EP1081336B1 - Anneau de guidage composé pour turbines à gaz - Google Patents

Anneau de guidage composé pour turbines à gaz Download PDF

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Publication number
EP1081336B1
EP1081336B1 EP00115821A EP00115821A EP1081336B1 EP 1081336 B1 EP1081336 B1 EP 1081336B1 EP 00115821 A EP00115821 A EP 00115821A EP 00115821 A EP00115821 A EP 00115821A EP 1081336 B1 EP1081336 B1 EP 1081336B1
Authority
EP
European Patent Office
Prior art keywords
blade
platform
airfoil
shroud
area
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
EP00115821A
Other languages
German (de)
English (en)
Other versions
EP1081336A2 (fr
EP1081336A3 (fr
Inventor
Richard Scharl
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
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Filing date
Publication date
Application filed by MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1081336A2 publication Critical patent/EP1081336A2/fr
Publication of EP1081336A3 publication Critical patent/EP1081336A3/fr
Application granted granted Critical
Publication of EP1081336B1 publication Critical patent/EP1081336B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00Stators
    • F01D9/02Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F01D9/044Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like

Definitions

  • the invention relates to a built Leitkranz for a gas turbine, comprising a Shroud having a peripheral surface and at least one airfoil having a surface, wherein the shroud has at least one opening for attachment of the Having airfoil, and wherein the airfoil on at least one end portion an at least partially protruding over the surface, a Transition curve having platform used in the breakthrough is.
  • Built-Leitkränze are integral components, which is generally an annular outer shroud, comprise a plurality of airfoils and possibly an annular inner shroud. Such Leitkränze can also be constructed in segments and be e.g. used in compressors of aircraft engines.
  • the shroud extends in generally around the longitudinal axis of the gas turbine.
  • the blades are in essentially arranged in the radial direction.
  • the airfoil has at least one End portion with a constant profile or a constant cross-sectional area on, which are used during assembly in a formed in the shroud breakthrough and by e.g. Soldering or welding is attached.
  • the airfoil can too at a opposite, second end portion a constant profile or a have a constant cross-section and in a second shroud, i. one - Outside and inside cover tape to be used.
  • the disadvantage here is that the profile of Although the blade does not have to be constant over the entire channel height, however is limited in terms of its profile geometry for assembly reasons.
  • the Airfoil may be e.g. no strong bend or significant thickening in his have between the end portions lying area.
  • From DE 12 00 070 B is a manufacturing method for a vane ring in which the blades are formed in grooves formed in a ring body with their Blade be used with the blade with a curvature in the Shovel goes over and the ring body finally separated into several segments becomes.
  • the airfoil has a platform at at least one end on, in the area of the entry and exit edge only slightly above the surface protrudes.
  • the platform In the middle area of the airfoil on the pressure side is the platform further ahead than at the entry and exit edges.
  • On the suction side is the supernatant the platform in the area of the largest profile thickness practically "zero". Upstream and downstream of the largest profile thickness, the supernatant initially increases and then back to the entrance or exit edge.
  • EP 0 704 602 A2 discloses turbine blades arranged on a support the blade surface in a radius in the peripheral surface of the carrier passes.
  • EP 0 199 073 A1 discloses a manufacturing method for a guide blade known, which is fixed by soldering to a stator, wherein the guide vane an excessively deflected profile bar is produced, and this to the Enlargement of the soldering surface at least one end in the cold state of a foot-like Thickening thickened and in the area of a soldering surface is formed.
  • the profile bar can be upset on one side become.
  • the object of the present invention is a built Leitkranz the to create the genus described above, the axial length saves, fixed keitstechnisch is low, can be relatively easily finished and no or little Limitations on the profile geometry of the airfoil, e.g. for assembly reasons, subject.
  • the solution of the task according to the invention is that the platform in the area an entry and / or exit edge of the airfoil less than in the central region of the airfoil on the suction side over the surface of the Projecting airfoil, or that the airfoil in the area of the entry and exit edge does not have over its surface projecting platform, and so on axial space is saved.
  • the platform can with its perimeter to a circumference of the airfoil, which is located radially in one of the tip of the airfoil Range is adjusted, so the distance between the two above-mentioned perimeters except in the area of the entry and / or exit edge in is essentially constant.
  • the transition curvature may be from a central region of the airfoil in the direction be formed increasingly narrower on the entry and / or exit edge.
  • the transition curvature nestles for optimal design in terms of aerodynamics and strength to the surface of the airfoil and in the mounted state adjacent to the platform peripheral surface of the shroud.
  • the platform also has its circumference in the entry and / or exit edge respectively leaking on both sides, the problem of too narrow and difficult to manufacture edges occurs in the breakthroughs of the shroud not on.
  • the surface of the airfoil may be in the region of the entry and / or exit edge in the mounted state adjacent to the peripheral surface of the shroud, wherein in other area along the circumference of the airfoil, e.g. in the middle area the suction and pressure side, a projecting beyond the circumference of the airfoil Platform with a transition curvature exists.
  • the transition curvature may be from a central region of the airfoil, e.g. on the suction and pressure side, in the direction of the entry and / or exit edge increasingly be formed narrower, so that due to the narrower curvature in the area the entry and / or exit edge axial length is saved.
  • the transition curvature can be at least partially circular be and have a radius, wherein this in the central region of the airfoil larger than in the other areas along the circumference of the airfoil can. Indicates the airfoil along its entire circumference over its circumference projecting platform, the radius is in the area of the entry and / or exit edge to reduce the axial length smallest.
  • the radius may be along the circumference of the airfoil constant and its center be changed so that the transition curvature along the entire circumference to the surface of the airfoil snuggles and at the entry and / or exit edge a tangent jump to the peripheral surface of the shroud.
  • the production with constant radius is favorable.
  • the Tangentensprung at the entry and / or exit edge the until there can gradually increase, reduces the axial length of the Leitkanranzes.
  • Fig. 1 shows a portion of a known from the prior art Leitkanranzes with an outer shroud 1 and an airfoil 2, which has an end section 3 having.
  • the outer shroud 1 In the outer shroud 1 are a plurality of generally equidistantly arranged Breakthroughs 4 formed.
  • an airfoil 2 inserted with its end portion 3 and there by e.g. Soldering or Welding attached.
  • the end sections In order to allow the assembly, the end sections must 3 the blades 2 have a two-dimensional or constant profile. Also if the blades 2 are not necessary a constant profile over the entire Channel height must have their profile geometry is subject to assembly reasons significant limitations. The blades 2 must not bend hard or have significant thickening. It is also problematic, the proportionate narrow profiled apertures 4 in the shroud 1 form.
  • FIG. 2 shows a plan view of an embodiment of the built-around guide ring, FIG. in which an airfoil 2 in cross-section and at the free end of the Blade 2 subsequent platform 5 is shown.
  • an airfoil 2 in cross-section and at the free end of the Blade 2 subsequent platform 5 is shown.
  • the surface 8 of the airfoil 2 goes with a transition curvature 9 in the Platt form 6, which is designed so that in the mounted state both to the Surface 8 of the airfoil 2 and to the inner peripheral surface 10 of the Deckbands 1 hugs.
  • the transition curvature 9 is formed as a radius which in the central region 11 of the Blade 2 larger than in the region of the leading edge and the trailing edge 12, 13th is and until then, e.g. can gradually decrease.
  • the transition curvature 9 along the circumference have a constant radius, wherein in in this case the center of which is so changed towards the entry and exit edges 12, 13 that the circumferential curvature 9 also there to the surface 8 of the airfoil 2 hugs and, as shown in Fig. 7, to the inner peripheral surface 10 of the shroud 1 has a tolerable Tangentensprung. This alternative has manufacturing advantages.
  • Fig. 3 shows a sectional view of the shroud 1 and the airfoil 2, at the radius of the transition curvature 9 in the central region 11 of the airfoil 2 is shown.
  • the blade 2 is connected to the platform 5 in a breakthrough 4 in the Shroud 1 used, the profile or the shape of the opening 4 the profile or the circumference 6 of the platform 5 corresponds.
  • the platform 5 stands with its circumference 6 in this area 11 clearly above the surface 8 of the airfoil 2 before.
  • Fig. 4 is a section in the region of the inlet and outlet edge 12, 13 of the airfoil 2 shown.
  • the blade 2 is with its platform 5 in the shroud 1 trained breakthrough 4 used and attached.
  • the platform 5 points as transition curvature 9 to a radius that is significantly smaller than that in the center region 11, shown in Fig. 3, is, so that the platform 5 with its circumference. 6 protrudes significantly less over the surface 8 of the airfoil 2.
  • the radius or the transition curvature 9 nestles on the one hand to the surface 8 of the Blade 2 and on the other hand to the inwardly facing peripheral surface 10th of the shroud 1 on. Due to the significant reduction of the transition radius 9 in Area of the entry and exit edge 12, 13 is the axial length of the built Leitranz effectively reduced.
  • the openings 4 in the Make shroud 1 more efficient due to the absence of sharp edges or the like because the circumference 6 of the platform 5 is larger than that of the blade 2.
  • the reduction of the axial length in the embodiment 4 manufacturing technology advantageous also with a transition curvature. 9 be achieved with a constant radius along the circumference, if its center, as described above, to the entry and / or exit edge 12, 13 out changes and there is a Tangentensprung T at the transition to the shroud 1 is allowed.
  • the Tangentensprung T can at constant radius to the entry and / or exit edge 12, 13 gradually increase.
  • Fig. 5 shows another embodiment of the constructed Leitkanranzes, in which a cut airfoil 2 and a platform 5 are shown in plan view.
  • the platform 5 stands with its circumference 6 in the central region 11 of the blade 2 or on the pressure and suction side over the surface 8 of the airfoil 2 before and here has a transition curvature 9.
  • the platform 5 ends immediately adjacent to the leading edge 12 and the trailing edge 13 and is in these two Not areas above the profile or the circumference 7 of the airfoil 2 before.
  • the respectively on both sides of the entry and / or exit edge 12, 13 ending transition curvature 9 is formed to circumferentially contact the surface 8 hugs or there directly at the entry and exit edge 12, 13th expires. In this way, the axial dimensions of the built Leitkranzes effectively reduce without having narrow apertures 4 with sharp edges in the shrouds 1 must be made.
  • FIG. 5 While in the embodiment in Fig. 2 to 4 at the entry and exit edge 12, 13 a transition curvature 9 with a much smaller radius (or with the same Radius and changed center and tangent jump) than on the suction and pressure side is present, the embodiment of FIG. 5 in the area of Einund Exit edge 12, 13 formed without transition curvature 9, so that the surface 8 of the airfoil 2 in the assembled state directly to the inner Peripheral surface 10 of the shroud 1 adjacent.
  • FIG. 6 shows the embodiment of FIG. 5 in a sectional view, in which the Shroud 1, the blade 2 and the platform 5 directly in the area of the inlet and Exit edge 12, 13 is shown.
  • the airfoil 2 at the transition to the platform 5 no transition curvature 9, whereby the axial length is effectively reduced.
  • Platform 5 is in this area with its circumference 6 substantially not over the surface 8 of the airfoil 2 and its scope 7 before.
  • FIG. 7 shows the embodiment from FIG. 5 in a section shown in FIG. 5 adjacent to the entry and exit edges 12, 13 of the airfoil 2.
  • the transition curvature 9 has the same radius as in the central region 11 of the airfoil 2 on.
  • the representation of the transition curvature 9 in the central region 11 corresponds in this embodiment, that of the embodiment according to FIG. 2 and is shown in FIG.

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)

Claims (8)

  1. Anneau de guidage composé pour turbine à gaz, comprenant une sangle (1) avec une surface périphérique (10) et au moins une ailette (2) avec une surface supérieure (8), la sangle (1) comprenant au moins un passage (4) en vue de la fixation de l'ailette (2), et l'ailette (2) comprenant sur au moins une section d'extrémité (3) une plate-forme (5) dépassant au moins par sections de sa surface supérieure (8), comprenant une courbure de transition (9), laquelle plate-forme est insérée dans le passage (4), la plate-forme (5) dépassant de la surface supérieure (8) de l'ailette (2), dans la zone centrale (11) de l'ailette (2) sur le côté d'aspiration et de pression, et la plate-forme (5) dépassant de la surface supérieure de l'ailette (2), dans la zone d'une arête d'entrée et/ou de sortie (12, 13) de l'ailette (2) moins que dans la zone centrale (11) de l'ailette (2) sur le côté de pression, caractérisé en ce que la plate-forme (5) dépasse de la surface supérieure de l'ailette (2) dans la zone d'une arête d'entrée et/ou de sortie (12) de l'ailette (2) moins que dans la zone centrale (11) de l'ailette (2) sur le côté d'aspiration, ou en ce que l'ailette (2) ne comprend dans la zone de l'arête d'entrée et/ou de sortie (12, 13) aucune plate-forme (5) dépassant de sa surface supérieure (8).
  2. Anneau de guidage composé selon la revendication 1, caractérisé en ce que la plate-forme (5) avec sa périphérie (6) est adaptée à une périphérie (7) de l'ailette (2).
  3. Anneau de guidage composé selon la revendication 1 ou 2, caractérisé en ce que la courbure de transition (9) est conçue en étant de plus en plus étroite depuis une zone centrale (11) de l'ailette (2) en direction d'une arête d'entrée et/ou de sortie (12, 13).
  4. Anneau de guidage composé selon l'une des revendications précédentes, caractérisé en ce que la courbure de transition (9) est adaptée à la surface supérieure (8) de l'ailette (2) et d'une surface périphérique (10) adjacente de la sangle (1).
  5. Anneau de guidage composé selon l'une des revendications précédentes, caractérisé en ce que la surface supérieure (8) de l'ailette (2) dans la zone de l'arête d'entrée et/ou de sortie (12, 13) est adjacente à la surface périphérique (10) de la sangle (1).
  6. Anneau de guidage composé selon l'une des revendications précédentes, caractérisé en ce que la courbure de transition (9) est réalisée au moins par sections comme un rayon.
  7. Anneau de guidage composé selon la revendication 6, caractérisé en ce que le rayon dans une zone centrale (11) de l'ailette (2) est plus grand que dans les autres zones le long de la périphérie (7) de l'ailette (2).
  8. Anneau de guidage composé selon la revendication 7, caractérisé en ce que le rayon est constant le long de la périphérie (7) de l'ailette (2) et son point central est modifié de sorte que la courbure de transition (9) est adaptée le long de l'ensemble de la périphérie (7) à la surface supérieure (8) de l'ailette (2) et un saut de tangente (T) par rapport à la surface périphérique (10) de la sangle (1) est présent sur le côté d'entrée et/ou de sortie (12, 13).
EP00115821A 1999-08-30 2000-07-22 Anneau de guidage composé pour turbines à gaz Expired - Lifetime EP1081336B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19941133A DE19941133C1 (de) 1999-08-30 1999-08-30 Gebauter Leitkranz für eine Gasturbine, insbesondere ein Flugtriebwerk
DE19941133 1999-08-30

Publications (3)

Publication Number Publication Date
EP1081336A2 EP1081336A2 (fr) 2001-03-07
EP1081336A3 EP1081336A3 (fr) 2003-10-01
EP1081336B1 true EP1081336B1 (fr) 2005-02-02

Family

ID=7920103

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00115821A Expired - Lifetime EP1081336B1 (fr) 1999-08-30 2000-07-22 Anneau de guidage composé pour turbines à gaz

Country Status (3)

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US (1) US6543998B1 (fr)
EP (1) EP1081336B1 (fr)
DE (2) DE19941133C1 (fr)

Families Citing this family (13)

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Publication number Priority date Publication date Assignee Title
FR2899270A1 (fr) * 2006-03-30 2007-10-05 Snecma Sa Aube de redresseur a amenagement de forme localise, secteur de redresseurs, etage de compression, compresseur et turbomachine comportant une telle aube
FR2899269A1 (fr) * 2006-03-30 2007-10-05 Snecma Sa Aube de redresseur optimisee, secteur de redresseurs, etage de compression, compresseur et turbomachine comportant une telle aube
US7748956B2 (en) * 2006-12-19 2010-07-06 United Technologies Corporation Non-stablug stator apparatus and assembly method
US8740557B2 (en) * 2009-10-01 2014-06-03 Pratt & Whitney Canada Corp. Fabricated static vane ring
US8920117B2 (en) * 2011-10-07 2014-12-30 Pratt & Whitney Canada Corp. Fabricated gas turbine duct
US9840929B2 (en) * 2013-05-28 2017-12-12 Pratt & Whitney Canada Corp. Gas turbine engine vane assembly and method of mounting same
US9869190B2 (en) 2014-05-30 2018-01-16 General Electric Company Variable-pitch rotor with remote counterweights
US20160017731A1 (en) * 2014-07-17 2016-01-21 Rolls-Royce Corporation Vane assembly
US10072510B2 (en) 2014-11-21 2018-09-11 General Electric Company Variable pitch fan for gas turbine engine and method of assembling the same
US9988918B2 (en) * 2015-05-01 2018-06-05 General Electric Company Compressor system and airfoil assembly
US10100653B2 (en) 2015-10-08 2018-10-16 General Electric Company Variable pitch fan blade retention system
US11674435B2 (en) 2021-06-29 2023-06-13 General Electric Company Levered counterweight feathering system
US11795964B2 (en) 2021-07-16 2023-10-24 General Electric Company Levered counterweight feathering system

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Publication number Priority date Publication date Assignee Title
US2681788A (en) * 1951-05-23 1954-06-22 Solar Aircraft Co Gas turbine vane structure
FR1095927A (fr) * 1953-02-02 1955-06-07 Bristol Aeroplane Co Ltd Perfectionnements apportés au montage des aubes à profil d'aile dans les compresseurs et autres applications
DE1200070B (de) * 1961-11-21 1965-09-02 Siemens Ag Verfahren zum Herstellen von Leitschaufel-kranzsegmenten fuer Gasturbinen
FR1389254A (fr) * 1963-04-08 1965-02-12 Rolls Royce Compresseur pour moteur à turbine à gaz
US4260327A (en) * 1979-07-25 1981-04-07 General Electric Company Guide vane assembly for reverse flow cooled dynamoelectric machine
DE3514122A1 (de) * 1985-04-19 1986-10-23 MAN Gutehoffnungshütte GmbH, 4200 Oberhausen Verfahren zur herstellung einer leitschaufel fuer ein turbinen- oder verdichter-leitrad und nach dem verfahren hergestellte leitschaufel
US5474419A (en) * 1992-12-30 1995-12-12 Reluzco; George Flowpath assembly for a turbine diaphragm and methods of manufacture
GB9417406D0 (en) * 1994-08-30 1994-10-19 Gec Alsthom Ltd Turbine blade
US5765993A (en) * 1996-09-27 1998-06-16 Chromalloy Gas Turbine Corporation Replacement vane assembly for fan exit guide

Also Published As

Publication number Publication date
DE50009400D1 (de) 2005-03-10
EP1081336A2 (fr) 2001-03-07
EP1081336A3 (fr) 2003-10-01
DE19941133C1 (de) 2000-12-28
US6543998B1 (en) 2003-04-08

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