EP1219779B1 - Turbomachine component with inspection hole, and method for inspecting and cleaning such a component - Google Patents
Turbomachine component with inspection hole, and method for inspecting and cleaning such a component Download PDFInfo
- Publication number
- EP1219779B1 EP1219779B1 EP01128803A EP01128803A EP1219779B1 EP 1219779 B1 EP1219779 B1 EP 1219779B1 EP 01128803 A EP01128803 A EP 01128803A EP 01128803 A EP01128803 A EP 01128803A EP 1219779 B1 EP1219779 B1 EP 1219779B1
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- EP
- European Patent Office
- Prior art keywords
- inspection
- component
- cleaning
- interior
- cooling
- 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.)
- Revoked
Links
- 238000007689 inspection Methods 0.000 title claims description 39
- 238000004140 cleaning Methods 0.000 title claims description 9
- 238000000034 method Methods 0.000 title claims description 5
- 238000001816 cooling Methods 0.000 claims description 28
- 239000000428 dust Substances 0.000 claims description 20
- 239000002826 coolant Substances 0.000 claims description 14
- 239000002245 particle Substances 0.000 claims description 9
- 230000002349 favourable effect Effects 0.000 description 2
- WYTGDNHDOZPMIW-RCBQFDQVSA-N alstonine Natural products C1=CC2=C3C=CC=CC3=NC2=C2N1C[C@H]1[C@H](C)OC=C(C(=O)OC)[C@H]1C2 WYTGDNHDOZPMIW-RCBQFDQVSA-N 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 238000010438 heat treatment Methods 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/002—Cleaning of turbomachines
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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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/10—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to unwanted deposits on blades, in working-fluid conduits or the like
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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
- F01D25/32—Collecting of condensation water; Drainage ; Removing solid particles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
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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
- F05D2260/60—Fluid transfer
- F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles
Definitions
- the present invention relates to a component of a turbomachine, in particular a gas turbine, which has cooling channels for a cooling medium and at least one inspection opening, through which an inspection of the interior of the component is made possible, and a method for inspecting and / or cleaning the interior of such a component ,
- the turbine blades have one or more chambers and / or channels formed as a cavity, via which a cooling medium can be supplied to the blades from the side of the rotor.
- a cooling medium can be supplied to the blades from the side of the rotor.
- In the inflow region of the turbine blades at the front edge thereof are usually provided numerous cooling air holes through which the cooling medium from the interior of the blade can escape to the outside.
- On the surface forms a cooling air film in this area, which protects the turbine blade from excessive heating.
- corresponding cooling air holes are present at the trailing edge of the turbine blade.
- the object of the present invention is to develop a hollow component of a turbomachine such that both the inspection and a reduction in the risk of clogging of the cooling air holes can be realized in a simple manner.
- Claim 6 further specifies a method for inspection and / or cleaning of the interior of a designed according to claim 1 component.
- the component according to the invention with cooling channels for a cooling medium and at least one inspection opening, through which an inspection of the interior of the component is made possible, is characterized in that the inspection opening is arranged and dimensioned on the component such that it simultaneously forms a dust discharge opening in the cooling medium contained dust or dirt particles.
- Staubaustragsö réelle Under a Staubaustragsö réelle here is an opening in the wall of the component to understand, on the entrained particles in the cooling medium escape due to their inertia from the interior of the component.
- a Staubaustragsö réelle must therefore be arranged inevitably on a deflection of the channel leading to the cooling medium or at the end of a branching of this channel at a corresponding deflection dust channel.
- Such Staubaustragsö réelleen are already used in components of turbomachines to prevent clogging of the cooling channel holes.
- An example of an embodiment of a turbine blade with such a dust discharge opening can be found, for example, in US Pat. No. 4,820,122.
- the interior of the turbine blade has serpentine here extending cooling air ducts on.
- the branching into the individual serpentine channels takes place already in the region of the entry of the cooling air into the turbine blade on the rotor.
- a direct extension of the inlet channel extends radially a rectilinear channel which leads directly to a Staubaustragsö réelle at the blade tip. Due to the cooling force, the particles entering with the cooling air are conveyed directly rectilinearly radially to this dust discharge opening, while approximately dirt-free cooling air can easily enter the other serpentine channels. The dirt particles are thus guided through this dust discharge or dust hole from the cooling channels to the outside, so that the actual cooling air holes can not be clogged by the dirt particles.
- inspection access openings by skillful arrangement can fulfill the function of Staubaustragsötechnischen or that Staubaustragsötechnischen can serve as InspektionszugDeutschsötechnischen by suitable dimensioning, in particular magnification.
- the Staubaustragsö Samuelen are in this case designed by the size and the situation so that both the dirt discharged favorable and an opening with sufficient diameter is formed in order to introduce a Boroskop through this opening can.
- This inspection opening or bore which at the same time constitutes a dust discharge opening, is preferably taken into account already during the casting of the component and not, like the cooling air openings, introduced by subsequent drilling.
- this inspection and Staubaustragsö réelle preferably located in the vicinity of the blade tip.
- these inspection and Staubaustragsö réelleen are arranged approximately parallel to the machine axis when the inspection tool is to be performed in the hot gas path of the gas turbine. If the inspection tool is to be guided radially into the machine, then a position at the blade tip is more favorable, in which the inspection and dust discharge opening extends radially to the machine axis.
- the inventive combination of the Staubaustrages and the inspection capability with one and the same opening unnecessary openings are avoided, which can cause an undesirable loss of cooling medium and thus a loss of efficiency.
- Figure 1 shows in cross section schematically a turbine blade with blade root 1, platform 2 and blade 3 in the cross section of the hollow channel 4 can be seen, via which the turbine blade cooling air from the blade root 1 is supplied forth.
- the turbine blade dust discharge 5 are discharged through the entrained with the cooling medium dirt particles due to their inertia from the hollow channel 4.
- the particles Due to the high flow rate of the cooling medium at the present at the dust discharge 5 deflection of the cooling channel 4, the particles take their way through the Staubaustragsö réelle 5 due to their large mass and do not get over the deflection in the further course of the cooling channel in which thus flows relatively dust-free cooling air ,
- This cooling air flows past the pins 6 and leaves the blade via openings at the trailing edge, for example via a slot.
- the Staubaustragsö réelle 5 is inventively formed in diameter so large that the introduction of a borescope is made possible through this opening 5 in the interior of the turbine blade. In this way, the interior of this component can be inspected at any time even when installed.
- FIG. 2 shows another example in which the dust discharge opening 5, however, does not run in the radial but in the axial direction. Also in this example, in turn, the blade root 1, the platform 2 and the blade 3 can be seen in cross section.
- the cooling channel 4 runs in the same way as in FIG. 1.
- the mechanism of the Staubaustragung is the same as that of Figure 1.
- the dirt particles take the path over the channel 7 leading to the dust hole 5, because of their inertia and the high velocity of the circulating cooling medium, while the cooling medium easily at the branch towards Machine axis is deflected and therefore relatively dustless on the pins or 6 passes over to the cooling air openings at the trailing edge of the blade.
- the dust hole 5 and / or the channel 7 leading to it are in turn in this case made of a diameter such that they allow the introduction of an inspection tool, in particular a borescope, into the interior of the turbine blade.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Die vorliegende Erfindung betrifft eine Komponente einer Strömungsmaschine, insbesondere einer Gasturbine, die Kühlkanäle für ein Kühlmedium sowie zumindest eine Inspektionsöffnung aufweist, durch die hindurch eine Inspektion des Inneren der Komponente ermöglicht wird, sowie ein Verfahren zur Inspektion und/oder Reinigung des Inneren einer derartigen Komponente.The present invention relates to a component of a turbomachine, in particular a gas turbine, which has cooling channels for a cooling medium and at least one inspection opening, through which an inspection of the interior of the component is made possible, and a method for inspecting and / or cleaning the interior of such a component ,
Moderne Hochtemperaturgasturbinen erfordern zur Erzielung eines hohen Wirkungsgrades ein ausgeklügeltes Kühlsystem, insbesondere zur Kühlung der hochbelasteten Turbinenschaufeln. Die Turbinenschaufeln weisen hierfür einen oder mehrere als Hohlraum ausgebildete Kammern und/oder Kanäle auf, über die den Schaufeln von der Seite des Rotors ein Kühlmedium zugeführt werden kann. Im Anströmbereich der Turbinenschaufeln an deren Vorderkante sind hierbei in der Regel zahlreiche Kühlluftbohrungen vorgesehen, durch die das Kühlmedium vom Inneren der Schaufel nach außen treten kann. Auf der Oberfläche bildet sich in diesem Bereich ein Kühlluftfilm, der die Turbinenschaufel vor einer zu starken Erwärmung schützt. In gleicher Weise sind auch entsprechende Kühlluftbohrungen an der Hinterkante der Turbinenschaufel vorhanden.Modern high-temperature gas turbines require a sophisticated cooling system to achieve high efficiency, in particular for cooling the highly loaded turbine blades. For this purpose, the turbine blades have one or more chambers and / or channels formed as a cavity, via which a cooling medium can be supplied to the blades from the side of the rotor. In the inflow region of the turbine blades at the front edge thereof are usually provided numerous cooling air holes through which the cooling medium from the interior of the blade can escape to the outside. On the surface forms a cooling air film in this area, which protects the turbine blade from excessive heating. In the same way, corresponding cooling air holes are present at the trailing edge of the turbine blade.
Ein Problem stellt bei derartigen hohlen Komponenten, wie beispielsweise Turbinenschaufeln oder Brennkammerelementen, die häufig aus einem Stück gegossen werden, die schlechte Zugänglichkeit des Inneren dieser Komponenten dar. Sie lassen sich daher in der Regel nur schlecht beispielsweise auf innere Beschädigungen wie Risse oder Schmutzablagerungen inspizieren.A problem with such hollow components, such as turbine blades or Combustor elements, which are often cast in one piece, the poor accessibility of the interior of these components. They are therefore usually poorly inspect, for example, for internal damage such as cracks or dirt deposits.
Zur Vermeidung dieser Problematik ist es beispielsweise aus der DE 198 01 804 A1 bekannt, zusätzlich zu den in jedem Falle erforderlichen Kühlluftbohrungen eine oder mehrere Inspektionszugangsöffnungen in die äußere Wand der Turbinenschaufel einzubringen, durch die hindurch das Schaufelinnere mit einem entsprechenden Inspektionswerkzeug untersucht werden kann. Eine derartige Inspektionsöffnung bzw. Inspektionszugangsöffnung ermöglicht auch die Inspektion einer bereits eingebauten Turbinenschaufel sowie die Reinigung des Inneren der Turbinenschaufel von Schmutzablagerungen, die zur Verstopfung der sehr engen Kühlluftbohrungen führen können. Die genannte Druckschrift sieht hierfür die Einführung eines speziellen Reinigungswerkzeuges durch die Inspektionszugangsöffnungen vor.To avoid this problem, it is known, for example from DE 198 01 804 A1, to introduce one or more inspection access openings into the outer wall of the turbine blade, in addition to the cooling air bores required in each case, through which the blade interior can be examined with a corresponding inspection tool. Such an inspection opening or inspection access opening also allows the inspection of an already installed turbine blade and the cleaning of the interior of the turbine blade of dirt deposits, which can lead to the blockage of very narrow cooling air holes. The cited document provides for the introduction of a special cleaning tool through the inspection access openings.
Die Aufgabe der vorliegenden Erfindung besteht darin, eine hohle Komponente einer Strömungsmaschine derart weiterzubilden, dass sowohl die Inspektion als auch eine Verminderung der Gefahr einer Verstopfung der Kühlluftbohrungen in einfacher Weise realisiert werden können.The object of the present invention is to develop a hollow component of a turbomachine such that both the inspection and a reduction in the risk of clogging of the cooling air holes can be realized in a simple manner.
Die Aufgabe wird mit der Komponente gemäß Patentanspruch 1 gelöst. Vorteilhafte Ausgestaltungen der Komponente sind Gegenstand der Unteransprüche. Patentanspruch 6 gibt weiterhin ein Verfahren zur Inspektion und/oder Reinigung des Inneren einer gemäß Patentanspruch 1 ausgestalteten Komponente an.The object is achieved with the component according to claim 1. Advantageous embodiments of the component are the subject of the dependent claims. Claim 6 further specifies a method for inspection and / or cleaning of the interior of a designed according to claim 1 component.
Die erfindungsgemäße Komponente mit Kühlkanälen für ein Kühlmedium sowie zumindest einer Inspektionsöffnung, durch die hindurch eine Inspektion des Inneren der Komponente ermöglicht wird, zeichnet sich dadurch aus, dass die Inspektionsöffnung derart an der Komponente angeordnet und dimensioniert ist, dass sie gleichzeitig eine Staubaustragsöffnung für im Kühlmedium enthaltene Staub- oder Schmutzpartikel bildet.The component according to the invention with cooling channels for a cooling medium and at least one inspection opening, through which an inspection of the interior of the component is made possible, is characterized in that the inspection opening is arranged and dimensioned on the component such that it simultaneously forms a dust discharge opening in the cooling medium contained dust or dirt particles.
Unter einer Staubaustragsöffnung ist hierbei eine Öffnung in der Wand der Komponente zu verstehen, über die im Kühlmedium mitgeführte Partikel aufgrund ihrer Trägheit aus dem Inneren der Komponente austreten. Eine Staubaustragsöffnung muss daher zwangsläufig an einer Umlenkung des das Kühlmedium führenden Kanals oder am Ende eines von diesem Kanal an einer entsprechenden Umlenkung abzweigenden Staubkanals angeordnet sein. Derartige Staubaustragsöffnungen werden bei Komponenten von Strömungsmaschinen bereits eingesetzt, um eine Verstopfung der Kühlkanalbohrungen zu verhindern. Ein Beispiel für eine Ausgestaltung einer Turbinenschaufel mit einer derartigen Staubaustragsöffnung ist beispielsweise der US 4,820,122 zu entnehmen. Das Innere der Turbinenschaufel weist hierbei serpentinenartig verlaufende Kühlluftführungen auf. Die Verzweigung in die einzelnen serpentinenartigen Kanäle erfolgt bereits im Bereich des Eintritts der Kühlluft in die Turbinenschaufel am Rotor. In direkter Verlängerung des Eintrittskanals erstreckt sich radial ein geradliniger Kanal der direkt zu einer Staubaustragsöffnung an der Schaufelspitze führt. Die mit der Kühlluft eintretenden Partikel werden aufgrund der Kühlkraft direkt geradlinig radial zu dieser Staubaustragsöffnung befördert, während annähernd schmutzfreie Kühlluft problemlos in die anderen serpentinenartigen Kanäle eintreten kann. Die Schmutzpartikel werden somit durch diese Staubaustragsöffnung bzw. dieses Staubloch aus den Kühlkanälen ins Freie geführt, so dass die eigentlichen Kühlluftbohrungen nicht von den Schmutzpartikeln verstopft werden können.Under a Staubaustragsöffnung here is an opening in the wall of the component to understand, on the entrained particles in the cooling medium escape due to their inertia from the interior of the component. A Staubaustragsöffnung must therefore be arranged inevitably on a deflection of the channel leading to the cooling medium or at the end of a branching of this channel at a corresponding deflection dust channel. Such Staubaustragsöffnungen are already used in components of turbomachines to prevent clogging of the cooling channel holes. An example of an embodiment of a turbine blade with such a dust discharge opening can be found, for example, in US Pat. No. 4,820,122. The interior of the turbine blade has serpentine here extending cooling air ducts on. The branching into the individual serpentine channels takes place already in the region of the entry of the cooling air into the turbine blade on the rotor. In a direct extension of the inlet channel extends radially a rectilinear channel which leads directly to a Staubaustragsöffnung at the blade tip. Due to the cooling force, the particles entering with the cooling air are conveyed directly rectilinearly radially to this dust discharge opening, while approximately dirt-free cooling air can easily enter the other serpentine channels. The dirt particles are thus guided through this dust discharge or dust hole from the cooling channels to the outside, so that the actual cooling air holes can not be clogged by the dirt particles.
Die Erfinder der vorliegenden Erfindung haben nun erkannt, dass Inspektionszugangsöffnungen durch geschickte Anordnung die Funktion von Staubaustragsöffnungen erfüllen können bzw. dass Staubaustragsöffnungen durch geeignete Dimensionierung, insbesondere Vergrößerung als Inspektionszugängsöffnungen dienen können. Die Staubaustragsöffnungen werden hierbei von der Größe und der Lage so ausgelegt, dass sowohl der Schmutz günstig ausgetragen als auch eine Öffnung mit ausreichendem Durchmesser gebildet wird, um ein Boroskop durch diese Öffnung einführen zu können.The inventors of the present invention have now recognized that inspection access openings by skillful arrangement can fulfill the function of Staubaustragsöffnungen or that Staubaustragsöffnungen can serve as Inspektionszugängsöffnungen by suitable dimensioning, in particular magnification. The Staubaustragsöffnungen are in this case designed by the size and the situation so that both the dirt discharged favorable and an opening with sufficient diameter is formed in order to introduce a Boroskop through this opening can.
Diese Inspektionsöffnung oder -bohrung, die gleichzeitig eine Staubaustragsöffnung darstellt, wird vorzugsweise bereits beim Gießen der Komponente berücksichtigt und nicht, wie die Kühlluftöffnungen, durch nachträgliches Bohren eingebracht. Bei Laufschaufeln sitzt diese Inspektions- und Staubaustragsöffnung bevorzugt in der Nähe der Schaufelspitze. Um die Schaufeln auch im eingebauten Zustand der Maschine inspizieren zu können, sind diese Inspektions- und Staubaustragsöffnungen annähernd parallel zur Maschinenachse angeordnet, wenn das Inspektionswerkzeug im Heißgaspfad der Gasturbine geführt werden soll. Soll das Inspektionswerkzeug radial in die Maschine geführt werden, so ist eine Position an der Schaufelspitze günstiger, bei der die Inspektions- und Staubaustragsöffnung radial zur Maschinenachse verläuft. Durch die erfindungsgemäße Kombination des Staubaustrages und der Inspektionsfähigkeit mit ein und der selben Öffnung werden unnötige Öffnungen vermieden, die einen unerwünschten Verlust an Kühlmedium und somit einen Verlust an Wirkungsgrad hervorrufen können.This inspection opening or bore, which at the same time constitutes a dust discharge opening, is preferably taken into account already during the casting of the component and not, like the cooling air openings, introduced by subsequent drilling. For blades, this inspection and Staubaustragsöffnung preferably located in the vicinity of the blade tip. In order to inspect the blades in the installed state of the machine, these inspection and Staubaustragsöffnungen are arranged approximately parallel to the machine axis when the inspection tool is to be performed in the hot gas path of the gas turbine. If the inspection tool is to be guided radially into the machine, then a position at the blade tip is more favorable, in which the inspection and dust discharge opening extends radially to the machine axis. The inventive combination of the Staubaustrages and the inspection capability with one and the same opening unnecessary openings are avoided, which can cause an undesirable loss of cooling medium and thus a loss of efficiency.
Die Erfindung wird nachfolgend anhand von Ausführungsbeispielen in Verbindung mit den Zeichnungen ohne Beschränkung des allgemeinen Erfindungsgedankens nochmals kurz erläutert. Hierbei zeigen:
- Fig. 1
- schematisch einen Schnitt durch eine Turbinenschaufel, die gemäß der vorliegenden Erfindung ausgestaltet ist; und
- Fig. 2
- ein weiteres Beispiel für die Ausgestaltung einer Turbinenschaufel im Querschnitt, die gemäß der vorliegenden Erfindung ausgestaltet ist.
- Fig. 1
- schematically a section through a turbine blade, which is designed according to the present invention; and
- Fig. 2
- Another example of the design of a turbine blade in Cross section, which is designed according to the present invention.
Figur 1 zeigt im Querschnitt schematisch eine Turbinenschaufel mit Schaufelfuß 1, Plattform 2 sowie Schaufelblatt 3. In dem Querschnitt ist der Hohlkanal 4 zu erkennen, über den der Turbinenschaufel Kühlluft vom Schaufelfuß 1 her zugeführt wird. An der Schaufelspitze ist im vorderen Bereich, d. h. im Anströmbereich der Turbinenschaufel eine Staubaustragsöffnung 5 dargestellt, durch die mit dem Kühlmedium mitgeführte Schmutzpartikel aufgrund ihrer Trägheit aus dem Hohlkanal 4 ausgetragen werden. Durch die hohe Strömungsgeschwindigkeit des Kühlmediums an der bei der Staubaustragsöffnung 5 vorhandenen Umlenkung des Kühlkanals 4 nehmen die Partikel aufgrund ihrer großen Masse den Weg durch die Staubaustragsöffnung 5 und gelangen nicht über die Umlenkung in den weiteren Verlauf des Kühlkanals, in dem somit relativ staubfreie Kühlluft strömt. Diese Kühlluft strömt an den Pins 6 vorbei und verlässt die Schaufel über Öffnungen an der Hinterkante, beispielsweise über einen Schlitz. Die Staubaustragsöffnung 5 ist erfindungsgemäß im Durchmesser derart groß ausgebildet, dass die Einführung eines Boroskops durch diese Öffnung 5 in das Innere der Turbinenschaufel ermöglicht wird. Auf diese Weise lässt sich das Innere dieser Komponente auch in eingebautem Zustand jederzeit inspizieren.Figure 1 shows in cross section schematically a turbine blade with blade root 1, platform 2 and
Figur 2 zeigt schließlich ein weiteres Beispiel, bei der die Staubaustragsöffnung 5 jedoch nicht in radialer, sondern in axialer Richtung verläuft. Auch bei diesem Beispiel sind wiederum der Schaufelfuß 1, die Plattform 2 sowie das Schaufelblatt 3 im Querschnitt zu erkennen. Der Kühlkanal 4 verläuft in gleicher Weise wie bei Figur 1. Das Staubloch 5, das in diesem Beispiel parallel zur Maschinenachse verläuft, ermöglicht die Inspektion mit einem im Heißgaspfad geführten Inspektionswerkzeug. Der Mechanismus der Staubaustragung ist der gleiche wie der der Figur 1. In diesem Beispiel nehmen die Schmutzpartikel aufgrund ihrer Trägheit und der hohen Geschwindigkeit des umströmenden Kühlmediums den Weg über den zum Staubloch 5 führenden Kanal 7, während das Kühlmedium problemlos an der Verzweigung in Richtung zur Maschinenachse umgelenkt wird und daher relativ staublos an den Stiften bzw. Pins 6 vorbei zu den Kühlluftöffnungen an der Hinterkante der Schaufel geleitet wird. Das Staubloch 5 bzw. der zu diesem führende Kanal 7 sind hierbei wiederum vom Durchmesser her derart ausgestaltet, dass sie die Einführung eines Inspektionswerkzeuges, insbesonderes eines Boroskops in das Innere der Turbinenschaufel ermöglichen.Finally, FIG. 2 shows another example in which the dust discharge opening 5, however, does not run in the radial but in the axial direction. Also In this example, in turn, the blade root 1, the platform 2 and the
- 11
- Schaufelfußblade
- 22
- Plattformplatform
- 33
- Schaufelblattairfoil
- 44
- Kühlkanalcooling channel
- 55
- Staubaustragsöffnung bzw. InspektionsöffnungDust discharge opening or inspection opening
- 66
- Stiftepencils
- 77
- StaubaustragskanalDust discharge channel
Claims (7)
- Component of a turbo machine, in particular of a gas turbine, which has cooling ducts (4) for a cooling medium and at least one inspection port (5) through which an inspection of the interior of the component is made possible, characterized in that the inspection port (5) is arranged and dimensioned in such a way that it forms a dust discharge port for dust or dirt particles contained in the cooling medium.
- Component according to Claim 1, characterized in that the inspection port (5) is dimensioned in such a way that it allows the introduction of a boroscope.
- Component according to Claim 1 or 2, which is designed as a moving blade for a turbine, the inspection port (5) being arranged in the vicinity of the blade tip.
- Component according to Claim 3, characterized in that the inspection port (5) runs approximately parallel to the machine axis.
- Component according to Claim 3, characterized in that the inspection port (5) is arranged at the blade tip and runs in the radial direction.
- Method for the inspection and/or cleaning of the interior of a component of a turbo machine, in particular a gas turbine, the said component being designed according to Patent Claim 1, characterized in that an inspection and/or cleaning tool is introduced through the inspection or dust discharge port, and an inspection and/or cleaning of the interior of the component is carried out by means of the inspection and/or cleaning tool.
- Method according to Claim 6, characterized in that the inspection tool used is a boroscope.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE10064269A DE10064269A1 (en) | 2000-12-22 | 2000-12-22 | Component of a turbomachine with an inspection opening |
| DE10064269 | 2000-12-22 |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| EP1219779A2 EP1219779A2 (en) | 2002-07-03 |
| EP1219779A3 EP1219779A3 (en) | 2003-12-10 |
| EP1219779B1 true EP1219779B1 (en) | 2006-11-02 |
Family
ID=7668442
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP01128803A Revoked EP1219779B1 (en) | 2000-12-22 | 2001-12-04 | Turbomachine component with inspection hole, and method for inspecting and cleaning such a component |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US20020090298A1 (en) |
| EP (1) | EP1219779B1 (en) |
| DE (2) | DE10064269A1 (en) |
Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE50304226D1 (en) * | 2002-03-25 | 2006-08-24 | Alstom Technology Ltd | COOLED TURBINE BUCKET |
| DE10305898A1 (en) * | 2003-02-13 | 2004-08-26 | Alstom Technology Ltd | Process for installing spiral thread inserts and installation tool for carrying out the process |
| FR2858352B1 (en) * | 2003-08-01 | 2006-01-20 | Snecma Moteurs | COOLING CIRCUIT FOR TURBINE BLADE |
| US7185662B2 (en) * | 2003-11-14 | 2007-03-06 | United Technologies Corporation | Methods of preparing, cleaning and repairing article and article repaired |
| EP1704933B1 (en) * | 2005-03-21 | 2012-12-19 | United Technologies Corporation | Methods of preparing, cleaning and repairing an article |
| US7377747B2 (en) * | 2005-06-06 | 2008-05-27 | General Electric Company | Turbine airfoil with integrated impingement and serpentine cooling circuit |
| US8245952B2 (en) * | 2009-02-20 | 2012-08-21 | Pratt & Whitney Canada Corp. | Compressor wash nozzle integrated in an inlet case strut |
| EP2236746A1 (en) | 2009-03-23 | 2010-10-06 | Alstom Technology Ltd | Gas turbine |
| DE102009039224B4 (en) | 2009-08-28 | 2022-10-06 | MTU Aero Engines AG | Method and device for detecting clogged holes in a component |
| US20140063228A1 (en) * | 2012-09-06 | 2014-03-06 | General Electric Company | Method and system for cleaning surfaces and non-destructive inspection thereof |
| US9938836B2 (en) * | 2015-12-22 | 2018-04-10 | General Electric Company | Turbine airfoil with trailing edge cooling circuit |
Family Cites Families (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3533711A (en) * | 1966-02-26 | 1970-10-13 | Gen Electric | Cooled vane structure for high temperature turbines |
| US3628885A (en) * | 1969-10-01 | 1971-12-21 | Gen Electric | Fluid-cooled airfoil |
| US3936217A (en) * | 1975-01-31 | 1976-02-03 | Westinghouse Electric Corporation | Inspection port for turbines |
| US4278400A (en) * | 1978-09-05 | 1981-07-14 | United Technologies Corporation | Coolable rotor blade |
| GB2051964B (en) * | 1979-06-30 | 1983-01-12 | Rolls Royce | Turbine blade |
| US4775296A (en) * | 1981-12-28 | 1988-10-04 | United Technologies Corporation | Coolable airfoil for a rotary machine |
| US4668162A (en) * | 1985-09-16 | 1987-05-26 | Solar Turbines Incorporated | Changeable cooling control system for a turbine shroud and rotor |
| JPS62228603A (en) * | 1986-03-31 | 1987-10-07 | Toshiba Corp | Gas turbine blade |
| US4767268A (en) * | 1987-08-06 | 1988-08-30 | United Technologies Corporation | Triple pass cooled airfoil |
| US4820122A (en) * | 1988-04-25 | 1989-04-11 | United Technologies Corporation | Dirt removal means for air cooled blades |
| US4820123A (en) * | 1988-04-25 | 1989-04-11 | United Technologies Corporation | Dirt removal means for air cooled blades |
| US4962640A (en) * | 1989-02-06 | 1990-10-16 | Westinghouse Electric Corp. | Apparatus and method for cooling a gas turbine vane |
| GB2244047B (en) * | 1990-05-17 | 1994-02-16 | Rolls Royce Plc | Inspection aperture sealing |
| US5052889A (en) * | 1990-05-17 | 1991-10-01 | Pratt & Whintey Canada | Offset ribs for heat transfer surface |
| US5603606A (en) * | 1994-11-14 | 1997-02-18 | Solar Turbines Incorporated | Turbine cooling system |
| US5797726A (en) * | 1997-01-03 | 1998-08-25 | General Electric Company | Turbulator configuration for cooling passages or rotor blade in a gas turbine engine |
| US5931638A (en) * | 1997-08-07 | 1999-08-03 | United Technologies Corporation | Turbomachinery airfoil with optimized heat transfer |
| US5902093A (en) * | 1997-08-22 | 1999-05-11 | General Electric Company | Crack arresting rotor blade |
| US5975851A (en) * | 1997-12-17 | 1999-11-02 | United Technologies Corporation | Turbine blade with trailing edge root section cooling |
| DE19801804C2 (en) * | 1998-01-19 | 1999-10-28 | Siemens Ag | Turbine blade and method for inspecting and / or cleaning a turbine blade |
| US6206638B1 (en) * | 1999-02-12 | 2001-03-27 | General Electric Company | Low cost airfoil cooling circuit with sidewall impingement cooling chambers |
| DE19921644B4 (en) * | 1999-05-10 | 2012-01-05 | Alstom | Coolable blade for a gas turbine |
| US6468033B1 (en) * | 2000-10-03 | 2002-10-22 | General Electric Company | Methods and apparatus for maintaining alignment of borescope plungers |
| US6431832B1 (en) * | 2000-10-12 | 2002-08-13 | Solar Turbines Incorporated | Gas turbine engine airfoils with improved cooling |
-
2000
- 2000-12-22 DE DE10064269A patent/DE10064269A1/en not_active Withdrawn
-
2001
- 2001-12-04 EP EP01128803A patent/EP1219779B1/en not_active Revoked
- 2001-12-04 DE DE50111356T patent/DE50111356D1/en not_active Expired - Lifetime
- 2001-12-05 US US10/002,141 patent/US20020090298A1/en not_active Abandoned
Also Published As
| Publication number | Publication date |
|---|---|
| EP1219779A3 (en) | 2003-12-10 |
| DE50111356D1 (en) | 2006-12-14 |
| DE10064269A1 (en) | 2002-07-04 |
| EP1219779A2 (en) | 2002-07-03 |
| US20020090298A1 (en) | 2002-07-11 |
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