondere bei Ausführungsvarianten mit verhältnismäßig kleinen Krümmungsradien. Damit können an dieser Stelle im späteren Betrieb der Turbine auch Abdichtungsprobleme auftreten. Schließlich hat sich gezeigt, dass die Befestigungshaken oftmals auch in Bezug auf ihr Verschleißverhalten bei betrieblicher Beanspruchung und in Bezug auf die zulässige maximale Lastaufnahme Schwachstellen der Turbinenschaufeln darstellen.In addition, it is often difficult to comply with the tolerances required for a snug fit of the mounting hook in the associated receiving groove, especially in embodiments with relatively small radii of curvature. Thus, sealing problems can occur at this point in the later operation of the turbine. Finally, it has been found that the fastening hooks often also represent weaknesses of the turbine blades with respect to their wear behavior under operational load and with regard to the permissible maximum load absorption.
Der Erfindung liegt daher die Aufgabe zugrunde, ein Leitschaufelsegment der eingangs genannten Art anzugeben, der bei einfach und kostengünstig gehaltener Fertigung unter Vermeidung gießtechnischer Problemzonen für eine besonders zuverlässige und sichere Befestigung an einem zugeordneten Leitschaufelträger ausgelegt ist. Weiterhin soll ein zur Herstellung des Leitschaufelsegmentes geeignetes Verfahren angegeben werden.The invention is therefore an object of the invention to provide a vane segment of the type mentioned above, which is designed for simple and cost-effective production while avoiding casting problem zones for a particularly reliable and secure attachment to an associated vane carrier. Furthermore, a method suitable for the production of the vane segment should be specified.
In Bezug auf das Leitschaufelsegment wird die Aufgabe dadurch gelöst, dass zumindest ein Teilstück mindestens eines der Befestigungselemente ein fest mit der dem Schaufelblatt abgewandten Seite der Plattform verbundenes, separat hergestelltes Bauteil ist.With regard to the vane segment, the object is achieved in that at least one section of at least one of the fastening elements is a separately manufactured component connected fixedly to the side of the platform facing away from the airfoil.
Die Erfindung geht dabei von der Überlegung aus, dass der Gusswerkstoff für das Leitschaufelsegment üblicherweise auf eine hohe Hochtemperaturfestigkeit hin optimiert sein sollte, um so eine hohe betriebliche Sicherheit und strukturelle Stabilität sowie eine möglichst lange Lebensdauer der unmittelbar dem heißen Arbeitsmedium ausgesetzten Teilbereiche, insbesondere der in den Strömungskanal der Gasturbine hineinragenden Schaufelblätter und der dem Strömungskanal zugewandten Oberseite der Plattform, zu gewährleisten. Eine derartige Auslegung ist jedoch, wie sich nunmehr herausgestellt hat, möglicherweise nicht optimal für die funktionell und auch strukturell vom restlichen Schaufelsegment entkoppelten Befestigungselemente einschließlich der Haken, die einerseits durch die vorgelagerte Plattform einer nur vergleichsweise geringen thermischen Belastung ausgesetzt sind, die jedoch andererseits relativ hohe mechanische Belastungen und Lager-oder Haltekräfte aufnehmen müssen. Zur Vermeidung der bislang bestehenden Nachteile wird gemäß dem hier vorgestellten Konzept vorgeschlagen, die funktionell vom restlichen Leitschaufelsegment entkoppelten Befestigungselemente, sprich den bzw. die Befestigungshaken, separat unter Verwendung eines konsequent an die jeweilige technische Funktion angepassten Werkstoffes herzustellen und erst im Anschluss daran mit Hilfe eines geeigneten Fügeverfahrens mit dem restlichen Befestigungselement oder mit der Plattform des beispielsweise in bewährter Gießtechnik hergestellten, d. h. integral ausgeführten, restlichen Leitschaufelsegmentes zu verbinden.The invention is based on the consideration that the casting material for the vane segment should usually be optimized for a high high-temperature strength, so as to achieve a high operational safety and structural stability and the longest possible life of the directly exposed to the hot working medium sections, in particular the to ensure the flow channel of the gas turbine in the projecting blades and the flow channel facing the top of the platform. However, such an interpretation is, as has now been found, may not be optimal for the functionally and structurally decoupled from the rest of the blade segment fasteners including the hook, which are exposed on the one hand by the upstream platform only comparatively low thermal stress, however On the other hand, relatively high mechanical loads and bearing or holding forces must absorb. In order to avoid the disadvantages existing up to now, it is proposed according to the concept presented here to separately produce the fastening elements that are functionally decoupled from the remainder of the stator blade segment, ie the fastening hook (s), using a material which has been consistently adapted to the respective technical function and only then with the aid of a suitable joining method with the rest of the fastener or with the platform of the example produced in the proven casting technique, ie integrally running, to connect the remaining vane segment.
Zur dauerhaften Verbindung mit der Plattform der Leitschaufel oder des Leitschaufelsegmentes umfasst das jeweilige Befestigungselement ein mit einer Auflagefläche versehenes Verbindungselement. Für eine besonders gleichmäßige Verteilung von Auflage- oder Verbindungskräften und für eine präzise Ausrichtbarkeit des Befestigungselementes relativ zur Plattform ist das Verbindungselement zweckmäßigerweise in der Art einer flachen Verbindungsplatte mit einer ebenen Auflagefläche ausgeführt. Zur Realisierung einer geringen Einbauhöhe ist das Verbindungselement oder die Verbindungsplatte versenkt in einer korrespondierenden Vertiefung der Plattform angeordnet, wobei insbesondere hierdurch eine einfach herzustellendes Leitschaufelsegment angegeben werden kann, da die für die Gußherstellung schwer zugängliche Geometrie der Leitschaufelsegmenthaken eliminiert worden ist.For permanent connection to the platform of the guide vane or the vane segment, the respective fastening element comprises a connecting element provided with a bearing surface. For a particularly uniform distribution of support or connecting forces and for precise alignment of the fastener relative to the platform, the connecting element is expediently designed in the manner of a flat connecting plate with a flat bearing surface. To realize a low installation height, the connecting element or the connecting plate is sunk in a corresponding recess of the platform, in particular by this a simple to produce Leitschaufelsegment can be specified, since the difficult to access the Gußherstellung geometry of the Leitschaufelsegmenthaken has been eliminated.
Bei dieser zumindest zweikomponentigen Ausführung des Leitschaufelsegmentes kann nicht nur die Werkstoffauswahl für die Befestigungselemente im Hinblick auf die Anforderungen der "verhakten" Befestigung am Leitschaufelträger optimiert werden, zum Beispiel in Bezug auf Lastaufnahme, Verschleiß und/oder Dichtung; darüber hinaus entfallen beispielsweise auch die eingangs geschilderten Schwierigkeiten bei der Herstellung des Wachsmodells oder beim Gießvorgang. Trotz des mit dem Fügevorgang einhergehenden zusätzlichen Fertigungsschrittes wird die Fertigung des Leitschaufelsegmentes damit insgesamt wesentlich einfacher.In this at least two-component design of the vane segment, not only the material selection for the fasteners with regard to the requirements of the "hooked" attachment to the vane support can be optimized, for example in terms of load bearing, wear and / or seal; In addition, for example, eliminates the difficulties described in the preparation of the wax model or during the casting process. Despite the With the joining process associated additional manufacturing step, the production of the vane segment is thus much easier.
In besonders zweckmäßiger Ausgestaltung umfasst das jeweilige Befestigungselement einen von der Plattform abstehenden, winklig abgebogenen Befestigungshaken, der in seiner Formgebung und Kontur an die zugeordnete Aufnahmenut eines Leitschaufelträgers angepasst ist. Eine mögliche Alternative hierzu stellt ein im Wesentlichen gerades Profilstück dar, das in eine polygonartige Aufnahme im Turbinengehäuse einführbar ist.In a particularly advantageous embodiment, the respective fastening element comprises a protruding from the platform, angularly bent fastening hook, which is adapted in its shape and contour to the associated receiving groove of a vane carrier. A possible alternative to this is a substantially straight profile piece, which is insertable into a polygonal receptacle in the turbine housing.
Vorteilhafterweise ist das Verbindungselement formschlüssig in einer auf die Form des Verbindungselementes abgestimmten Vertiefung oder Nut der Plattform fixiert. Eine derart formschlüssige Verbindung ist beispielsweise dadurch gegeben, dass die Plattform im Randbereich der Vertiefung oder der Nut eine Anzahl von Vorsprüngen aufweist, die das Verbindungselement jeweils an seiner der Auflagefläche abgewandten Seite umgreifen. Zur Montage des Befestigungselementes an der Plattform wird dann zum Beispiel das Verbindungselement seitlich in die Vertiefung oder die Aufnahmenut der Plattform eingeschoben und anschließend auf geeignete Weise, zum Beispiel form-, kraft- und/oder stoffschlüssig, gegen seitliches Wegrutschen fixiert. Da die Verbindungskräfte im Wesentlichen durch die das Verbindungselement formschlüssig umgreifenden Vorsprünge aufgenommen werden, muss die zusätzliche Fixierung lediglich für verhältnismäßig geringe Belastungen ausgelegt sein.Advantageously, the connecting element is positively fixed in a matched to the shape of the connecting element depression or groove of the platform. Such a positive connection, for example, given by the fact that the platform in the edge region of the recess or the groove has a number of projections which engage around the connecting element in each case on its side facing away from the support surface. For mounting the fastening element to the platform then, for example, the connecting element is laterally inserted into the recess or the receiving groove of the platform and then fixed in a suitable manner, for example, positive, non-positive and / or cohesive against lateral slipping. Because the connection forces are essentially by the projections positively embracing the connecting element are received, the additional fixation must be designed only for relatively low loads.
Anstelle der formschlüssigen Verbindung zwischen dem Verbindungselement und der Plattform oder zusätzlich dazu kann auch eine stoffschlüssige Verbindung, vorzugsweise durch Löten oder Verschweißen, vorgesehen sein.Instead of the positive connection between the connecting element and the platform or in addition thereto, a cohesive connection, preferably by soldering or welding, may be provided.
Vorzugsweise wird das jeweilige Befestigungselement für eine hohe mechanische Belastbarkeit integral aus einem einkomponentigen Werkstück hergestellt. Dabei kann zum Beispiel der Befestigungshaken als gerades Profilstück gefräst oder stranggepresst und in einem zweiten Arbeitsgang in den erforderlichen Radius gebogen werden. Vorzugsweise ist das Befestigungselement aus einem im Vergleich zum restlichen Leitschaufelsegment weniger hochtemperaturfesten, dafür aber zäheren Werkstoff hergestellt.Preferably, the respective fastener for a high mechanical strength is made integrally from a one-component workpiece. In this case, for example, the attachment hook can be milled or extruded as a straight profile piece and bent in a second operation in the required radius. The fastening element is preferably produced from a material which is less resistant to high temperatures but tougher than the rest of the stator blade segment.
Zweckmäßigerweise weist die Leitschaufel oder das Leitschaufelsegment für eine sichere Befestigung am Leitschaufelträger eine Mehrzahl von Befestigungselementen auf, wobei vorzugsweise jedes der Befestigungselemente ein in der oben beschriebenen Weise separat hergestelltes und ausgestaltetes Bauteil ist.Conveniently, the guide vane or vane segment has a plurality of fasteners for secure attachment to the vane support, and preferably each of the fastener elements is a separately fabricated and configured component as described above.
Üblicherweise weist eine Gasturbine mehrere Turbinenstufen auf, wobei jede der Turbinenstufen eine Vielzahl von in Umfangsrichtung um den Strömungskanal herum am Turbinengehäuse angeordneten Leitschaufeln umfasst, die in ihrer Gesamtheit eine Leitschaufelreihe bilden. Dabei können, wie bereits eingangs erwähnt, jeweils mehrere benachbarte Leitschaufeln zu einem Leitschaufelsegment oder einem "Mehrling" zusammengefasst sein. Jede der Leitschaufeln oder jedes Leitschaufelsegment weist zweckmäßigerweise eine Plattform mit hakenartigen Befestigungselementen auf, wobei die Vorgaben für das Verhakungsprofil hinsichtlich Biegewinkel und/oder Biegeradius in der Regel mit der Einbauposition variieren, d. h. insbesondere von der Turbinenstufe beziehungsweise von der Leitschaufelreihe abhängen. Besonders vorteilhaft ist in diesem Zusammenhang eine normierte oder standardisierte Ausführung der Verbindungselemente und der korrespondierenden plattformseitigen Aufnahmen oder Vertiefungen, mittels derer die Befestigungselemente mit der jeweiligen Plattform verbunden sind. Auch das jeweilige Profilstück, aus dem durch Biegen der Befestigungshaken entsteht, kann im ursprünglichen "Rohzustand" für alle Befestigungselemente gleich aussehen. Ein und dasselbe Befestigungselement kann damit im Prinzip für alle Turbinenstufen einer Turbine verwendet werden; lediglich der Biegeradius und/oder der Biegewinkel des Befestigungshakens muss an den jeweiligen Einsatzort bzw. an den jeweiligen Verwendungszweck angepasst werden. Zweckmäßigerweise erfolgt das Biegen des Profilstücks noch vor der Verbindung des Verbindungselements mit der Plattform des Leitschaufelsegmentes, weil dies die Handhabung und die Durchführung des Biegevorganges erleichtert. Es ist im Prinzip aber auch möglich, erst nach der Verbindung von Befestigungselement und Plattform den Befestigungshaken in die gewünschte oder erforderliche Form zu biegen.Typically, a gas turbine includes a plurality of turbine stages, each of the turbine stages including a plurality of stator vanes circumferentially disposed around the flow passage on the turbine housing, which in their entirety form a row of vanes. In this case, as already mentioned, in each case a plurality of adjacent guide vanes can be combined to form a vane segment or a "multiple". Each of the guide vanes or each vane segment expediently has a platform with hook-like fastening elements, wherein the specifications for the hooking profile in terms of bending angle and / or bending radius usually vary with the mounting position, ie in particular depend on the turbine stage or the guide vane row. Particularly advantageous in this context is a standardized or standardized design of the connecting elements and the corresponding platform-side receptacles or depressions, by means of which the fastening elements are connected to the respective platform. Also, the respective profile piece, from which arises by bending the fastening hooks, can look the same in the original "raw state" for all fasteners. One and the same fastener can thus be used in principle for all turbine stages of a turbine; only the bending radius and / or the bending angle of the fastening hook must be adapted to the respective place of use or to the respective intended use. Conveniently, the bending of the profile piece takes place before the connection of the connecting element with the platform of the vane segment, because this facilitates the handling and the implementation of the bending process. In principle, however, it is also possible to bend the fastening hook into the desired or required shape only after the connection of the fastening element and the platform.
Die mit der Erfindung erzielten Vorteile bestehen insbesondere in folgenden Punkten:
- Die Werkstoffauswahl für das Befestigungselement kann auf die Verhakungsanforderungen hin optimiert werden, insbesondere in Bezug auf Lastaufnahme, Verschleiß und/oder Dichtung.
- Die Fertigung der Leitschaufel oder des Leitschaufelsegmentes wird insgesamt wesentlich einfacher.
- Toleranzen können einfacher eingestellt bzw. eingehalten werden.
- Ein Verhakungsprofil kann als Standard für weitgehend alle Turbinenstufen/Leistungsklassen verwandt und durch unterschiedliche Biegeradien an den jeweiligen Verwendungszweck angepasst werden.
- Im Gussteil werden gießtechnische Problemzonen vermieden.
- Die Wachswerkzeuge für die Leitschaufeln werden einfacher, haben weniger Einsätze oder Schieber.
- The material selection for the fastener can be optimized to the Verhakungsanforderungen out, especially in terms of load bearing, wear and / or seal.
- The manufacture of the vane or the vane segment is much easier overall.
- Tolerances can be set or adhered to more easily.
- A hooking profile can be used as a standard for almost all turbine stages / performance classes and adapted to the respective intended use by different bending radii.
- Casting problem areas are avoided in the casting.
- The wax tools for the vanes are simpler, have fewer inserts or slides.
Die Vorteile wiegen bei einem Leitschaufelsegment mit mehreren Schaufelblättern auf einer gemeinsamen Plattform noch stärker als bei einer Einzelschaufel.The advantages weigh even more in a vane segment with multiple blades on a common platform than a single blade.
Ein Ausführungsbeispiel der Erfindung wird anhand einer Zeichnung näher erläutert. Darin zeigen:
- FIG 1
- eine Leitschaufel mit einem Befestigungselement ge- mäß einer ersten Ausführungsform,
- FIG 2
- eine Leitschaufel mit einem Befestigungselement ge- mäß einer zweiten Ausführungsform, und
- FIG 3
- eine Leitschaufel mit einem zur Erfindung alternativen Befestigungselement.
- FIG. 1
- a guide vane with a fastening element according to a first embodiment,
- FIG. 2
- a guide blade with a fastening element according to a second embodiment, and
- FIG. 3
- a vane with an alternative to the invention fastener.
Gleiche Teile sind in allen Figuren mit denselben Bezugszeichen versehen.Identical parts are provided with the same reference numerals in all figures.
Die in
Das Befestigungselement 14 ist bei einfach und kostengünstig gehaltener Fertigung spezifisch an die mit der Verhakung im Leitschaufelträger verbundenen mechanischen Belastungen angepasst. Dazu ist das Befestigungselement 14 als separates, unabhängig von der restlichen Leitschaufel 2 hergestelltes und erst nachträglich mit ihr verbundenes Bauteil ausgeführt, wobei der für das Befestigungselement 14 eingesetzte Werkstoff weniger hochtemperaturbeständig, dafür aber zäher ist als der Werkstoff, aus dem das Schaufelblatt 6 und die Plattform 8 hergestellt sind.The
Das Befestigungselement 14 umfasst neben einem von der Rückseite 12 der Plattform 8 abstehenden, annähernd rechtwinklig abgewinkelten Befestigungshaken 18 eine daran angeformte Verbindungsplatte 20 mit rechteckiger Grundfläche. Die Verbindungsplatte 20 ist formschlüssig in einer zugeordneten Vertiefung 21 der Plattform 8 fixiert. Mit ihrer ebenen Auflagefläche 22 liegt die Verbindungsplatte 20 plan auf der Grundfläche der Vertiefung 21 auf. Die Tiefe der Vertiefung 21 entspricht der Dicke der Verbindungsplatte 20, so dass sich im Randgebiet zur Plattformoberfläche ein versatzfreier Übergang ergibt.The
Zur Realisierung der formschlüssigen Verbindung sind im Ausführungsbeispiel gemäß
Das in
Schließlich zeigt
Claims (10)
- Stator blade segment (2) for a thermal turbomachine,
with at least one profiled blade airfoil (6) which is arranged on a platform (8),
wherein a number of fastening elements (14) for fastening the stator blade segment (2) on an associated stator blade carrier are provided on the essentially flat side of the platform (8) which faces away from the blade airfoil (6),
wherein at least one of the fastening elements (14) is a separately produced component which is connected in a fixed manner to the side of the platform (8) which faces away from the blade airfoil (6),
characterized in that
the respective fastening element (14) comprises a fastening hook (18) which projects from the platform (8), and a connecting element which by a bearing surface (22) is recessed in the platform (8). - Stator blade segment (2) according to Claim 1,
in which the respective fastening element (14) is produced integrally from a single-component workpiece. - Stator blade segment (2) according to either of Claims 1 or 2,
in which the respective fastening element (14) is produced from a material which is tougher in comparison to the platform (8) and/or to the blade airfoil (6). - Stator blade segment (2) according to one of Claims 1 to 3,
in which the connecting element is a connecting plate (20). - Stator blade segment (2) according to one of Claims 1 to 4,
in which the connecting element is fixed in a positive-locking manner in a recess (21) or slot of the platform (8) which is matched to the shape of the connecting element. - Stator blade segment (2) according to Claim 5,
in which the platform (8) in the edge region of the recess (21) or of the slot has a number of projections (26) which grip round the connecting element in each case on its side which faces away from the bearing surface (22). - Stator blade segment (2) according to one of Claims 1 to 6,
in which the respective fastening element (14) is connected in a materially-bonding manner, preferably by soldering, to the platform (8) or to the remaining part of the fastening element (14). - Stator blade segment (2) according to one of Claims 1 to 7, with a multiplicity of blade airfoils (6) on a common platform (8).
- Thermal turbomachine,
especially a gas turbine,
with at least one stator blade segment (2) according to one of Claims 1 to 8. - Method for producing a stator blade segment (2) according to one of Claims 1 to 8,
in which a fastening element (14) with a fastening hook (18) is produced from a workpiece which comprises a longish profiled section,
by the profiled section being deformed by bending to form the fastening hook (18), and wherein the fastening element (14) is then connected by a bearing surface (22) in a non-positive-locking and/or materially-bonding manner, being recessed in the platform (8).
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
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EP07704682A EP2002085B1 (en) | 2006-04-06 | 2007-02-21 | Guide blade segment of a thermal turbomachine, associated production method and thermal turbomachine |
PL07704682T PL2002085T3 (en) | 2006-04-06 | 2007-02-21 | Guide blade segment of a thermal turbomachine, associated production method and thermal turbomachine |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
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EP06007332A EP1843009A1 (en) | 2006-04-06 | 2006-04-06 | Stator vane segment for a turbomachine, associated manufacturing method and turbomachine |
EP07704682A EP2002085B1 (en) | 2006-04-06 | 2007-02-21 | Guide blade segment of a thermal turbomachine, associated production method and thermal turbomachine |
PCT/EP2007/051669 WO2007113053A1 (en) | 2006-04-06 | 2007-02-21 | Guide blade segment of a thermal turbomachine, associated production method and thermal turbomachine |
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EP2002085A1 EP2002085A1 (en) | 2008-12-17 |
EP2002085B1 true EP2002085B1 (en) | 2010-02-10 |
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EP06007332A Withdrawn EP1843009A1 (en) | 2006-04-06 | 2006-04-06 | Stator vane segment for a turbomachine, associated manufacturing method and turbomachine |
EP07704682A Not-in-force EP2002085B1 (en) | 2006-04-06 | 2007-02-21 | Guide blade segment of a thermal turbomachine, associated production method and thermal turbomachine |
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EP06007332A Withdrawn EP1843009A1 (en) | 2006-04-06 | 2006-04-06 | Stator vane segment for a turbomachine, associated manufacturing method and turbomachine |
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US (1) | US8128357B2 (en) |
EP (2) | EP1843009A1 (en) |
JP (1) | JP4782225B2 (en) |
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EP1970533A1 (en) * | 2007-03-12 | 2008-09-17 | Siemens Aktiengesellschaft | Turbine with at least one rotor with rotor disks and a tie bolt |
DE102008043605B4 (en) * | 2007-11-16 | 2015-05-07 | Alstom Technology Ltd. | Method for producing a turbine housing |
ES2561037T3 (en) * | 2009-07-03 | 2016-02-24 | Alstom Technology Ltd | Method of replacing a cover of a guide blade of a gas turbine |
FR2976968B1 (en) * | 2011-06-21 | 2015-06-05 | Snecma | TURBOMACHINE COMPRESSOR COMPRESSOR OR TURBINE DISPENSER PART AND METHOD FOR MANUFACTURING THE SAME |
US9631517B2 (en) | 2012-12-29 | 2017-04-25 | United Technologies Corporation | Multi-piece fairing for monolithic turbine exhaust case |
US20160186579A1 (en) * | 2014-09-29 | 2016-06-30 | United Technologies Corporation | HYBRID GAMMA TiAl ALLOY COMPONENT |
US10711637B2 (en) * | 2017-06-15 | 2020-07-14 | General Electric Company | Turbine component assembly |
CN113500479B (en) * | 2021-07-07 | 2022-06-03 | 彭忠捷 | Automatic processing robot for steel wire guide hook for orthopedic operation |
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US2402005A (en) | 1944-05-08 | 1946-06-11 | Hans R Amundsen | Friction brake or clutch |
US2942844A (en) * | 1952-12-22 | 1960-06-28 | Gen Motors Corp | Turbine nozzle |
US3072380A (en) * | 1959-02-05 | 1963-01-08 | Dresser Ind | Stator blade carrier assembly mounting |
IT1124958B (en) * | 1978-11-25 | 1986-05-14 | Rolls Royce | ASSEMBLY OF DIRECT DISTRIBUTOR VANE FOR GAS TURBINE ENGINE |
SU859656A1 (en) | 1979-08-27 | 1981-08-30 | Предприятие П/Я А-3513 | Turbomachine guiding apparatus |
US5669757A (en) * | 1995-11-30 | 1997-09-23 | General Electric Company | Turbine nozzle retainer assembly |
RU2204021C2 (en) | 1999-03-01 | 2003-05-10 | Закрытое акционерное общество "Научно-инженерный центр Керамические тепловые двигатели им. А.М. Бойко" | Quasiadiabatic ceramic nozzle assembly of high- temperature gas turbine (versions) |
US6375415B1 (en) | 2000-04-25 | 2002-04-23 | General Electric Company | Hook support for a closed circuit fluid cooled gas turbine nozzle stage segment |
DE50011923D1 (en) | 2000-12-27 | 2006-01-26 | Siemens Ag | Gas turbine blade and gas turbine |
JP4562931B2 (en) * | 2001-02-19 | 2010-10-13 | 三菱重工業株式会社 | Stator blade assembly and fluid-operated rotating machine having the stator blade assembly |
FR2825780B1 (en) | 2001-06-06 | 2003-08-29 | Snecma Moteurs | COMBUSTION CHAMBER ARCHITECURE OF CERAMIC MATRIX MATERIAL |
DE10312956B4 (en) * | 2003-03-22 | 2011-08-11 | MTU Aero Engines GmbH, 80995 | Arrangement for the axial and radial fixing of a guide vane assembly in the housing of a turbine engine |
JP4269763B2 (en) * | 2003-04-28 | 2009-05-27 | 株式会社Ihi | Turbine nozzle segment |
GB0318609D0 (en) * | 2003-08-08 | 2003-09-10 | Rolls Royce Plc | An arrangement for mounting a non-rotating component |
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RU2008144021A (en) | 2010-05-20 |
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JP4782225B2 (en) | 2011-09-28 |
CN101460709A (en) | 2009-06-17 |
US8128357B2 (en) | 2012-03-06 |
ES2339717T3 (en) | 2010-05-24 |
EP2002085A1 (en) | 2008-12-17 |
CN101460709B (en) | 2011-11-02 |
RU2421624C2 (en) | 2011-06-20 |
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