EP0899426B1 - Guide vane for a gas turbine - Google Patents

Guide vane for a gas turbine Download PDF

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Publication number
EP0899426B1
EP0899426B1 EP98114445A EP98114445A EP0899426B1 EP 0899426 B1 EP0899426 B1 EP 0899426B1 EP 98114445 A EP98114445 A EP 98114445A EP 98114445 A EP98114445 A EP 98114445A EP 0899426 B1 EP0899426 B1 EP 0899426B1
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EP
European Patent Office
Prior art keywords
guide vane
guide
platform
face
projection
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EP98114445A
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German (de)
French (fr)
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EP0899426A2 (en
EP0899426A3 (en
Inventor
Rudolf Stanka
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MTU Aero Engines AG
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MTU Aero Engines GmbH
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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

Definitions

  • the invention relates to a guide vane for a gas turbine, in particular a low-pressure turbine, with an airfoil that sits between an inner platform and an outer platform, the outer platform securing means for attachment to a housing, a vane segment from at least three guide vanes and a guide ring assembly.
  • Guide vanes of low pressure turbines are made of metal and are in the development phase generally initially to segments of three or six guide vanes soldered together.
  • the profile of the airfoils is like a real gas turbine engine put together several guide vane segments to form a closed guide ring assembly, the individual guide vane segments to compensate for thermal expansion are not rigidly interconnected.
  • the guide vanes are attached to their outer platforms in a (engine) housing and releasably together on their inner platforms by metal clips or the like braced. By bracing the inner platforms, this is supposed to Vibration behavior of the airfoils can be improved.
  • the use of the Tension clamps as additional components have the disadvantage of being more complex Assembly and higher costs.
  • guide vanes are made of mostly carbon fiber reinforced plastics used and examined in so-called aerodynamic "cold" test benches. Such Guide vanes are much faster and cheaper to manufacture than corresponding ones Guide vanes made of metal and are therefore used in the upstream investigations preferably used.
  • the guide vanes are made of plastic in the test bench at significantly lower temperatures (approx. 130 ° C) than in real operation, however loaded with gas forces of the same order of magnitude as in the real engine.
  • the problem here is the geometry of the outer and inner platform of the guide vanes made of metal for those made of plastic, as these are the loads cannot withstand the high, real gas forces. Gluing three or six guide vanes each to form individual guide vane segments the wreath of guiding rings has not solved this problem, like bracing the guide vanes by means of bolts that are in the lateral end faces the outer and inner platforms are provided. The vibration amplitudes were too large and caused the guide vanes to break.
  • EP-A-0 654 586 is concerned with guide vane segments made of fiber composite material, each segment having at least two blades and an inner and an outer Platform segment (cover band segment) includes.
  • the inner platform segment is designed as a continuously open hollow section with a roughly rectangular cross section, whose curvature is coaxial to the engine axis. At one end the hollow profile is tapered in steps, so that it is largely free of play and positive fits into the open end of an adjacent hollow profile. In this way can adjacent vane segments over their inner platform segments be form-fitted together. Because the continuously open hollow profiles (see also column 3, lines 44 to 46) are still relatively easily deformable (cross-sectional deformation), is the overall dimensional stability resulting in the guide vane ring and stiffness not optimal. The simple, compliant execution of the outer platforms also have a negative impact.
  • the invention has for its object a guide vane of the one described Generate genus that has an improved dynamic vibration behavior has, the vibration amplitude of adjacent guide vanes limited and manufacturing technology is easy and inexpensive to manufacture.
  • the solution to the problem is characterized in that the outer Platform and the inner platform as torsion and rigid hollow structures are executed, the outer platform being a platform, a stiffening wall, two spaced-apart cross struts and a closed end face and wherein the inner platform is a platform, a reinforcement wall and has a closed end surface that the projections are integral Elements of the closed end faces are narrow, their peripheral contour have forming side faces, and that the open end faces of the platforms with their inner surfaces the receptacles for the projections of a neighboring one Form the guide vane.
  • the advantage is: in that e.g. adjacent vanes of adjacent Guide vane segments (e.g. from three interconnected guide vanes) are optimally coupled to one another in the axial direction and by the friction on the contact surfaces creates a damping effect. Also effect the protrusions seal off gaps occurring between the platforms.
  • the structural rigidity is also optimized.
  • each projection runs perpendicular to the first, generally radial end face the outer or inner platform.
  • the side surface of the projection therefore runs in the circumferential direction heavily loaded by the gas flow and enables there damping due to friction on the contact surfaces.
  • each projection is preferably at least 3 mm above the first End face of the outer or inner platform, so that a sufficiently large Friction or contact surface with the recording of an adjacent guide vane is present.
  • each projection has at least 30% of the (cross-sectional) area the first end face on the respective platform so that the neighboring ones Guide vanes are not only coupled point-to-point and are reliable Limitation of the vibration amplitude is made possible.
  • the projection with play in the exception of the neighboring one is seated or fitted so that, for example, one another adjacent guide vanes of adjacent guide vane segments as a result of Thermal expansion can move away from each other and towards each other without any problems.
  • An inner surface adjacent to the second end surface runs most preferably the recording in the assembled state parallel to the side surface of the projection, so that a secure frictional contact between the inner surface of the receptacle and the side surface the lead is guaranteed.
  • the guide vane is formed in one piece, so that it is inexpensive can be made by metal or injection molding.
  • the guide vane is made of carbon fiber reinforced plastic, so that it is can be examined in so-called aerodynamic "cold" test benches. This makes it clear faster and less expensive test data for the calibration of aerodynamic design processes determine than is the case when using metal guide vanes.
  • Experimental guide vanes made of plastic can also be glued to guide vane segments connect from three or six guide vanes.
  • the side surface of the tab offers adhesive surfaces that are in contrast to the first and second end surfaces the outer and inner platforms are not subjected to tension / compression, but to shear become. This is the much cheaper form of stress for adhesive bonds.
  • FIG. 1 shows an exemplary embodiment of the guide vane according to the invention, designated by 1, which is made of carbon fiber reinforced plastic and manufactured by injection molding is.
  • a guide vane 1 is used in so-called aerodynamic "cold" test benches Fast and inexpensive test data from pressure, speed and flow field measurements for the calibration of aerodynamic design processes.
  • the guide vane 1 comprises an airfoil 2, an outer platform 3 from a platform 3 'and a spaced stiffening wall 4 and an inner platform 5 from one Platform 5 'and an associated and also extending at a distance from it Reinforcement wall 6. Both the outer and inner platforms 3 and 5 are on one first end face 7 is provided with a projection 8, each of which over the first end face 7 has about 3 mm protruding side surface 9.
  • the airfoil 2 with its between the outer and inner platform 3 or 5 extending longitudinal extent substantially in the radial direction the engine assembly arranged.
  • Fig. 2 shows the guide vane 1 of Fig. 1 in a side view, in which the substantially parallel to the (outer) platform 3 'stiffening wall 4 and with the (inner) platform 5 'connected reinforcement wall 6, which extends over several corners are.
  • On the outer platform 3 are two hook-like fastening means 11 for attachment the guide vane 1 is formed on an engine housing (not shown).
  • Each cavity forms a receptacle 12 with which the second end face 13 of the outer and inner platform 3 and 5 is provided.
  • a Projection 8 of an adjacent guide vane 1 is positively received in this receptacle 12, the dimensions of which are matched to those of the projection 8 so that the outer and inner platforms 3 and 5 adjacent guide vanes 1 in the assembled state aligned, as can be seen in FIGS. 4 and 5.
  • the receptacle 12 has one to the second End face 13 adjacent inner surface 14, which in the assembled state due to the coordinated Dimensioning of the projection 8 and the receptacle 12 a contact surface with the Side surface 9 of the projection 8 forms. This also creates a seal between neighboring vanes 1 achieved.
  • Fig. 2 it can be seen that the projection 8 and the Image 12 more than 50% of the cross-sectional area of the first or Make out the second end face 7 or 13.
  • FIG. 3 shows a single guide vane 1 vibrating in the axial direction, two different ones Vibration states are shown. 3 in particular on the inner platform 5 or the vibration amplitude of the reinforcement wall 6, which is clearly recognizable at the guide vane 1 according to the invention arranged in a guide ring assembly is thereby effective limits that each of the projection 8 in the receptacle 12 of an adjacent guide vane 1 is positively received. In addition, the vibration is damped by the occurring between the inner surfaces 14 of the receptacle 12 and the side surface 9 of the projection 8 Friction.
  • FIG. 4 shows a guide vane segment 15 consisting of three guide vanes 1.
  • Such guide vane segments, from which a ring-shaped vane assembly is formed serve for reinforcement of the individual guide vanes 1.
  • the guide vanes 1 made of plastic become not only by the form fit between the projection 8 and the receptacle 12 adjacent Guide vanes 1 and the friction present in the contact surface are connected to one another, but additionally at least on the side surface 9 of the projection 8 or the inner surface 14 of the receptacle 12 glued together.
  • the guide blades 1 can also their first and second end faces 7 and 13 may be glued together.
  • the adhesive connection between the side surface 9 of the projection 8 and the inner surface 14 of the receptacle 12 stressed under shear stresses during operation and is therefore clear more resilient than a bonded connection between the first and tensile / compression second end face 7 or 13.
  • a plurality of guide vane segments 15 are used to form an annular guide ring assembly assembled, which do not stick together to compensate for thermal expansion, but only by the positive connection between the projection 8 and the receptacle 12 are coupled to each other.
  • the interlocking causes by between the side surface 9 of the projection 8 and the inner surface 14 of the receptacle 12 friction occurring Damping effect and thus an improvement in the dynamic vibration behavior of the Guide vane 1.
  • the above-described limitation occurs due to the positive locking the vibration amplitude and a seal of the gaps between adjacent guide vane ice segments.
  • each guide vane 1 of a guide vane segment 15 is in the stiffening wall 4 outer platform 3, a bore 16 is provided, in which a (not shown) engages bolts on the housing and the guide vane against gas / flow forces is supported in the circumferential direction.
  • the stiffening wall 4 locally thickened around the bore 16 to reduce the surface pressure.
  • the hole 16 is designed as an elongated hole in the axial direction of the engine arrangement, so that the gas or Flow forces in the axial direction over the hook-like fastening means at the rear in the illustration 11 and not through the bolt into the engine housing.
  • FIG. 5 shows the guide vane segment 15 from FIG. 4 in a perspective view, in which the Profile of the blades 2 can be seen. It can also be seen that the Dimensioning of the projection 8 and the receptacle 12 are coordinated so that align the outer and inner platforms 3 and 5 when assembled.
  • the left part of the 5 shows the projections 8 on the outer and inner platforms 3, 5, that in a receptacle 12 of a guide vane 1 of an adjacent guide vane segment 15 positively received within a lead ring assembly, but is not glued.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)

Description

Die Erfindung betrifft eine Leitschaufel für eine Gasturbine, insbesondere eine Niederdruckturbine, mit einem Schaufelblatt, das sich zwischen einer inneren Plattform und einer äußeren Plattform erstreckt, wobei die äußere Plattform Befestigungsmittel zur Anbringung an einem Gehäuse aufweist, ein Leitschaufelsegment aus wenigstens drei Leitschaufeln sowie einen Leitkranzverbund.The invention relates to a guide vane for a gas turbine, in particular a low-pressure turbine, with an airfoil that sits between an inner platform and an outer platform, the outer platform securing means for attachment to a housing, a vane segment from at least three guide vanes and a guide ring assembly.

Leitschaufeln von Niederdruckturbinen bestehen aus Metall und werden in der Entwicklungsphase im allgemeinen zunächst zu Segmenten aus drei oder sechs Leitschaufeln zusammengelötet. Bei den Untersuchungen zur aerodynamischen Auslegung des Profils der Schaufelblätter werden wie bei einem realen Gasturbinentriebwerk mehrere Leitschaufelsegmente zu einem geschlossenen Leitkranzverbund zusammengesetzt, wobei die einzelnen Leitschaufelsegmente zum Ausgleich von Wärmedehnungen untereinander nicht starr miteinander verbunden sind. Die Leitschaufeln sind dabei an ihren äußeren Plattformen in einem (Triebwerks-)Gehäuse befestigt und an ihren inneren Plattformen durch Metallklammern oder dgl. lösbar miteinander verspannt. Durch das Verspannen an den inneren Plattformen soll das Schwingungsverhalten der Schaufelblätter verbessert werden. Die Verwendung der Verspannungsklammern als zusätzliche Bauteile hat den Nachteil einer aufwendigeren Montage und höherer Kosten.Guide vanes of low pressure turbines are made of metal and are in the development phase generally initially to segments of three or six guide vanes soldered together. In the investigations on the aerodynamic design The profile of the airfoils is like a real gas turbine engine put together several guide vane segments to form a closed guide ring assembly, the individual guide vane segments to compensate for thermal expansion are not rigidly interconnected. The guide vanes are attached to their outer platforms in a (engine) housing and releasably together on their inner platforms by metal clips or the like braced. By bracing the inner platforms, this is supposed to Vibration behavior of the airfoils can be improved. The use of the Tension clamps as additional components have the disadvantage of being more complex Assembly and higher costs.

Aus der DE-A-485 833 ist es bekannt, Leit- bzw. Laufschaufeln nach dem Prinzip einer Nut- und Federverbindung in der Weise formschlüssig zu verbinden, dass axiale Relativbewegungen benachbarter Schaufeln weitestgehend verhindert werden. Hierfür sind die innere und äußere Plattform der Schaufeln mit "Nuten und Federn" bzw. mit gekrümmten, komplementären Flächen versehen. Der stabile Schaufelverbund ist hier die Voraussetzung dafür, dass die Dichtfins der Labyrinthdichtungen an den Schaufelplattformen am komplett montierten Schaufelkranz gefertigt bzw. endbearbeitet werden können. Somit geht es bei diesem Patent um fertigungstechnische Aspekte.From DE-A-485 833 it is known to guide or guide blades according to the principle to connect a tongue and groove connection in a positive manner in such a way that axial Relative movements of adjacent blades are largely prevented. Therefor are the inner and outer platform of the blades with "grooves and tongues" or provided with curved, complementary surfaces. The stable blade combination is the prerequisite here that the sealing fins of the labyrinth seals on the Bucket platforms manufactured or finished on the completely assembled bucket ring can be. So this patent is about manufacturing technology Aspects.

Zur Kalibrierung von aerodynamischen Auslegungsverfahren und zur schnellen Ermittlung von Versuchsdaten von Druck-, Geschwindigkeits- oder Strömungsfeldmessungen werden alternativ Leitschaufeln aus meist kohlefaserverstärkten Kunststoffen eingesetzt und in sog. aerodynamischen "Kalt"-Prüfständen untersucht. Derartige Leitschaufeln sind erheblich schneller und kostengünstiger herzustellen als entsprechende Leitschaufeln aus Metall und werden daher in den vorgelagerten Untersuchungen bevorzugt eingesetzt. Im Prüfstand werden die Leitschaufeln aus Kunststoff unter erheblich geringeren Temperaturen (ca. 130° C) als im realen Betrieb, jedoch mit Gaskräften in der gleichen Größenordnung wie im realen Triebwerk belastet.For the calibration of aerodynamic design processes and for quick determination experimental data from pressure, speed or flow field measurements alternatively, guide vanes are made of mostly carbon fiber reinforced plastics used and examined in so-called aerodynamic "cold" test benches. such Guide vanes are much faster and cheaper to manufacture than corresponding ones Guide vanes made of metal and are therefore used in the upstream investigations preferably used. The guide vanes are made of plastic in the test bench at significantly lower temperatures (approx. 130 ° C) than in real operation, however loaded with gas forces of the same order of magnitude as in the real engine.

Problematisch ist dabei, die Geometrie der äußeren und inneren Plattform der Leitschaufeln aus Metall für jene aus Kunststoff zu übernehmen, da diese den Belastungen mit den hohen, realen Gaskräften nicht standhalten können. Das Verkleben von jeweils drei oder sechs Leitschaufeln zu einzelnen Leitschaufelsegmenten, aus denen der Leitkranzverbund gebildet wird, hat dieses Problem ebenso wenig gelöst, wie das Verspannen der Leitschaufeln mittels Bolzen, die in den seitlichen Stirnflächen der äußeren und inneren Plattformen vorgesehen sind. Die Schwingungsamplituden waren zu groß und führten zu Brüchen der Leitschaufeln.The problem here is the geometry of the outer and inner platform of the guide vanes made of metal for those made of plastic, as these are the loads cannot withstand the high, real gas forces. Gluing three or six guide vanes each to form individual guide vane segments the wreath of guiding rings has not solved this problem, like bracing the guide vanes by means of bolts that are in the lateral end faces the outer and inner platforms are provided. The vibration amplitudes were too large and caused the guide vanes to break.

Die EP-A-0 654 586 befasst sich mit Leitschaufelsegmenten aus Faserverbundmaterial, wobei jedes Segment mindestens zwei Schaufeln sowie ein inneres und ein äußeres Plattformsegment (Deckbandsegment) umfasst. Das innere Plattformsegment ist als durchgehend offenes, im Querschnitt etwa rechteckiges Hohlprofil ausgeführt, dessen Krümmung koaxial zur Triebwerksachse verläuft. An einem stirnseitigen Ende ist das Hohlprofil stufenartig verjüngt, so dass es weitgehend spielfrei und formschlüssig in das offene Ende eines benachbarten Hohlprofils passt. Auf diese Weise können benachbarte Leitschaufelsegmente über ihre inneren Plattformsegmente formschlüssig zusammengesteckt werden. Da die durchgehend offenen Hohlprofile (siehe u.a. Spalte 3, Zeilen 44 bis 46) noch relativ leicht verformbar sind (Querschnittsverformung), ist die sich insgesamt im Leitschaufelkranz ergebende Formstabilität und Steifigkeit nicht optimal. Die einfache, nachgiebige Ausführung der äußeren Plattformen wirkt sich zusätzlich negativ aus.EP-A-0 654 586 is concerned with guide vane segments made of fiber composite material, each segment having at least two blades and an inner and an outer Platform segment (cover band segment) includes. The inner platform segment is designed as a continuously open hollow section with a roughly rectangular cross section, whose curvature is coaxial to the engine axis. At one end the hollow profile is tapered in steps, so that it is largely free of play and positive fits into the open end of an adjacent hollow profile. In this way can adjacent vane segments over their inner platform segments be form-fitted together. Because the continuously open hollow profiles (see also column 3, lines 44 to 46) are still relatively easily deformable (cross-sectional deformation), is the overall dimensional stability resulting in the guide vane ring and stiffness not optimal. The simple, compliant execution of the outer platforms also have a negative impact.

Der Erfindung liegt die Aufgabe zugrunde, eine Leitschaufel der eingangs beschriebenen Gattung zu schaffen, die ein verbessertes dynamisches Schwingungsverhalten aufweist, die Schwingungsamplitude benachbarter Leitschaufeln begrenzt und fertigungstechnisch einfach und kostengünstig herzustellen ist.The invention has for its object a guide vane of the one described Generate genus that has an improved dynamic vibration behavior has, the vibration amplitude of adjacent guide vanes limited and manufacturing technology is easy and inexpensive to manufacture.

Die Lösung der Aufgabe ist erfindungsgemäß dadurch gekennzeichnet, dass die äußere Plattform und die innere Plattform als torsions- und biegesteife Hohlstrukturen ausgeführt sind, wobei die äußere Plattform eine Plattform, eine Versteifungswand, zwei mit Abstand zueinander verlaufende Querstreben und eine geschlossene Stirnfläche aufweist, und wobei die innere Plattform eine Plattform, eine Verstärkungswand und eine geschlossene Stirnfläche aufweist, dass die Vorsprünge integrale Elemente der geschlossenen Stirnflächen sind und schmale, ihre Umfangskontur bildende Seitenflächen aufweisen, und dass die offenen Stirnflächen der Plattformen mit ihren Innenflächen unmittelbar die Aufnahmen für die Vorsprünge einer benachbarten Leitschaufel bilden.The solution to the problem is characterized in that the outer Platform and the inner platform as torsion and rigid hollow structures are executed, the outer platform being a platform, a stiffening wall, two spaced-apart cross struts and a closed end face and wherein the inner platform is a platform, a reinforcement wall and has a closed end surface that the projections are integral Elements of the closed end faces are narrow, their peripheral contour have forming side faces, and that the open end faces of the platforms with their inner surfaces the receptacles for the projections of a neighboring one Form the guide vane.

Der Vorteil besteht u.a. darin, dass z.B. aneinander angrenzende Leitschaufeln benachbarter Leitschaufelsegmente (aus z.B. drei miteinander verbundenen Leitschaufeln) in Axialrichtung optimal formschlüssig miteinander gekoppelt sind und durch die Reibung an den Kontaktflächen ein Dämpfungseffekt entsteht. Zudem bewirken die Vorsprünge eine Abdichtung von zwischen den Plattformen auftretenden Spalten. Weiterhin ist die Struktursteifigkeit optimiert.The advantage is: in that e.g. adjacent vanes of adjacent Guide vane segments (e.g. from three interconnected guide vanes) are optimally coupled to one another in the axial direction and by the friction on the contact surfaces creates a damping effect. Also effect the protrusions seal off gaps occurring between the platforms. The structural rigidity is also optimized.

In einer bevorzugten Ausgestaltung verläuft die Seitenfläche jedes Vorsprungs rechtwinklig zur ersten, im allgemeinen in Radialrichtung verlaufenden Stirnfläche der äußeren oder inneren Plattform. Die Seitenfläche des Vorsprungs verläuft mithin in der durch die Gasströmung stark belasteten Umfangsrichtung und ermöglicht dort eine Dämpfung infolge von Reibung an den Kontaktflächen.In a preferred embodiment, the side surface of each projection runs perpendicular to the first, generally radial end face the outer or inner platform. The side surface of the projection therefore runs in the circumferential direction heavily loaded by the gas flow and enables there damping due to friction on the contact surfaces.

Bevorzugt steht die Seitenfläche jedes Vorsprungs wenigstens 3mm über die erste Stirnfläche der äußeren oder inneren Plattform vor, so dass eine ausreichend große Reib- bzw. Kontaktfläche mit der Aufnahme einer benachbarten Leitschaufel vorliegt.The side surface of each projection is preferably at least 3 mm above the first End face of the outer or inner platform, so that a sufficiently large Friction or contact surface with the recording of an adjacent guide vane is present.

Es ist vorteilhaft, dass jeder Vorsprung wenigstens 30 % der (Querschnitts-)Fläche der ersten Stirnfläche an der jeweiligen Plattform ausmacht, damit die benachbarten Leitschaufeln nicht lediglich punktuell miteinander gekoppelt sind und eine zuverlässige Begrenzung der Schwingungsamplitude ermöglicht wird.It is advantageous that each projection has at least 30% of the (cross-sectional) area the first end face on the respective platform so that the neighboring ones Guide vanes are not only coupled point-to-point and are reliable Limitation of the vibration amplitude is made possible.

Weiterhin ist es bevorzug, dass der Vorsprung mit Spiel in der Ausnahme der benachbarten Leitschaufel sitzt bzw. eingepasst ist, so dass sich beispielsweise aneinander angrenzende Leitschaufeln benachbarter Leitschaufelsegmente infolge von Wärmedehnungen problemlos voneinander weg und aufeinander zu bewegen können.Furthermore, it is preferred that the projection with play in the exception of the neighboring one The guide vane is seated or fitted so that, for example, one another adjacent guide vanes of adjacent guide vane segments as a result of Thermal expansion can move away from each other and towards each other without any problems.

Höchst bevorzugt verläuft eine an die zweite Stirnfläche angrenzende Innenfläche der Aufnahme im montierten Zustand parallel zur Seitenfläche des Vorsprungs, so dass ein sicherer Reibkontakt zwischen der Innenfläche der Aufnahme und er Seitenfläche des Vorsprungs gewährleistet ist. An inner surface adjacent to the second end surface runs most preferably the recording in the assembled state parallel to the side surface of the projection, so that a secure frictional contact between the inner surface of the receptacle and the side surface the lead is guaranteed.

In einer bevorzugten Ausgestaltung ist die Leitschaufel einstückig ausgebildet, so daß sie kostengünstig durch Metall- oder Spritzgußverfahren hergestellt werden kann.In a preferred embodiment, the guide vane is formed in one piece, so that it is inexpensive can be made by metal or injection molding.

Höchst bevorzugt besteht die Leitschaufel aus kohlefaserverstärktem Kunststoff, so daß sie sich in sog. aerodynamischen "Kalt"-Prüfständen untersuchen läßt. Hiermit lassen sich deutlich schneller und kostengünstiger Versuchsdaten zur Kalibrierung von aerodynamischen Auslegungsverfahren ermitteln, als dieses beim Einsatz von Leitschaufeln aus Metall der Fall ist. Derartige Versuchsleitschaufeln aus Kunststoff lassen sich durch Verkleben ebenfalls zu Leitschaufelsegmenten aus drei oder sechs Leitschaufeln verbinden. Die Seitenfläche des Vorsprungs bietet dafür Klebflächen an, die im Gegensatz zu den ersten und zweiten Stirnflächen der äußeren bzw. inneren Plattformen nicht auf Zug/Druck, sondern auf Scherung beansprucht werden. Dieses ist die deutlich günstigere Belastungsform für Klebverbindungen.Most preferably, the guide vane is made of carbon fiber reinforced plastic, so that it is can be examined in so-called aerodynamic "cold" test benches. This makes it clear faster and less expensive test data for the calibration of aerodynamic design processes determine than is the case when using metal guide vanes. such Experimental guide vanes made of plastic can also be glued to guide vane segments connect from three or six guide vanes. The side surface of the tab offers adhesive surfaces that are in contrast to the first and second end surfaces the outer and inner platforms are not subjected to tension / compression, but to shear become. This is the much cheaper form of stress for adhesive bonds.

Weitere Ausgestaltungen der Erfindung sind in den Unteransprüchen beschrieben.Further refinements of the invention are described in the subclaims.

Im folgenden wird die Erfindung anhand eines Ausführungsbeispiels unter Bezugnahme auf eine Zeichnung näher erläutert. Es zeigt:

Fig. 1
einen Längsschnitt in perspektivischer Darstellung eines Ausführungsbeispiels der erfindungsgemäßen Leitschaufel,
Fig. 2
eine Seitenansicht der Leitschaufel aus Fig. 1,
Fig. 3
eine Seitenansicht der schwingenden Leitschaufel aus Fig. 1 und 2,
Fig.
4 einen Längsschnitt in perspektivischer Darstellung eines Leitschaufelsegments aus drei Leitschaufeln gemäß Fig. 1 bis 3 und
Fig. 5
eine perspektivische Darstellung des Leitschaufelsegments aus Fig. 4.
The invention is explained in more detail below using an exemplary embodiment with reference to a drawing. It shows:
Fig. 1
2 shows a longitudinal section in perspective representation of an exemplary embodiment of the guide vane according to the invention,
Fig. 2
2 shows a side view of the guide vane from FIG. 1,
Fig. 3
2 shows a side view of the vibrating guide vane from FIGS. 1 and 2,
FIG.
4 shows a longitudinal section in perspective representation of a guide vane segment comprising three guide vanes according to FIGS. 1 to 3 and
Fig. 5
3 shows a perspective illustration of the guide vane segment from FIG. 4.

Fig. 1 zeigt ein im ganzen mit 1 bezeichnetes Ausführungsbeispiel der erfindungsgemäßen Leitschaufel, die aus kohlefaserverstärkten Kunststoff besteht und im Spritzgußverfahren hergestellt ist. Eine solche Leitschaufel 1 wird in sog. aerodynamischen "Kalt"-Prüfständen eingesetzt, um schnell und kostengünstig Versuchsdaten aus Druck- Geschwindigkeits- und Strömungsfeldmessungen zur Kalibrierung von aerodynamischen Auslegungsverfahren zu ermitteln.1 shows an exemplary embodiment of the guide vane according to the invention, designated by 1, which is made of carbon fiber reinforced plastic and manufactured by injection molding is. Such a guide vane 1 is used in so-called aerodynamic "cold" test benches Fast and inexpensive test data from pressure, speed and flow field measurements for the calibration of aerodynamic design processes.

Die Leitschaufel 1 umfaßt ein Schaufelblatt 2, eine äußere Plattform 3 aus einer Plattform 3' und einer mit Abstand dazu angeordneten Versteifungswand 4 sowie eine innere Plattform 5 aus einer Plattform 5' und einer damit verbundenen und sich ebenfalls mit Abstand dazu erstreckenden Verstärkungswand 6. Sowohl die äußere als auch die innere Plattform 3 bzw. 5 ist an einer ersten Stirnfläche 7 mit einem Vorsprung 8 versehen, der jeweils eine über die erste Stirnfläche 7 um etwa 3 mm vorstehende Seitenfläche 9 aufweist.The guide vane 1 comprises an airfoil 2, an outer platform 3 from a platform 3 'and a spaced stiffening wall 4 and an inner platform 5 from one Platform 5 'and an associated and also extending at a distance from it Reinforcement wall 6. Both the outer and inner platforms 3 and 5 are on one first end face 7 is provided with a projection 8, each of which over the first end face 7 has about 3 mm protruding side surface 9.

Wenn mehrere Leitschaufeln 1 zu einem ringförmigen Leitkranzverbund zusammengesetzt und in einem Triebwerksgehäuse befestigt sind, ist das Schaufelblatt 2 mit seiner zwischen der äußeren und inneren Plattform 3 bzw. 5 verlaufenden Längserstreckung im wesentlichen in Radialrichtung der Triebwerksanordnung angeordnet.If several guide blades 1 are assembled into an annular guide ring assembly and are fixed in an engine housing, the airfoil 2 with its between the outer and inner platform 3 or 5 extending longitudinal extent substantially in the radial direction the engine assembly arranged.

Fig. 2 zeigt die Leitschaufel 1 aus Fig. 1 in einer Seitenansicht, in der die im wesentlichen parallel zur (äußeren) Plattform 3' verlaufende Versteifungswand 4 sowie mit der (inneren) Plattform 5' verbundene, sich über mehrere Ecken erstreckende Verstärkungswand 6 dargestellt sind. An der äußeren Plattform 3 sind zwei hakenartige Befestigungsmittel 11 zur Anbringung der Leitschaufel 1 an einem (nicht gezeigten) Triebwerksgehäuse ausgebildet. Der zwischen der (äußeren) Plattform 3', der Versteifungswand 4 und sich dazwischen erstreckenden Querstreben 10 einerseits sowie der (inneren) Plattform 5' und der Verstärungswand 6 andererseits vorliegende Hohlraum bildet jeweils eine Aufnahme 12, mit der die zweite Stimfläche 13 der äußeren und inneren Plattform 3 bzw. 5 versehen ist.Fig. 2 shows the guide vane 1 of Fig. 1 in a side view, in which the substantially parallel to the (outer) platform 3 'stiffening wall 4 and with the (inner) platform 5 'connected reinforcement wall 6, which extends over several corners are. On the outer platform 3 are two hook-like fastening means 11 for attachment the guide vane 1 is formed on an engine housing (not shown). The between the (outer) platform 3 ', the stiffening wall 4 and transverse struts extending therebetween 10 on the one hand and the (inner) platform 5 'and the reinforcement wall 6 on the other hand Each cavity forms a receptacle 12 with which the second end face 13 of the outer and inner platform 3 and 5 is provided.

Wenn mehrere Leitschaufeln 1 zu einem Leitkranzverbund zusammengesetzt werden, wird ein Vorsprung 8 einer benachbarten Leitschaufel 1 in dieser Aufnahme 12 formschlüssig aufgenommen, wobei deren Dimensionierung auf jene des Vorsprungs 8 so abgestimmt ist, daß die äußeren und innerne Plattformen 3 bzw. 5 benachbarter Leitschaufeln 1 im montierten Zustand fluchten, wie dieses in Fig. 4 und 5 zu erkennen ist. Die Aufnahme 12 besitzt eine an die zweite Stirnfläche 13 angrenzende Innenfläche 14, die im montierten Zustand aufgrund der abgestimmten Dimensionierung des Vorsprungs 8 und der Aufnahme 12 eine Kontaktfläche mit der Seitenfläche 9 des Vorsprungs 8 bildet. Auf diese Weise wird zudem eine Abdichtung zwischen benachbarten Leitschaufeln 1 erzielt. In Fig. 2 ist zu erkennen, daß der Vorsprung 8 und die Aufnahme 12 mehr als 50 % der in der Bildebene liegenden Querschnittsfläche der ersten bzw. zweiten Stimfläche 7 bzw. 13 ausmachen.If several guide vanes 1 are assembled to form a guide ring assembly, a Projection 8 of an adjacent guide vane 1 is positively received in this receptacle 12, the dimensions of which are matched to those of the projection 8 so that the outer and inner platforms 3 and 5 adjacent guide vanes 1 in the assembled state aligned, as can be seen in FIGS. 4 and 5. The receptacle 12 has one to the second End face 13 adjacent inner surface 14, which in the assembled state due to the coordinated Dimensioning of the projection 8 and the receptacle 12 a contact surface with the Side surface 9 of the projection 8 forms. This also creates a seal between neighboring vanes 1 achieved. In Fig. 2 it can be seen that the projection 8 and the Image 12 more than 50% of the cross-sectional area of the first or Make out the second end face 7 or 13.

Fig. 3 zeigt eine einzelne, in Axialrichtung schwingende Leitschaufel 1, wobei zwei unterschiedliche Schwingungszustände dargestellt sind. Die in Fig. 3 insbesondere an der inneren Plattform 5 bzw. deren der Verstärkungswand 6 deutlich zu erkennende Schwingungsamplitude wird bei der in einem Leitkranzverbund angeordneten, erfindungsgemäßen Leitschaufel 1 dadurch wirksam begrenzt, daß jeweils der Vorsprung 8 in der Aufnahme 12 einer benachbarten Leitschaufel 1 formschlüssig aufgenommen ist. Zudem erfolgt eine Dämpfung der Schwingung durch die zwischen den Innenflächen 14 der Aufnahme 12 und der Seitenfläche 9 des Vorsprungs 8 auftretende Reibung.3 shows a single guide vane 1 vibrating in the axial direction, two different ones Vibration states are shown. 3 in particular on the inner platform 5 or the vibration amplitude of the reinforcement wall 6, which is clearly recognizable at the guide vane 1 according to the invention arranged in a guide ring assembly is thereby effective limits that each of the projection 8 in the receptacle 12 of an adjacent guide vane 1 is positively received. In addition, the vibration is damped by the occurring between the inner surfaces 14 of the receptacle 12 and the side surface 9 of the projection 8 Friction.

Fig. 4 zeigt ein aus drei Leitschaufeln 1 bestehendes Leitschaufelsegment 15. Derartige Leitschaufelsegmente, aus denen ein ringförmiger Leitkranzverbund gebildet wird, dienen zur Verstärkung der einzelnen Leitschaufeln 1. Die aus Kunststoff bestehenden Leitschaufeln 1 werden nicht nur durch den Formschluß zwischen dem Vorsprung 8 und der Aufnahme 12 benachbarter Leitschaufeln 1 sowie die in der Kontaktfläche vorliegende Reibung miteinander verbunden, sondern zusätzlich wenigstens an der Seitenfläche 9 des Vorsprungs 8 bzw. der Innenfläche 14 der Aufnahme 12 miteinander verklebt. Zusätzlich können die Leitschaufeln 1 auch an ihren ersten und zweiten Stirnflächen 7 bzw. 13 miteinander verklebt sein. Die Klebverbindung zwischen der Seitenfläche 9 des Vorsprungs 8 und der Innenfläche 14 der Aufnahme 12 wird unter den im Betrieb auftretenden Belastungen auf Scherung beansprucht und ist somit deutlich höher belastbar als eine auf Zug/Druck beanspruchte Klebverbindung zwischen der ersten und zweiten Stimfläche 7 bzw. 13.4 shows a guide vane segment 15 consisting of three guide vanes 1. Such guide vane segments, from which a ring-shaped vane assembly is formed serve for reinforcement of the individual guide vanes 1. The guide vanes 1 made of plastic become not only by the form fit between the projection 8 and the receptacle 12 adjacent Guide vanes 1 and the friction present in the contact surface are connected to one another, but additionally at least on the side surface 9 of the projection 8 or the inner surface 14 of the receptacle 12 glued together. In addition, the guide blades 1 can also their first and second end faces 7 and 13 may be glued together. The adhesive connection between the side surface 9 of the projection 8 and the inner surface 14 of the receptacle 12 stressed under shear stresses during operation and is therefore clear more resilient than a bonded connection between the first and tensile / compression second end face 7 or 13.

Zur Bildung eines ringförmigen Leitkranzverbunds werden mehrere Leitschaufelsegmente 15 zusammengesetzt, wobei diese zum Ausgleich von Wärmedehnungen nicht miteinander verklebt, sondern lediglich durch den Fomschluß zwischen dem Vorsprung 8 und der Aufnahme 12 aneinander gekoppelt sind. Der Formschluß bewirkt jedoch durch die zwischen der Seitenfläche 9 des Vorsprungs 8 und der Innenfläche 14 der Aufnahme 12 auftretende Reibung einen Dämpfungseffekt und somit eine Verbesserung des dynamischen Schwingungsverhaltens der Leitschaufel 1. Darüber hinaus erfolgt durch den Formschluß die oben beschriebene Begrenzung der Schwingungsamplitude und eine Abdichtung der Spalten zwischen benachbarten Leitschaufeisegmenten.A plurality of guide vane segments 15 are used to form an annular guide ring assembly assembled, which do not stick together to compensate for thermal expansion, but only by the positive connection between the projection 8 and the receptacle 12 are coupled to each other. However, the interlocking causes by between the side surface 9 of the projection 8 and the inner surface 14 of the receptacle 12 friction occurring Damping effect and thus an improvement in the dynamic vibration behavior of the Guide vane 1. In addition, the above-described limitation occurs due to the positive locking the vibration amplitude and a seal of the gaps between adjacent guide vane ice segments.

In jeweils einer Leitschaufel 1 eines Leitschaufelsegments 15 ist in der Versteifungswand 4 der äußeren Plattform 3 eine Bohrung 16 vorgesehen, in die ein (nicht dargestellter) gehäuseseitiger Bolzen eingreift und die Leitschaufel gegen Gas/Strömungskräfte in Umfangsrichtung abstützt. Wie in Fig. 4 gezeigt, ist die Versteifungswand 4 um die Bohrung 16 herum zur Reduzierung der Flächenpressung örtlich verdickt. Die Bohrung 16 ist in Axialrichtung der Triebwerksanordnung als Langloch ausgebildet, so daß die Gas- bzw. Strömungskräfte in Axialrichtung über den in der Darstellung hinteren, hakenartigen Befestigungsmittel 11 und nicht über den Bolzen in das Triebwerksgehäuse geleitet werden.In each guide vane 1 of a guide vane segment 15 is in the stiffening wall 4 outer platform 3, a bore 16 is provided, in which a (not shown) engages bolts on the housing and the guide vane against gas / flow forces is supported in the circumferential direction. As shown in FIG. 4, the stiffening wall 4 locally thickened around the bore 16 to reduce the surface pressure. The hole 16 is designed as an elongated hole in the axial direction of the engine arrangement, so that the gas or Flow forces in the axial direction over the hook-like fastening means at the rear in the illustration 11 and not through the bolt into the engine housing.

Fig. 5 zeigt das Leitschaufelsegment 15 aus Fig. 4 in perspektivischer Darstellung, in der das Profil der Schaufelblätter 2 andeutungsweise zu erkennen ist. Es ist ferner zu erkennen, daß die Dimensionierung des Vorsprungs 8 und der Aufnahme 12 so aufeinander abgestimmt sind, daß die äußere und innere Plattform 3 bzw. 5 im montierten Zustand fluchten. Im linken Teil der Zeichnung gemäß Fig. 5 sind die Vorsprünge 8 an der äußeren und inneren Plattform 3,5 dargestellt, die in einer Aufnahme 12 einer Leitschaufel 1 eines benachbarten Leitschaufelsegments 15 innerhalb eines Leitkranzverbundes formschlüssig aufgenommen, jedoch nicht verklebt wird.FIG. 5 shows the guide vane segment 15 from FIG. 4 in a perspective view, in which the Profile of the blades 2 can be seen. It can also be seen that the Dimensioning of the projection 8 and the receptacle 12 are coordinated so that align the outer and inner platforms 3 and 5 when assembled. In the left part of the 5 shows the projections 8 on the outer and inner platforms 3, 5, that in a receptacle 12 of a guide vane 1 of an adjacent guide vane segment 15 positively received within a lead ring assembly, but is not glued.

Claims (18)

  1. Guide vane (1) for a gas turbine, in particular a low-pressure turbine, with a blade (2) which extends between an inner platform (5) and an outer platform (3), such that the outer platform (3) comprises attachment means (11) for fixing to a housing, with an end face (7) directed towards one circumferential direction and an end face (13) directed towards the opposite circumferential direction on both platforms (3, 5), with projections (8) on one end face (7) and with recesses (12) on the other end face (13) for an at least axially formenclosing connection with neighbouring guide vanes by virtue of corresponding projections and recesses,
    characterised in that
    the outer platform (3) and the inner platform (5) are formed as hollow structures rigid against torsion and bending, the outer platform (3) having a platform (3') a stiffening wall (4), two crossbars (10) extending a distance apart, and a closed end face (7), and the inner platform (5) having a platform (5'), a reinforcing wall (6) and a closed end face (7), the projections (8) being integral elements of the closed end faces (7) and having narrow side surfaces (9) which form their contour, and the open end faces (13) of the platforms (3, 5) directly forming with their inside surfaces (14) the recesses (12) for the projections of an adjacent guide vane.
  2. Guide vane according to Claim 1,
    characterised in that
    the side surface (9) of each projection (8) extends perpendicularly to the first end face (7).
  3. Guide vanes according to Claims 1 or 2,
    characterised in that
    the side surface (9) of each projection (8) projects at least 3 mm proud of the first end face (7).
  4. Guide vane according to Claims I or 2,
    characterised in that
    the side surface (9) of each projection (8) projects at least 5 mm proud of the first end face (7).
  5. Guide vane according to any of the preceding claims,
    characterised in that
    each projection (8) and each recess (12) occupies at least 30% of the (cross-sectional) area of the first or second end face (7 or 13), respectively, on the corresponding platform (3, 5).
  6. Guide vane according to any of Claims 1 to 4,
    characterised in that
    each projection (8) occupies at least 50% of the (cross-sectional) area of the first end face (7) on the corresponding platform (3, 5).
  7. Guide vane according to any of the preceding claims,
    characterised in that
    each projection (8) fits into the recess (12) with some clearance.
  8. Guide vane according to any of the preceding claims,
    characterised in that
    the inner surface (14) of each recess (12) adjacent to the second end face (13) extends parallel to the side surface (9) of the projection (8) in the mounted condition.
  9. Guide vane according to any of the preceding claims,
    characterised in that
    the stiffening wall (4) extends essentially parallel to the platform (3').
  10. Guide vane according to Claim 9,
    characterised in that
    the crossbars (10) extend over the full width (B) of the platform (3').
  11. Guide vane according to Claims 9 or 10,
    characterised in that
    the wall thicknesses of the platforms (3', 5'), the reinforcing and stiffening wall (4, 6) and the crossbars (10) are in each case constant.
  12. Guide vane according to any of Claims 9 to 11,
    characterised in that
    the wall thicknesses of the platforms (3', 5'), the reinforcing and stiffening wall (4, 6) and the crossbars (10) are all approximately equal.
  13. Guide vane according to any of the preceding claims,
    characterised in that
    it is formed in one piece.
  14. Guide vane according to any of the preceding claims,
    characterised in that
    the guide vane (1) consists of fibre-reinforced plastic.
  15. Guide vane according to any of Claims 1 to 13,
    characterised in that
    the guide vane (1) is made of metal.
  16. Guide-vane segment comprising at least three guide vanes according to any of the preceding Claims,
    characterised in that
    in each case two projections (8) fit in a form-enclosed way into two recesses (12) of an adjacent guide vane (1), and adjacent guide vanes (1) are bonded to one another at least on the side surface (9) of each recess (8).
  17. Guide-vane segment according to Claim 16,
    characterised in that
    at least one guide vane (1) has a hole (16) in the stiffening wall (4) in the radial direction, in which a bolt on the housing engages.
  18. Guide-vane ring combination of guide-vane segments according to Claims 16 or 17,
    characterised in that
    in each case two projections (8) fit in a form-enclosed way into two recesses (12) of a guide vane (1) of an adjacent guide-vane segment (15).
EP98114445A 1997-08-23 1998-08-01 Guide vane for a gas turbine Expired - Lifetime EP0899426B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE29715180U 1997-08-23
DE29715180U DE29715180U1 (en) 1997-08-23 1997-08-23 Guide blade for a gas turbine

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Publication Number Publication Date
EP0899426A2 EP0899426A2 (en) 1999-03-03
EP0899426A3 EP0899426A3 (en) 1999-12-08
EP0899426B1 true EP0899426B1 (en) 2003-04-02

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP98114445A Expired - Lifetime EP0899426B1 (en) 1997-08-23 1998-08-01 Guide vane for a gas turbine

Country Status (4)

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US (1) US6217282B1 (en)
EP (1) EP0899426B1 (en)
JP (1) JPH11107704A (en)
DE (2) DE29715180U1 (en)

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Also Published As

Publication number Publication date
JPH11107704A (en) 1999-04-20
EP0899426A2 (en) 1999-03-03
DE29715180U1 (en) 1997-10-16
DE59807705D1 (en) 2003-05-08
EP0899426A3 (en) 1999-12-08
US6217282B1 (en) 2001-04-17

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