EP0899426B1 - Aube de guidage pour turbines à gaz - Google Patents

Aube de guidage pour turbines à gaz 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
Authority
EP
European Patent Office
Prior art keywords
guide vane
guide
platform
face
projection
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP98114445A
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German (de)
English (en)
Other versions
EP0899426A2 (fr
EP0899426A3 (fr
Inventor
Rudolf Stanka
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP0899426A2 publication Critical patent/EP0899426A2/fr
Publication of EP0899426A3 publication Critical patent/EP0899426A3/fr
Application granted granted Critical
Publication of EP0899426B1 publication Critical patent/EP0899426B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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

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.

Landscapes

  • 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)

Claims (18)

  1. Aube directrice (1) pour une turbine à gaz, en particulier une turbine à basse pression, comprenant une pale (2) qui s'étend entre une plate-forme intérieure (5) et une plate-forme extérieure (3), où la plate-forme extérieurs (3) comprend des moyens de fixation (11) pour la fixation sur un carter, des surfaces frontales (7) pointant dans une direction périphérique et des surfaces frontales (13) pointent dans la direction périphérique opposée, ces surfaces frontales étant disposées sur les deux plates-formes (3, 5), des parties saillantes (8) sur les surfaces frontales (7) et des logements (12) sur les autres surfaces frontales (13) pour un assemblage à liaison par sûreté de forme au moins dans le sens axial avec des aubes directrices voisines, par des parties saillantes et des logements appropriés,
    caractérisée en ce que la plate-forme extérieure (3) et la plate-forme intérieure (5) sont réalisées comme des structures creuses résistant aux torsions et aux flexions, où la plate-forme extérieure (3) comprend une plate-forme (3'), une paroi de raidissement (4), deux traverses (10) s'étendant en étant espacées l'une de l'autre et une surface frontale fermée (7), et où la plate-forme intérieure (5) comprend une plate-forme (5'), une paroi de renfort (6) et une surface frontale fermée (7), en ce que les parties saillantes (8) sont des éléments intégrés des surfaces frontales fermées (7) et comprennent des surfaces latérales étroites (9) formant leur contour périphérique, et en ce que les surfaces frontales ouvertes (13) des plates-formes (3, 5) forment, avec leurs surfaces intérieures (14), directement les logements (12) pour les parties saillantes d'une aube directrice voisine.
  2. Aube directrice selon la revendication 1, caractérisée en ce que la surface latérale (9) de chaque partie saillante (8) s'étend à angle droit par rapport à la première surface frontale (7) .
  3. Aube directrice selon la revendication 1 ou 2,
    caractérisée en ce que la surface latérale (9) de chaque partie saillante (6) dépasse ou moins de 3 mm par rapport à la première surface frontale (7).
  4. Aube directrice selon la revendication 1 ou 2,
    caractérisée en ce que la surface latérale (9) de chaque partie saillante (8) dépasse au moins de 5 mm par rapport à la première surface frontale (7).
  5. Aube directrice selon l'une quelconque des revendications précédentes, caractérisée en ce que chaque partie saillante (8) ou chaque logement (12) constitue, sur la plate-forma respective (3, 5), au moins 30 % de la surface de section de la première ou de la seconde surface frontale (7 ou 13).
  6. Aube directrice selon l'une quelconque des revendications 1 à 4, caractérisée en ce que chaque partie saillante (8) constitue, sur la plate-forme respective (3, 5), au moins 50 % de la surface de section de la première surface frontale (7).
  7. Aube directrice selon l'une quelconque des revendications précédentes, caractérisés en ce que chaque partie saillante (8) est placée dans le logement (12) en ayant du jeu.
  8. Aube directrice selon l'une quelconque des revendications précédentes, caractérisée en ce que la surface intérieure (14) de chaque logement (12), adjacente à la seconde surface frontale (13), s'étend, une fois montée, parallèlement à la surface latérale (9) de la partie saillante (8).
  9. Aube directrice selon l'une quelconque des revendications précédentes, caractérisée en ce que la paroi de raidissement (4) s'étend pratiquement de façon parallèle à la plate-forme (3').
  10. Aube directrice selon la revendication 9, caractérisée en ce que les traverses (10) s'étendent sur toute la largeur (B) de la plate-forme (3').
  11. Aube directrice selon la revendication 9 ou 10,
    caractérisée en ce que les épaisseurs de paroi des plates-formes (3', 5'), de la paroi de raidissement (4), de la paroi de renfort (6) et des traverses (10) sont respectivement constantes.
  12. Aube directrice selon l'une quelconque des revendications 9 à 11, caractérisée en ce que les épaisseurs de paroi des plates-formes (3', 5'), de la paroi de raidissement (4), de la paroi de renfort (6) et des traverses (10) sont respectivement presque identiques.
  13. Aube directrice selon l'une quelconque des revendications précédentes, caractérisée par une configuration réalisée avec une seule pièce.
  14. Aube directrice selon l'une quelconque des revendications précédentes, caractérisée en ce que l'aube directrice (1) se compose de matière plastique renforcée par des fibres.
  15. Aube directrice selon l'une quelconque des revendications 1 à 13, caractérisée en ce que l'aube directrice (1) est en métal.
  16. Segment d'aube directrice d'au moins trois aubes directrices selon l'une quelconque des revendications précédentes, caractérisé en ce que, à chaque fois, deux parties saillantes (8) à liaison par sûreté de forme sont logées dans deux logements (12) d'une aube directrice voisine (1), et des aubes directrices voisines (1) sont collées ensemble au moins sur la surface latérale (9) de chaque partie saillante (8).
  17. Segment d'aube directrice selon la revendication 16,
    caractérisé en ce qu'au moins une aube directrice (1) comprend, dans le sens radial, un perçage (16) pratiqué dans la paroi de raidissement (4), perçage dans lequel pénètre un boulon placé côté carter.
  18. Assemblage de couronne directrice à partir de segments d'aube directrice selon la revendication 16 ou 17, caractérisé en ce que, à chaque fois, deux parties saillantes (8) à liaison par sûreté de forme sont logées dans deux logements (12) d'une aube directrice (1) d'un segment voisin (15) d'aube directrice.
EP98114445A 1997-08-23 1998-08-01 Aube de guidage pour turbines à gaz Expired - Lifetime EP0899426B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE29715180U 1997-08-23
DE29715180U DE29715180U1 (de) 1997-08-23 1997-08-23 Leitschaufel für eine Gasturbine

Publications (3)

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

Family

ID=8045040

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98114445A Expired - Lifetime EP0899426B1 (fr) 1997-08-23 1998-08-01 Aube de guidage pour turbines à gaz

Country Status (4)

Country Link
US (1) US6217282B1 (fr)
EP (1) EP0899426B1 (fr)
JP (1) JPH11107704A (fr)
DE (2) DE29715180U1 (fr)

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CN103422903A (zh) * 2012-05-21 2013-12-04 阿尔斯通技术有限公司 涡轮隔板构造
EP4603677A1 (fr) * 2024-02-16 2025-08-20 MTU Aero Engines AG Segment d'aube directrice

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JP6763157B2 (ja) * 2016-03-11 2020-09-30 株式会社Ihi タービンノズル
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US11274569B2 (en) 2017-12-13 2022-03-15 Pratt & Whitney Canada Corp. Turbine shroud cooling
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US10738634B2 (en) * 2018-07-19 2020-08-11 Raytheon Technologies Corporation Contact coupled singlets
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Publication number Priority date Publication date Assignee Title
CN103422903A (zh) * 2012-05-21 2013-12-04 阿尔斯通技术有限公司 涡轮隔板构造
CN103422903B (zh) * 2012-05-21 2015-11-25 阿尔斯通技术有限公司 涡轮隔板构造
EP4603677A1 (fr) * 2024-02-16 2025-08-20 MTU Aero Engines AG Segment d'aube directrice

Also Published As

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

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