EP3170986B1 - Blade cluster with circumferential retention device - Google Patents

Blade cluster with circumferential retention device Download PDF

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Publication number
EP3170986B1
EP3170986B1 EP16195409.4A EP16195409A EP3170986B1 EP 3170986 B1 EP3170986 B1 EP 3170986B1 EP 16195409 A EP16195409 A EP 16195409A EP 3170986 B1 EP3170986 B1 EP 3170986B1
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EP
European Patent Office
Prior art keywords
securing
rib
guide vane
ribs
circumferential direction
Prior art date
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EP16195409.4A
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German (de)
French (fr)
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EP3170986A1 (en
Inventor
Markus Schlemmer
Oliver Thiele
Bernd Kislinger
Wilfried SCHÜTTE
Manuel Hein
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MTU Aero Engines AG
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MTU Aero Engines AG
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Publication date
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Publication of EP3170986A1 publication Critical patent/EP3170986A1/en
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Classifications

    • 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
    • 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
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2240/20—Rotors
    • F05D2240/24—Rotors for turbines
    • 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

Definitions

  • the invention relates to a stator blade segment for a gas turbine, in particular an aircraft gas turbine, comprising at least one radially outer shroud and a radially inner shroud extending along a respective arc and together form a ring portion, wherein in the radial direction between the outer shroud and the inner shroud more Guide vanes are arranged side by side in the circumferential direction, which are materially connected to the inner shroud and the outer shroud, in particular integrally connected, wherein the outer shroud comprises an axial front longitudinal wall member and an axially rear end wall element, such that the outer shroud and the two end walls in longitudinal section form a trough-like profile, wherein an associated reinforcing rib is formed on the outer shroud for each vane, which extends between the two end walls.
  • the object of the invention is to improve a guide blade segment with regard to its installation and securing in an associated housing so that the above disadvantages can be overcome.
  • At least one guide vane on the rear end wall at least two adjacently arranged securing ribs are formed, wherein a limited by the two securing ribs in the circumferential direction space is tapered from radially outside to radially inside.
  • the two securing ribs are formed by a first securing rib and a second securing rib, wherein the first securing rib is connected to the reinforcing rib of the circumferentially inwardly associated associated guide vane.
  • the second securing rib is formed only in the rear end wall.
  • the configuration of the two securing ribs represents an optimized adaptation of the structural rigidity to the relevant guide blade in combination with the desired circumferential securing by the two securing ribs.
  • first securing rib and the second securing rib have mutually different rib widths relative to a width direction running along a circumferential direction tangent, wherein the circumferential direction tangent lies at the same radial distance from the center of the circle segment.
  • first securing rib and / or the second securing rib have a width that increases from radially outside to radially inside.
  • first and second securing ribs have mutually different rib heights measured at the same radial distance from the center of the circle segment in the axial direction.
  • the first securing rib at the same radial distance from the center of the circle segment have a greater rib height and a larger rib width than the second securing rib.
  • the shaping can in particular also be optimized to that effect that an improved surface pressure between the securing ribs and an adjacent housing component, in particular a housing groove receiving the two securing ribs, can be achieved.
  • the guide blade segments used in a gas turbine in particular an aircraft gas turbine, to be provided with an optimum circumferential securing for each operating state of the gas turbine.
  • the vane segment preferably comprises at least three, more preferably four to six vanes, wherein the two securing ribs are associated, relative to the circumferential direction, of an inner vane (16, 16a), preferably the second or the third or the fourth vane.
  • the vane segment may also have a different number of vanes, in particular 7 or more. More generally, the two securing ribs are arranged in a central region of the rear end wall with respect to the circumferential direction or associated with a vane adjacent to the center of the end wall or associated with an odd number of vanes of the middle vane ,
  • the two securing ribs are formed integrally with the rear end wall, in particular in one piece with the vane segment.
  • the invention also relates to a gas turbine, in particular aircraft gas turbine with at least one annular vane module, which is composed of a plurality of vane segments described above.
  • the guide vane module may be part of a turbine stage, in particular a turbine stage of a low-pressure turbine.
  • a housing element of the turbine in particular the low-pressure turbine is designed such that it is in positive or / and frictional connection with the securing ribs of at least one vane segment, such that the vane segment during operation of the gas turbine, at least in the circumferential direction is held by the connection between the housing and securing ribs. It is preferred that the connection between the housing and securing ribs is formed by a groove receiving the securing ribs.
  • FIG. 1 in simplified perspective illustrated vane element 10 comprises a radially inner shroud 12 (bottom in FIG. 1 ), a radially outer shroud 14 (at the top in FIG FIG. 1 ) and a plurality of guide vanes 16, which are arranged in the radial direction RR between the two shrouds 12 and 14. In the circumferential direction a plurality of guide vanes 16 are arranged side by side.
  • the two shrouds 14, 16 form a ring portion, wherein a plurality of Leitschaufelsegmente, which are assembled to a Leitschaufelring (not shown) in the radial direction RR and in the circumferential direction UR define an annular channel through which a fluid, in particular hot gas can flow in the axial direction AR ,
  • the guide vanes 16 are preferably materially connected to the two shrouds 12 and 14, in particular integrally formed.
  • a vane segment 10 can in particular be produced by casting from metal.
  • the guide vanes 16 are preferably hollow.
  • openings 18 can be seen, which are in communication with the cavity of the individual vanes 16 and which serve in particular to remove the casting core after the casting of the vane segment 10 from the individual vanes 16 again.
  • a front end wall 20 and a rear end wall 22 are provided in the axial direction AR, which protrude radially from the shroud 16 outwardly, such that the shroud 16 and the end walls 20, 22 a trough-like profile in a to the axial direction AR parallel longitudinal section have.
  • the end walls 20, 22 are inclined relative to the radial direction, preferably at an angle of about 20 ° to 45 °.
  • the guide vanes 16 have a flow or blade profile with a non-visible due to the viewing angle convex suction side and a concave pressure side 24, wherein the suction side and the pressure side 24 via a front edge 26 and a trailing edge 28 are interconnected.
  • Hot gas flows in a substantially axial direction AR in the flow channels 30 formed by the shrouds 12, 14 and the guide vanes 16 due to the flow profiles of the vanes 16 acts in the embodiment shown in the circumferential direction UR to the left (or counterclockwise) force acting on the Guide vane segment 10.
  • each guide vane 16 in the radially outer shroud 14 may be assigned a reinforcing rib 32 in order to support the forces acting on the shroud 14 and the end walls 20, 22.
  • the forces acting on hot gas in the circumferential direction UR forces are further supported by at least two securing ribs 34, 36 on a housing (not shown) receiving the guide vane segment 10 so that the vane segment 10 or a Leitschaufelsegmenten formed of a turbine stage of a Gastrubine in Circumference is secured.
  • first locking rib 34 and a second locking rib 36 will be described below with reference to the enlarged view of FIG. 2 explained, the dashed bordered area II of Fig. 1 equivalent.
  • the first securing rib 34 extends in the radial direction RR from an upper edge 38 of the end wall 22 downwardly or radially inwardly. In its upper region, starting from the upper edge 38, it has a transition region 35, which is preferably inclined or step-like. In its lower region, it goes directly into the vane 16a (transition region) 39 (FIG. Fig. 1 ) associated with reinforcing rib 32a.
  • the first securing rib 34 has a width extending in the circumferential direction UR or along a circumferential direction tangent, the width increasing from radially outward to radially inward. In the axial direction, the first securing rib 34 projects from the end wall 22 and has an associated height which extends in the axial direction.
  • the second securing rib 36 also extends in the radial direction RR from the upper edge 38 of the end wall 22 downwards or radially inward. In its upper region, starting from the upper edge 38, it has a transition region 37, which is preferably inclined or step-like. However, the second securing rib ends in the radial direction RR in a closing region 41 between end wall 22 and shroud 14, which is in this Presentation is only hinted at.
  • the second securing rib 36 is thus preferably provided only on the end wall 22 and has no rib-like continuation or connection to another reinforcing rib of a guide vane.
  • the second securing rib 36 also has a width extending in the circumferential direction UR or along a circumferential direction tangent, the width increasing from radially outward to radially inward. In the axial direction, the second securing rib 36 projects from the end wall 22 and has an associated height extending in the axial direction.
  • the first securing rib 34 and the second securing rib 36 are arranged at a distance RA from one another, which corresponds to a width of an intermediate space 40 formed between the two securing ribs 34, 36.
  • the width RA of the intermediate space 40 decreases from radially outside to radially inside.
  • the gap 40 is thus tapered from radially outward to radially inward or narrowing.
  • This tapering of the intermediate space 40 is formed by a first inner wall 42 of the first securing rib 34 facing the intermediate space 40 and a second inner wall 44 of the second securing rib 36 facing the intermediate space 40 being inclined relative to one another.
  • both inner walls 42, 44 are inclined, at least in relation to a plane spanned by the radial direction RR and the axial direction, which in the present representation runs essentially orthogonal to the plane of the drawing.
  • Each securing rib 34, 36 has an outer wall 46 or 48 facing away from the intermediate space 40, wherein the outer wall 46 is assigned to the first securing rib 34 and the outer wall 48 is assigned to the second securing rib.
  • the two securing ribs 34, 36 are received in a common groove formed on a housing, such that the two outer walls 46, 48 can come into contact with corresponding inner sides of the housing groove, not shown. This planar contact of the outer walls 46, 48 on the insides of the housing groove allows a support of the stator blade segment in the circumferential direction of the housing.
  • the outer walls 46, 48 of the first securing rib 34 and the second securing rib 36 preferably extend substantially parallel or slightly convergent from one another radially inward to radially outward. If the outer walls 46, 48 formed in this manner, the vane member 10 in the radial direction easily and easily be inserted into the securing ribs 34, 36 receiving groove of the housing.
  • the groove of the housing can be made particularly easy if the groove in the circumferential direction bounding walls also substantially parallel or from radially inward to radially outwardly slightly convergent to each other.
  • the width of the first securing rib 34 is greater between the radially outer transition region 35 and the radially inner transition region 39 over the entire radial length than the width of the second securing rib 36 between its radially outer transition region 37 and its termination region 41.
  • the height, d. H. the extent in the axial direction, the first securing rib 34 between the transition region 35 and the transition region 39 is greater than the height of the second securing rib 36 between the transition region 37 and the termination region 41.
  • the cross-sectional area of the first securing rib 34th This is true for the embodiment shown here for the entire radial length of the first and second securing ribs 34, 36. Accordingly, the outer surface 46 of the first securing rib 34 is larger than the outer surface 48 of the second securing rib 36 ,
  • the dimensioning of the two securing ribs takes place in consideration of the arrangement of the guide vanes 16 and their blade profile and the associated force effects in the circumferential direction on the vane segment 10.
  • act in the present embodiment when flowing through hot gas through the vane segment 10 and by a closed Leitschaufelring larger compressive forces in the circumferential direction to the left (counterclockwise), so that larger forces in the circumferential direction by means of the first securing rib 34 must be supported during operation.
  • the larger outer surface 46 of the first securing rib 34 allows sufficient surface pressure and support of the guide vane segment 10 on the housing or the groove provided in the housing.
  • the radially inwardly to radially inwardly decreasing width RA of the gap 40 is effected by the increasing width of the first and second securing ribs 34, 36.
  • the two securing ribs 34, 36 thus have their greatest width radially inward, based on the radial length of the two securing ribs 34, 36 below (radially inward) of their respective center. In this way, in particular in the transition region between the reinforcing rib 32a of the guide vane 16a acting forces that are greater than those that still act radially outward, optimally over the shroud 14, the end wall 22 and the securing ribs 34, 36 are supported.
  • the embodiment shown here is purely exemplary.
  • the first and the second securing ribs 34, 36 could also be interchanged, for example, if the guide vanes 16 were configured differently with their blade profile, in particular the pressure side and the suction side would be reversed, so that larger compressive forces would act in the circumferential direction to the right (clockwise).
  • the dimensioning of the two securing ribs can be adapted to different gas turbines or different housing. Different shapes and dimensions of the two securing ribs 34, 36 can already be taken into account during the production of a guide blade segment 10, so that a finished, in particular cast guide blade element 10 already has the two securing ribs 34, 36, which are formed integrally with the guide blade segment.
  • an optimized setting of the surface pressure between the securing ribs and the housing groove can be achieved by the choice and dimensioning of the two securing ribs. Furthermore, there is a cost savings in the housing production by choosing an optimized distance between the two securing ribs, by the elimination of additional processing steps, such as application of solder material or insertion of locking pins and the like.
  • the two securing ribs 34, 36 thus allow a total of flexible adaptation to the necessary structural conditions of a gas turbine type, in which the guide blade segments are to be used.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

Die Erfindung betrifft ein Leitschaufelsegment für eine Gasturbine, insbesondere Fluggasturbine, umfassend wenigstens ein radial äußeres Deckband und ein radial inneres Deckband, die sich entlang eines jeweiligen Kreisbogens erstrecken und gemeinsam einen Ringabschnitt bilden, wobei in radialer Richtung zwischen dem äußeren Deckband und dem inneren Deckband mehrere Leitschaufeln in Umfangsrichtung nebeneinander angeordnet sind, die mit dem inneren Deckband und dem äußeren Deckband materialschlüssig verbunden, insbesondere einstückig verbunden sind, wobei das äußere Deckband bezogen auf eine axiale Längsrichtung ein axial vorderes Stirnwandelement und ein axial hinteres Stirnwandelement umfasst, derart dass das äußere Deckband und die beiden Stirnwände im Längsschnitt ein wannenartiges Profil bilden, wobei am äußeren Deckband für jede Leitschaufel eine zugeordnete Verstärkungsrippe ausgebildet ist, die sich zwischen den beiden Stirnwänden erstreckt.The invention relates to a stator blade segment for a gas turbine, in particular an aircraft gas turbine, comprising at least one radially outer shroud and a radially inner shroud extending along a respective arc and together form a ring portion, wherein in the radial direction between the outer shroud and the inner shroud more Guide vanes are arranged side by side in the circumferential direction, which are materially connected to the inner shroud and the outer shroud, in particular integrally connected, wherein the outer shroud comprises an axial front longitudinal wall member and an axially rear end wall element, such that the outer shroud and the two end walls in longitudinal section form a trough-like profile, wherein an associated reinforcing rib is formed on the outer shroud for each vane, which extends between the two end walls.

Richtungsangaben wie "Axial-" bzw. "axial", "Radial-" bzw. "radial" und "Umfangs-" sind grundsätzlich auf die Maschinenachse der Gasturbine bezogen zu verstehen, sofern sich aus dem Kontext nicht explizit oder implizit etwas anderes ergibt.Directional information such as "axial" or "axial", "radial" or "radial" and "circumferential" are basically based on the machine axis of the gas turbine to understand, unless the context explicitly or implicitly otherwise results.

Für die Sicherung in Umfangsrichtung derartiger Leitschaufelsegmente in einem zugehörigen Gehäuse ist es bekannt, stiftartige Elemente zu verwenden (sogenannte Pin-Sicherung) oder am Leitschaufelsegment ein hierfür ausgebildetes Sicherungselement anzulöten, wobei die Verwendung von derartigen zusätzlichen Bauteilen als Sicherungselemente zusätzliche Arbeitsschritte bei der Montage erfordert. EP2615243A1 , FR2928962A1 , DE10331599A1 , US2007/0183898A1 , WO2013/171407A1 offenbaren Leitschaufelsegmente, wie sie aus dem Stand der Technik bekannt sind.For securing in the circumferential direction of such vane segments in an associated housing, it is known to use pin-like elements or to solder on the vane segment a fuse element designed for this purpose, wherein the use of such additional components as securing elements requires additional steps during assembly. EP2615243A1 . FR2928962A1 . DE10331599A1 . US2007 / 0183898A1 . WO2013 / 171407A1 disclose vane segments as known in the art.

Aufgabe der Erfindung ist es, ein Leitschaufelsegment im Hinblick auf dessen Einbau und Sicherung in einem zugehörigen Gehäuse so zu verbessern, dass die obigen Nachteile überwunden werden können.The object of the invention is to improve a guide blade segment with regard to its installation and securing in an associated housing so that the above disadvantages can be overcome.

Zur Lösung wird vorgeschlagen, dass bei wenigstens einer Leitschaufel an der hinteren Stirnwand wenigstens zwei nebeneinander angeordnete Sicherungsrippen ausgebildet sind, wobei ein durch die beiden Sicherungsrippen in Umfangsrichtung begrenzter Zwischenraum von radial außen nach radial innen verjüngend ausgebildet ist.To solve it is proposed that at least one guide vane on the rear end wall at least two adjacently arranged securing ribs are formed, wherein a limited by the two securing ribs in the circumferential direction space is tapered from radially outside to radially inside.

Durch die vorgeschlagene Ausgestaltung des Leitschaufelelements mit den beiden Sicherungsrippen und dem zwischen ihnen ausgebildeten Zwischenraum kann auf die Pin-Sicherung bzw. gelötete Sicherungselemente verzichtet werden. Dies vereinfacht den Zusammenbau bzw. die Herstellung der Gasturbine.Due to the proposed embodiment of the vane element with the two securing ribs and the intermediate space formed between them can be dispensed with the pin fuse or soldered fuse elements. This simplifies the assembly or the manufacture of the gas turbine.

Es ist bevorzugt, dass die beiden Sicherungsrippen durch eine erste Sicherungsrippe und eine zweite Sicherungsrippe gebildet sind, wobei die erste Sicherungsrippe mit der Verstärkungsrippe der in Umfangsrichtung innen liegenden zugeordneten Leitschaufel verbunden ist.It is preferred that the two securing ribs are formed by a first securing rib and a second securing rib, wherein the first securing rib is connected to the reinforcing rib of the circumferentially inwardly associated associated guide vane.

Weiter wird vorgeschlagen, dass die zweite Sicherungsrippe nur in der hinteren Stirnwand ausgebildet ist.It is further proposed that the second securing rib is formed only in the rear end wall.

Die Ausgestaltung der beiden Sicherungsrippen stellt eine optimierte Anpassung der strukturellen Steifigkeit an der betreffenden Leitschaufel dar in Kombination mit der gewünschten Umfangssicherung durch die beiden Sicherungsrippen.The configuration of the two securing ribs represents an optimized adaptation of the structural rigidity to the relevant guide blade in combination with the desired circumferential securing by the two securing ribs.

Weiterbildend wird vorgeschlagen, dass die erste Sicherungsrippe und die zweite Sicherungsrippe bezogen auf eine entlang einer Umfangsrichtungstangente verlaufende Breitenrichtung voneinander verschiedene Rippenbreiten aufweisen, wobei die Umfangsrichtungstangente auf jeweils gleichem radialem Abstand vom Zentrum des Kreissegments liegt.In a further development, it is proposed that the first securing rib and the second securing rib have mutually different rib widths relative to a width direction running along a circumferential direction tangent, wherein the circumferential direction tangent lies at the same radial distance from the center of the circle segment.

Dabei ist es bevorzugt, dass die erste Sicherungsrippe oder/und die zweite Sicherungsrippe eine von radial außen nach radial innen zunehmende Breite aufweisen.It is preferred that the first securing rib and / or the second securing rib have a width that increases from radially outside to radially inside.

Weiter wird vorgeschlagen, dass die erste und die zweite Sicherungsrippe auf gleichem radialem Abstand vom Zentrum des Kreissegments in axialer Richtung gemessene voneinander unterschiedliche Rippenhöhen aufweisen.It is also proposed that the first and second securing ribs have mutually different rib heights measured at the same radial distance from the center of the circle segment in the axial direction.

Dabei kann die erste Sicherungsrippe auf gleichem radialem Abstand vom Zentrum des Kreissegments eine größere Rippenhöhe und eine größere Rippenbreite aufweisen als die zweite Sicherungsrippe.In this case, the first securing rib at the same radial distance from the center of the circle segment have a greater rib height and a larger rib width than the second securing rib.

Aus diesen einzelnen bevorzugten Merkmalen ergeben sich zwei in ihren Dimensionen und ihrer jeweiligen Form optimal angepasste Sicherungsrippen für die Umfangssicherung des Leitschaufelsegments. Die Formgebung kann insbesondere auch dahingehend optimiert sein, dass eine verbesserte Flächenpressung zwischen den Sicherungsrippen und einem anliegenden Gehäusebauteil, insbesondere einer die beiden Sicherungsrippen aufnehmende Gehäusenut, erreicht werden kann. Hierdurch kann für die in einer Gasturbine, insbesondere Fluggasturbine verwendeten Leitschaufelsegmente ein für jeden Betriebszustand der Gasturbine optimale Umfangssicherung ermöglicht werden.From these individual preferred features, there are two securing ribs optimally adapted in terms of their dimensions and their respective shape for the circumferential securing of the guide blade segment. The shaping can in particular also be optimized to that effect that an improved surface pressure between the securing ribs and an adjacent housing component, in particular a housing groove receiving the two securing ribs, can be achieved. As a result, it is possible for the guide blade segments used in a gas turbine, in particular an aircraft gas turbine, to be provided with an optimum circumferential securing for each operating state of the gas turbine.

Das Leitschaufelsegment umfasst vorzugsweise wenigstens drei, weiter bevorzugt vier bis sechs Leitschaufeln, wobei die beiden Sicherungsrippen bezogen auf die Umfangsrichtung einer innen liegenden Leitschaufel (16, 16a), vorzugsweise der zweiten oder der dritten oder der vierten Leitschaufel zugeordnet sind. Allerdings kann das Leitschaufelsegment auch eine andere Anzahl von Leitschaufeln aufweisen, insbesondere auch 7 oder mehr. Allgemeiner kann auch gesagt werden, dass die beiden Sicherungsrippen bezogen auf die Umfangsrichtung in einem mittleren Bereich der hinteren Stirnwand angeordnet sind bzw. einer Leitschaufel zugeordnet sind, die benachbart zur Mitte der Stirnwand liegt, oder bei einer ungeraden Anzahl von Leitschaufeln der mittleren Leitschaufel zugeordnet sind.The vane segment preferably comprises at least three, more preferably four to six vanes, wherein the two securing ribs are associated, relative to the circumferential direction, of an inner vane (16, 16a), preferably the second or the third or the fourth vane. However, the vane segment may also have a different number of vanes, in particular 7 or more. More generally, the two securing ribs are arranged in a central region of the rear end wall with respect to the circumferential direction or associated with a vane adjacent to the center of the end wall or associated with an odd number of vanes of the middle vane ,

Um die strukturelle Steifigkeit zu verbessern ist es bevorzugt, dass die beiden Sicherungsrippen einstückig mit der hinteren Stirnwand, insbesondere einstückig mit dem Leitschaufelsegment ausgebildet sind.In order to improve the structural rigidity, it is preferred that the two securing ribs are formed integrally with the rear end wall, in particular in one piece with the vane segment.

Die Erfindung betrifft auch eine Gasturbine, insbesondere Fluggasturbine mit wenigstens einem ringförmigen Leitschaufelmodul, das aus mehreren oben beschriebenen Leitschaufelsegmenten zusammengesetzt ist.The invention also relates to a gas turbine, in particular aircraft gas turbine with at least one annular vane module, which is composed of a plurality of vane segments described above.

Dabei kann das Leitschaufelmodul Teil einer Turbinenstufe sein, insbesondere einer Turbinenstufe einer Niederdruckturbine.In this case, the guide vane module may be part of a turbine stage, in particular a turbine stage of a low-pressure turbine.

Bei der Gasturbine ist es ferner bevorzugt, dass ein Gehäuseelement der Turbine, insbesondere der Niederdruckturbine derart ausgestaltet ist, dass es mit den Sicherungsrippen von wenigstens einem Leitschaufelsegment in formschlüssiger oder/und reibschlüssiger Verbindung steht, derart dass das Leitschaufelsegment im Betrieb der Gasturbine zumindest in Umfangsrichtung durch die Verbindung zwischen zwischen Gehäuse und Sicherungsrippen gehalten ist. Dabei ist es bevorzugt, dass die Verbindung zwischen Gehäuse und Sicherungsrippen durch eine die Sicherungsrippen aufnehmende Nut gebildet ist.In the gas turbine, it is further preferred that a housing element of the turbine, in particular the low-pressure turbine is designed such that it is in positive or / and frictional connection with the securing ribs of at least one vane segment, such that the vane segment during operation of the gas turbine, at least in the circumferential direction is held by the connection between the housing and securing ribs. It is preferred that the connection between the housing and securing ribs is formed by a groove receiving the securing ribs.

Die Erfindung wird nachfolgend unter Bezugnahme auf die anliegenden Figuren beispielhaft und nicht einschränkend beschrieben.

  • Fig. 1 zeigt in einer vereinfachten schematischen Perspektivdarstellung eine Ausführungsform eines Leitschaufelsegments.
  • Fig. 2 zeigt in einer schematischen vergrößerten Perspektivdarstellung Sicherungsrippen gemäß dem gestrichelt gekennzeichneten Bereich II der Figur 1.
The invention will be described below by way of example and not limitation with reference to the attached figures.
  • Fig. 1 shows in a simplified schematic perspective view of an embodiment of a vane segment.
  • Fig. 2 shows in a schematic enlarged perspective view securing ribs according to the dashed line area II of FIG. 1 ,

Ein in Figur 1 vereinfacht perspektivisch dargestelltes Leitschaufelelement 10 umfasst ein radial inneres Deckband 12 (unten in Figur 1), ein radial äußeres Deckband 14 (oben in Figur 1) und mehrere Leitschaufeln 16, die in radialer Richtung RR zwischen den beiden Deckbändern 12 und 14 angeordnet sind. In Umfangsrichtung sind mehrere Leitschaufeln 16 nebeneinander angeordnet. Die beiden Deckbänder 14, 16 bilden einen Ringabschnitt, wobei mehrere Leitschaufelsegmente, die zu einem Leitschaufelring (nicht dargestellt) zusammengesetzt sind, in radialer Richtung RR und in Umfangsrichtung UR einen Ringkanal begrenzen, durch den in axialer Richtung AR ein Fluid, insbesondere Heißgas strömen kann.An in FIG. 1 in simplified perspective illustrated vane element 10 comprises a radially inner shroud 12 (bottom in FIG. 1 ), a radially outer shroud 14 (at the top in FIG FIG. 1 ) and a plurality of guide vanes 16, which are arranged in the radial direction RR between the two shrouds 12 and 14. In the circumferential direction a plurality of guide vanes 16 are arranged side by side. The two shrouds 14, 16 form a ring portion, wherein a plurality of Leitschaufelsegmente, which are assembled to a Leitschaufelring (not shown) in the radial direction RR and in the circumferential direction UR define an annular channel through which a fluid, in particular hot gas can flow in the axial direction AR ,

Die Leitschaufeln 16 sind mit den beiden Deckbändern 12 und 14 vorzugsweise materialschlüssig verbunden, insbesondere einstückig ausgebildet. Ein Leitschaufelsegment 10 kann insbesondere durch Gießverfahren aus Metall hergestellt werden. Die Leitschaufeln 16 sind bevorzugt hohl ausgebildet. Am radial äußeren Deckband 14 sind Öffnungen 18 ersichtlich, die mit dem Hohlraum der einzelnen Leitschaufeln 16 in Verbindung stehen und die insbesondere dazu dienen, den Gießkern nach nach dem Gießen des Leitschaufelsegments 10 aus den einzelnen Leitschaufeln 16 wieder zu entfernen.The guide vanes 16 are preferably materially connected to the two shrouds 12 and 14, in particular integrally formed. A vane segment 10 can in particular be produced by casting from metal. The guide vanes 16 are preferably hollow. On the radially outer shroud 14 openings 18 can be seen, which are in communication with the cavity of the individual vanes 16 and which serve in particular to remove the casting core after the casting of the vane segment 10 from the individual vanes 16 again.

Bei dem radial äußeren Deckband 14 sind in axialer Richtung AR eine vordere Stirnwand 20 und eine hintere Stirnwand 22 vorgesehen, die vom Deckband 16 aus radial nach außen vorstehen, derart dass das Deckband 16 und die Stirnwände 20, 22 ein wannenartiges Profil in einem zur Axialrichtung AR parallelen Längsschnitt aufweisen. Die Stirnwände 20, 22 sind gegenüber der radialen Richtung geneigt, vorzugsweise unter einem Winkel von etwa 20° bis 45°.In the radially outer shroud 14, a front end wall 20 and a rear end wall 22 are provided in the axial direction AR, which protrude radially from the shroud 16 outwardly, such that the shroud 16 and the end walls 20, 22 a trough-like profile in a to the axial direction AR parallel longitudinal section have. The end walls 20, 22 are inclined relative to the radial direction, preferably at an angle of about 20 ° to 45 °.

Wie aus der Figur 1 ersichtlich, weisen die Leitschaufeln 16 ein Strömungs- bzw. Schaufelprofil auf mit einer aufgrund des Blickwinkels nicht sichtbaren konvexen Saugseite und einer konkaven Druckseite 24, wobei die Saugseite und die Druckseite 24 über eine Vorderkante 26 und eine Hinterkante 28 miteinander verbunden sind. Strömt Heißgas in im Wesentlichen axialer Richtung AR in den durch die Deckbänder 12, 14 und die Leitschaufeln 16 gebildeten Strömungskanälen 30 wirkt aufgrund der Strömungsprofile der Leitschaufeln 16 eine in der gezeigten Ausführungsform in Umfangsrichtung UR nach links (bzw. im Gegenuhrzeigersinn) wirkende Kraft auf das Leitschaufelsegment 10. Um die notwendige strukturelle Festigkeit zu gewährleisten, kann jeder Leitschaufel 16 im radial äußeren Deckband 14 eine Verstärkungsrippe 32 zugeordnet sein, um die wirkenden Kräfte am Deckband 14 bzw. den Stirnwänden 20, 22 abzustützen.Like from the FIG. 1 As can be seen, the guide vanes 16 have a flow or blade profile with a non-visible due to the viewing angle convex suction side and a concave pressure side 24, wherein the suction side and the pressure side 24 via a front edge 26 and a trailing edge 28 are interconnected. Hot gas flows in a substantially axial direction AR in the flow channels 30 formed by the shrouds 12, 14 and the guide vanes 16 due to the flow profiles of the vanes 16 acts in the embodiment shown in the circumferential direction UR to the left (or counterclockwise) force acting on the Guide vane segment 10. In order to ensure the necessary structural strength, each guide vane 16 in the radially outer shroud 14 may be assigned a reinforcing rib 32 in order to support the forces acting on the shroud 14 and the end walls 20, 22.

Die beim Durchströmen von Heißgas in Umfangsrichtung UR wirkenden Kräfte werden ferner durch wenigstens zwei Sicherungsrippen 34, 36 an einem das Leitschaufelsegment 10 aufnehmenden Gehäuse (nicht dargestellt) abgestützt, so dass das Leitschaufelsegment 10 bzw. ein aus mehreren Leitschaufelsegmenten gebildeter Leitschaufelring einer Turbinenstufe einer Gastrubine in Umfangsrichtung gesichert ist.The forces acting on hot gas in the circumferential direction UR forces are further supported by at least two securing ribs 34, 36 on a housing (not shown) receiving the guide vane segment 10 so that the vane segment 10 or a Leitschaufelsegmenten formed of a turbine stage of a Gastrubine in Circumference is secured.

Die Ausgestaltung und Anordnung einer ersten Sicherungsrippe 34 und einer zweiten Sicherungsrippe 36 wird nachfolgend anhand der vergrößerten Darstellung der Figur 2 erläutert, die dem gestrichelt umrandeten Bereich II der Fig. 1 entspricht.The configuration and arrangement of a first locking rib 34 and a second locking rib 36 will be described below with reference to the enlarged view of FIG. 2 explained, the dashed bordered area II of Fig. 1 equivalent.

Die erste Sicherungsrippe 34 erstreckt sich in radialer Richtung RR von einem oberen Rand 38 der Stirnwand 22 nach unten bzw. radial innen. In ihrem oberen Bereich weist sie ausgehend vom oberen Rand 38 einen Übergangsbereich 35 auf, der bevorzugt geneigt oder stufenartig ausgebildet ist. In ihrem unteren Bereich geht sie bei 39 (Übergangsbereich) direkt in die der Leitschaufel 16a (Fig. 1) zugeordnete Verstärkungsrippe 32a über. Die erste Sicherungsrippe 34 weist eine in Umfangsrichtung UR bzw. entlang einer Umfangrichtungstangente verlaufende Breite auf, wobei die Breite von radial außen nach radial innen zunimmt. In axialer Richtung steht die erste Sicherungsrippe 34 von der Stirnwand 22 ab und weist eine in axialer Richtung verlaufende zugehörige Höhe auf.The first securing rib 34 extends in the radial direction RR from an upper edge 38 of the end wall 22 downwardly or radially inwardly. In its upper region, starting from the upper edge 38, it has a transition region 35, which is preferably inclined or step-like. In its lower region, it goes directly into the vane 16a (transition region) 39 (FIG. Fig. 1 ) associated with reinforcing rib 32a. The first securing rib 34 has a width extending in the circumferential direction UR or along a circumferential direction tangent, the width increasing from radially outward to radially inward. In the axial direction, the first securing rib 34 projects from the end wall 22 and has an associated height which extends in the axial direction.

Die zweite Sicherungsrippe 36 erstreckt sich ebenfalls in radialer Richtung RR von dem oberen Rand 38 der Stirnwand 22 nach unten bzw. radial innen. In ihrem oberen Bereich weist sie ausgehend vom oberen Rand 38 einen Übergangsbereich 37 auf, der bevorzugt geneigt oder stufenartig ausgebildet ist. Allerdings endet die zweite Sicherungsrippe in radialer Richtung RR in einem Abschlussbereich 41 zwischen Stirnwand 22 und Deckband 14, das in dieser Darstellung nur noch angedeutet ist. Die zweite Sicherungsrippe 36 ist also vorzugsweise nur an der Stirnwand 22 vorgesehen und weist keine rippenartige Fortsetzung oder Verbindung zu einer anderen Verstärkungsrippe einer Leitschaufel auf. Auch die zweite Sicherungsrippe 36 weist eine in Umfangsrichtung UR bzw. entlang einer Umfangrichtungstangente verlaufende Breite auf, wobei die Breite von radial außen nach radial innen zunimmt. In axialer Richtung steht die zweite Sicherungsrippe 36 von der Stirnwand 22 ab und weist eine in axialer Richtung verlaufende zugehörige Höhe auf.The second securing rib 36 also extends in the radial direction RR from the upper edge 38 of the end wall 22 downwards or radially inward. In its upper region, starting from the upper edge 38, it has a transition region 37, which is preferably inclined or step-like. However, the second securing rib ends in the radial direction RR in a closing region 41 between end wall 22 and shroud 14, which is in this Presentation is only hinted at. The second securing rib 36 is thus preferably provided only on the end wall 22 and has no rib-like continuation or connection to another reinforcing rib of a guide vane. The second securing rib 36 also has a width extending in the circumferential direction UR or along a circumferential direction tangent, the width increasing from radially outward to radially inward. In the axial direction, the second securing rib 36 projects from the end wall 22 and has an associated height extending in the axial direction.

Die erste Sicherungsrippe 34 und die zweite Sicherungsrippe 36 sind voneinander in einem Abstand RA angeordnet, der einer Breite eines zwischen den beiden Sicherungsrippen 34, 36 gebildeten Zwischenraumes 40 entspricht. Die Breite RA des Zwischenraumes 40 nimmt von radial außen nach radial innen ab. Der Zwischenraum 40 ist also von radial außen nach radial innen verjüngend bzw. sich verengend ausgebildet. Diese Verjüngung des Zwischenraumes 40 wird dadurch gebildet, dass eine dem Zwischenraum 40 zugewandte erste Innenwand 42 der ersten Sicherungsrippe 34 und eine dem Zwischenraum 40 zugewandte zweite Innenwand 44 der zweiten Sicherungsrippe 36 geneigt zueinander verlaufen. Dabei sind beiden Innenwände 42, 44 zumindest bezogen auf eine durch die Radialrichtung RR und die Axialrichtung aufgespannte Ebene geneigt, die in der vorliegenden Darstellung im Wesentlichen orthogonal zur Zeichnungsebene verläuft.The first securing rib 34 and the second securing rib 36 are arranged at a distance RA from one another, which corresponds to a width of an intermediate space 40 formed between the two securing ribs 34, 36. The width RA of the intermediate space 40 decreases from radially outside to radially inside. The gap 40 is thus tapered from radially outward to radially inward or narrowing. This tapering of the intermediate space 40 is formed by a first inner wall 42 of the first securing rib 34 facing the intermediate space 40 and a second inner wall 44 of the second securing rib 36 facing the intermediate space 40 being inclined relative to one another. In this case, both inner walls 42, 44 are inclined, at least in relation to a plane spanned by the radial direction RR and the axial direction, which in the present representation runs essentially orthogonal to the plane of the drawing.

Jede Sicherungsrippe 34, 36 weist eine vom Zwischenraum 40 abgewandte Außenwand 46 bzw. 48 auf, wobei die Außenwand 46 der ersten Sicherungsrippe 34 zugeordnet ist und die Außenwand 48 der zweiten Sicherungsrippe zugeordnet ist. In einem zusammengebauten Zustand einer Gasturbine sind die beiden Sicherungsrippen 34, 36 in einer an einem Gehäuse ausgebildeten gemeinsamen Nut aufgenommen, derart dass die beiden Außenwände 46, 48 mit korrespondierenden Innenseiten der nicht dargestellten Gehäusenut in Kontakt kommen können bzw. stehen können. Diese flächige Anlage der Außenwände 46, 48 an den Innenseiten der Gehäusenut ermöglicht eine Abstützung des Leitschaufelsegments in Umfangsrichtung an dem Gehäuse. Die Außenwände 46, 48 der ersten Sicherungsrippe 34 und der zweiten Sicherungsrippe 36 erstrecken sich vorzugsweise im Wesentlichen parallel oder von radial innen nach radial außen leicht konvergent zueinander. Werden die Außenwände 46, 48 in dieser Art ausgebildet, kann das Leitschaufelelement 10 in radialer Richtung leichtgängig und einfach in die die Sicherungsrippen 34, 36 aufnehmende Nut des Gehäuses eingeführt werden. Die Nut des Gehäuses kann besonderes einfach hergestellt werden, wenn die die Nut in Umfangsrichtung begrenzenden Wandungen ebenfalls im Wesentlichen parallel oder von radial innen nach radial außen leicht konvergent zueinander verlaufen.Each securing rib 34, 36 has an outer wall 46 or 48 facing away from the intermediate space 40, wherein the outer wall 46 is assigned to the first securing rib 34 and the outer wall 48 is assigned to the second securing rib. In an assembled state of a gas turbine, the two securing ribs 34, 36 are received in a common groove formed on a housing, such that the two outer walls 46, 48 can come into contact with corresponding inner sides of the housing groove, not shown. This planar contact of the outer walls 46, 48 on the insides of the housing groove allows a support of the stator blade segment in the circumferential direction of the housing. The outer walls 46, 48 of the first securing rib 34 and the second securing rib 36 preferably extend substantially parallel or slightly convergent from one another radially inward to radially outward. If the outer walls 46, 48 formed in this manner, the vane member 10 in the radial direction easily and easily be inserted into the securing ribs 34, 36 receiving groove of the housing. The groove of the housing can be made particularly easy if the groove in the circumferential direction bounding walls also substantially parallel or from radially inward to radially outwardly slightly convergent to each other.

Die Breite der ersten Sicherungsrippe 34 ist zwischen dem radial äußeren Übergangsbereich 35 und dem radial inneren Übergangsbereich 39 auf der gesamten radialen Länge größer als die Breite der zweiten Sicherungsrippe 36 zwischen deren radial äußerem Übergangsbereich 37 und deren Abschlussbereich 41. Zusätzlich ist die Höhe, d. h. die Erstreckung in axialer Richtung, der ersten Sicherungsrippe 34 zwischen dem Übergangsbereich 35 und dem Übergangsbereich 39 größer als die Höhe der zweiten Sicherungsrippe 36 zwischen deren Übergangsbereich 37 und deren Abschlussbereich 41. Anders ausgedrückt ist bei gleichem radialen Abstand vom Zentrum die Querschnittsfläche der ersten Sicherungsrippe 34 größer als die Querschnittsfläche der zweiten Sicherungsrippe 36. Dies gilt für die hier dargestellte Ausführungsform für die gesamte radiale Länge der ersten und der zweiten Sicherungsrippe 34, 36. Entsprechend ist die Außenfläche 46 der ersten Sicherungsrippe 34 größer als die Außenfläche der 48 der zweiten Sicherungsrippe 36.The width of the first securing rib 34 is greater between the radially outer transition region 35 and the radially inner transition region 39 over the entire radial length than the width of the second securing rib 36 between its radially outer transition region 37 and its termination region 41. In addition, the height, d. H. the extent in the axial direction, the first securing rib 34 between the transition region 35 and the transition region 39 is greater than the height of the second securing rib 36 between the transition region 37 and the termination region 41. In other words, with the same radial distance from the center, the cross-sectional area of the first securing rib 34th This is true for the embodiment shown here for the entire radial length of the first and second securing ribs 34, 36. Accordingly, the outer surface 46 of the first securing rib 34 is larger than the outer surface 48 of the second securing rib 36 ,

Die Dimensionierung der beiden Sicherungsrippen erfolgt unter Berücksichtigung der Anordnung der Leitschaufeln 16 und deren Schaufelprofil sowie den damit verbundenen Krafteinwirkungen in Umfangsrichtung auf das Leitschaufelsegment 10. Wie bereits oben beschrieben, wirken in der vorliegenden Ausführungsform beim Durchströmen von Heißgas durch das Leitschaufelsegment 10 bzw. durch einen geschlossenen Leitschaufelring größere Druckkräfte in Umfangsrichtung nach links (Gegenuhrzeigersinn), so dass im Betrieb größere Kräfte in Umfangsrichtung mittels der ersten Sicherungsrippe 34 abgestützt werden müssen. Insbesondere die größere Außenfläche 46 der ersten Sicherungsrippe 34 ermöglicht eine ausreichende Flächenpressung und Abstützung des Leitschaufelsegments 10 am Gehäuse bzw. der im Gehäuse vorgesehenen Nut.The dimensioning of the two securing ribs takes place in consideration of the arrangement of the guide vanes 16 and their blade profile and the associated force effects in the circumferential direction on the vane segment 10. As already described above, act in the present embodiment, when flowing through hot gas through the vane segment 10 and by a closed Leitschaufelring larger compressive forces in the circumferential direction to the left (counterclockwise), so that larger forces in the circumferential direction by means of the first securing rib 34 must be supported during operation. In particular, the larger outer surface 46 of the first securing rib 34 allows sufficient surface pressure and support of the guide vane segment 10 on the housing or the groove provided in the housing.

Die von radial außen nach radial innen abnehmende Breite RA des Zwischenraums 40 wird durch die zunehmende Breite der ersten und der zweiten Sicherungsrippe 34, 36 bewirkt. Die beiden Sicherungsrippen 34, 36 weisen somit ihre größte Breite radial innen, bezogen auf die radiale Länge der beiden Sicherungsrippen 34, 36 unterhalb (nach radial innen) ihrer jeweiligen Mitte auf. Hierdurch können insbesondere im Übergangsbereich zwischen der Verstärkungsrippe 32a der Leitschaufel 16a wirkende Kräfte, die größer sind, als diejenigen, die radial außen noch wirken, optimal über das Deckband 14, die Stirnwand 22 und die Sicherungsrippen 34, 36 abgestützt werden.The radially inwardly to radially inwardly decreasing width RA of the gap 40 is effected by the increasing width of the first and second securing ribs 34, 36. The two securing ribs 34, 36 thus have their greatest width radially inward, based on the radial length of the two securing ribs 34, 36 below (radially inward) of their respective center. In this way, in particular in the transition region between the reinforcing rib 32a of the guide vane 16a acting forces that are greater than those that still act radially outward, optimally over the shroud 14, the end wall 22 and the securing ribs 34, 36 are supported.

Die hier dargestellte Ausführungsform ist rein exemplarisch. Die erste und die zweite Sicherungsrippe 34, 36 könnten auch vertauscht sein, beispielsweise wenn die Leitschaufeln 16 mit ihrem Schaufelprofil anders ausgestaltet wären, insbesondere die Druckseite und die Saugseite vertauscht wären, so dass in Umfangsrichtung größere Druckkräfte nach rechts (Uhrzeigersinn) wirken würden. Die Dimensionierung der beiden Sicherungsrippen kann an unterschiedliche Gasturbinen bzw. unterschiedliche Gehäuse angepasst werden. Dabei können unterschiedliche Formen und Dimensionen der beiden Sicherungsrippen 34, 36 bereits bei der Herstellung eines Leitschaufelsegments 10 berücksichtigt werden, so dass ein fertig hergestelltes, insbesondere gegossen Leitschaufelelement 10, bereits die beiden Sicherungsrippen 34, 36 aufweist, die einstückig mit dem Leitschaufelsegment ausgebildet sind. Insgesamt kann durch die Wahl und Dimensionierung der beiden Sicherungsrippen eine optimierte Einstellung der Flächenpressung zwischen den Sicherungsrippen und der Gehäusenut erreicht werden. Ferner ergibt sich eine Kostenersparnis bei der Gehäusefertigung durch die Wahl eines optimierten Abstandes zwischen den beiden Sicherungsrippen, durch den Wegfall von zusätzlichen Bearbeitungsschritten, wie etwa Auftrag von Lotmaterial oder Einsetzen von Sicherungsstiften und dergleichen. Die beiden Sicherungsrippen 34, 36 ermöglichen also insgesamt eine flexible Anpassung an notwendige strukturelle Gegebenheiten eines Gasturbinentyps, bei dem die Leitschaufelsegmente zum Einsatz kommen sollen.The embodiment shown here is purely exemplary. The first and the second securing ribs 34, 36 could also be interchanged, for example, if the guide vanes 16 were configured differently with their blade profile, in particular the pressure side and the suction side would be reversed, so that larger compressive forces would act in the circumferential direction to the right (clockwise). The dimensioning of the two securing ribs can be adapted to different gas turbines or different housing. Different shapes and dimensions of the two securing ribs 34, 36 can already be taken into account during the production of a guide blade segment 10, so that a finished, in particular cast guide blade element 10 already has the two securing ribs 34, 36, which are formed integrally with the guide blade segment. Overall, an optimized setting of the surface pressure between the securing ribs and the housing groove can be achieved by the choice and dimensioning of the two securing ribs. Furthermore, there is a cost savings in the housing production by choosing an optimized distance between the two securing ribs, by the elimination of additional processing steps, such as application of solder material or insertion of locking pins and the like. The two securing ribs 34, 36 thus allow a total of flexible adaptation to the necessary structural conditions of a gas turbine type, in which the guide blade segments are to be used.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

1010
LeitschaufelelementGuide vane
1212
radial inneres Deckbandradially inner shroud
1414
radial äußeres Deckbandradially outer shroud
16/16a16/16
Leitschaufelvane
1818
Öffnungopening
2020
vordere Stirnwandfront end wall
2222
hintere Stirnwandrear end wall
2424
Druckseitepressure side
2626
Vorderkanteleading edge
2828
Hinterkantetrailing edge
3030
Strömungskanäleflow channels
32/32a32 / 32a
Verstärkungsrippereinforcing rib
3434
erste Sicherungsrippefirst securing rib
3535
ÜbergangsbereichTransition area
3636
zweite Sicherungsrippesecond securing rib
3737
ÜbergangsbereichTransition area
3838
oberer Randupper edge
3939
ÜbergangsbereichTransition area
4040
Zwischenraumgap
4141
Abschlussbereichtermination region
4242
erste Innenwand der ersten Sicherungsrippefirst inner wall of the first securing rib
4444
zweite Innenwand der zweiten Sicherungsrippesecond inner wall of the second securing rib
4646
Außenwand der ersten SicherungsrippeOuter wall of the first securing rib
4848
Außenwand der zweiten SicherungsrippeOuter wall of the second securing rib
ARAR
axiale Richtungaxial direction
RARA
Breite des Zwischenraums 40Width of the gap 40
RRRR
radiale Richtungradial direction
URUR
Umfangsrichtungcircumferentially

Claims (12)

  1. Guide vane segment (10) for a gas turbine, in particular an aircraft gas turbine, comprising at least one radially outer shroud (14) and one radially inner shroud (12) which extend in each case along a circular arc and together form a ring portion, a plurality of guide vanes (16, 16a) being arranged adjacent to one another in the circumferential direction (UR) between the outer shroud (14) and the inner shroud (12) in the radial direction (RR), and being integrally joined to the inner shroud (12) and the outer shroud (14), in particular joined in one piece, the outer shroud (14) comprising, in an axial longitudinal direction (AR), an axially front end wall element (20) and an axially rear end wall element (22) such that the outer shroud (14) and the two end walls (20, 22) form a trough-like profile in the longitudinal section, an associated reinforcing rib (32, 32a) being formed on the outer shroud (14) for each guide vane (16, 16a), which rib extends between the two end walls (20, 22), at least two securing ribs (34, 36) arranged adjacent to one another being formed at the rear end wall (22) in the case of at least one guide vane (16a), a gap (40) being delimited by the two securing ribs (34, 36) in the circumferential direction (UR), characterized in that a width (RA) of the gap (40) decreases radially from the outside to the inside such that the gap (40) tapers radially from the outside to the inside.
  2. Guide vane segment according to claim 1, characterized in that the two securing ribs (34, 36) are formed by a first securing rib (34) and a second securing rib (36), the first securing rib (34) being connected to a reinforcing rib (32a) which is associated with a guide vane (16a) that is positioned on the inside in the circumferential direction (UR).
  3. Guide vane segment according to claim 2, characterized in that the second securing rib (36) is formed only in the rear end wall (22).
  4. Guide vane segment according to either claim 2 or claim 3, characterized in that the first securing rib (34) and the second securing rib (36) have rib widths that differ from one another based on a width direction that extends along a circumferential direction tangent, the circumferential direction tangent being positioned in each case at the same radial spacing from the center of the circular segment.
  5. Guide vane segment according to claim 4, characterized in that the first securing rib (34) and/or the second securing rib (36) have a width that increases radially from the outside to the inside.
  6. Guide vane segment according to any of claims 2 to 5, characterized in that the first and the second securing rib (34, 36) have rib heights that differ from one another when measured in the axial direction (AR) at the same radial spacing from the center of the circular segment.
  7. Guide vane segment according to claim 6, characterized in that the first securing rib (34), at the same radial spacing from the center of the circular segment, has a greater rib height and a greater rib width than the second securing rib (36).
  8. Guide vane segment according to any of the preceding claims, characterized in that it comprises at least three, preferably four to six guide vanes (16, 16a), the two securing ribs (34, 36) preferably being associated with the second or the third or the fourth guide vane (16a) based on the circumferential direction (UR) of a guide vane (16, 16a) positioned on the inside.
  9. Guide vane segment according to any of the preceding claims, characterized in that the two securing ribs (34, 36) are integral with the rear end wall (22), in particular integral with the guide vane segment (10).
  10. Gas turbine, in particular an aircraft gas turbine, comprising at least one annular guide vane module assembled from a plurality of guide vane segments (10) according to any of the preceding claims.
  11. Gas turbine according to claim 10, characterized in that the guide vane module is part of a turbine stage, in particular of a turbine stage of a low-pressure turbine.
  12. Gas turbine according to either claim 10 or claim 11, characterized in that a housing element of the turbine, in particular of the low-pressure turbine, is designed in such a way that it is interlockingly and/or frictionally connected to the securing ribs (34, 36) of at least one guide vane segment (10) in such a way that the guide vane segment (10) during operation is supported at least in the circumferential direction by the connection between a housing and the securing ribs (34, 36), the connection between the housing and the securing ribs (34, 36) preferably being formed by a groove that accommodates the securing ribs (34, 36).
EP16195409.4A 2015-11-19 2016-10-25 Blade cluster with circumferential retention device Active EP3170986B1 (en)

Applications Claiming Priority (1)

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DE102015222834.7A DE102015222834A1 (en) 2015-11-19 2015-11-19 Bucket cluster with circumference protection

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EP3170986B1 true EP3170986B1 (en) 2018-12-12

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DE (1) DE102015222834A1 (en)
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KR101901683B1 (en) * 2017-02-06 2018-09-27 두산중공업 주식회사 Gas Turbine Ring Segment Having Straight Type Cooling Hole, And Gas Turbine Having The Same
US11536147B2 (en) 2021-03-30 2022-12-27 Raytheon Technologies Corporation Vane arc segment with flange and gusset

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3403889A (en) * 1966-04-07 1968-10-01 Gen Electric Frame assembly having low thermal stresses
EP1112440B1 (en) * 1998-08-31 2003-06-18 Siemens Aktiengesellschaft Turbine guide blade
DE10331599A1 (en) * 2003-07-11 2005-02-03 Mtu Aero Engines Gmbh Component for a gas turbine and method for producing the same
CA2633337C (en) * 2005-12-29 2014-11-18 Rolls-Royce Power Engineering Plc Airfoil for a second stage nozzle guide vane
FR2928962B1 (en) * 2008-03-19 2013-10-18 Snecma TURBINE DISPENSER WITH HOLLOW BLADES.
FR2941488B1 (en) * 2009-01-28 2011-09-16 Snecma TURBINE RING WITH ANTI-ROTATION INSERT
US8360716B2 (en) 2010-03-23 2013-01-29 United Technologies Corporation Nozzle segment with reduced weight flange
PL2615243T3 (en) * 2012-01-11 2017-12-29 MTU Aero Engines AG Blade ring segment for a fluid flow engine and method for producing the same
FR2990719B1 (en) * 2012-05-16 2016-07-22 Snecma TURBOMACHINE DISPENSER AND METHOD OF MANUFACTURE
EP2787178B1 (en) 2013-04-03 2016-03-02 MTU Aero Engines AG Guide vane assembly
US9797262B2 (en) 2013-07-26 2017-10-24 United Technologies Corporation Split damped outer shroud for gas turbine engine stator arrays

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

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US10428668B2 (en) 2019-10-01
DE102015222834A1 (en) 2017-05-24
ES2704288T3 (en) 2019-03-15
US20170145842A1 (en) 2017-05-25
EP3170986A1 (en) 2017-05-24

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