EP0937864B1 - Configuration des aubes de guidage pour une turbomachine axiale - Google Patents

Configuration des aubes de guidage pour une turbomachine axiale Download PDF

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Publication number
EP0937864B1
EP0937864B1 EP99103156A EP99103156A EP0937864B1 EP 0937864 B1 EP0937864 B1 EP 0937864B1 EP 99103156 A EP99103156 A EP 99103156A EP 99103156 A EP99103156 A EP 99103156A EP 0937864 B1 EP0937864 B1 EP 0937864B1
Authority
EP
European Patent Office
Prior art keywords
housing
guide vane
vane ring
shroud
guide
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
EP99103156A
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German (de)
English (en)
Other versions
EP0937864A2 (fr
EP0937864A3 (fr
Inventor
Hermann Klingels
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 EP0937864A2 publication Critical patent/EP0937864A2/fr
Publication of EP0937864A3 publication Critical patent/EP0937864A3/fr
Application granted granted Critical
Publication of EP0937864B1 publication Critical patent/EP0937864B1/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F01D9/042—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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/60—Assembly methods
    • F05B2230/604—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins
    • F05B2230/606—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation

Definitions

  • the invention relates to a turbomachine with rotor and stator in fluidic one or more stages, according to the preamble of the patent award 1.
  • Such a turbomachine is known, for example from DE-PS 27 45 130 b e-know this writing is specific to axial turbines with labyrinth seals refers.
  • the flow channel of the working medium leads alternately by Leit- and Blade rims wherein the static components are radially from the outside, the rotating ones protrude radially from the inside into this.
  • Figure 1 clearly shows this document gives there are both radially inwardly disposed seals between the rotor and the vane rings ("Inner Airseal") as well as radially outwardly disposed seals between the blades and the stator (“Outer Airseal").
  • the sealing fins (Pos.8) of the "Inner Airseal” attached to the rotor (Pos.4) so that their dimensions or deviations from the Ve r-ratios depend on the rotor (temperature, speed).
  • the associated seal s-lining (Pos.7) is in contrast to the inner shroud (Pos. 20) of the vane segments (Pos.1,5) attached.
  • the vane segments are on the housing (pos. 13,14), so that the dimensions or deviations of the sealing coating Ultimately be determined by the conditions outside the housing significantly.
  • each vane segment there is a longitudinally angled abutment with a radially outwardly facing abutment surface which, in operation, is forced against the corresponding hook-shaped housing member around the upstream "claw bearing" as a result of a flow-induced overturning moment (see Fig.1).
  • DE-PS 35 40 943 describes such a gap control system especially for a Turbofan engine.
  • the secondary air duct extends at least until to the end of the turbine area and has openings (Pos.11) in its inner wall on, by the secondary air from the outside targeted to areas of the turbine housing can be blown.
  • This simplified ACC system may have the problem of that the low pressure of the secondary air flow is not sufficient to Locally confined housing zones by correspondingly small flow cross sections To generate cooling air flows with sufficient mass flow rate.
  • Compressor air is discharged from the booster or low-pressure compressor branched off as a coolant, guided in separate channels and valves blown targeted.
  • vane rings In smaller gas turbine engines, it is known to use vane rings as self-supporting, to perform integral components with closed shrouds and centered in the housing.From manufacturing and strength engineering Reasons (thermal stresses) is this "monolithic" solution on blade rings limited to relatively small dimensions.
  • DE-OS 33 36 420 describes a mechanism for protection against over-rotation a gas turbine rotor at break.
  • the mechanism works in the Way that the vane segments of at least one vane ring axially pivoted and brought into contact / engagement with adjacent blades become.
  • the reciprocal mechanical vane friction and destruction brakes the rotor quickly and effectively.
  • the vane segments associated with the mechanism each have a pivot bearing on the outer shroud segment and are on their inner circumference by means of a positive, annular reinforcing element connected so that the segments together a stiff, self-supporting Forming the vane ring.
  • U.S. Patent 3,588,267 protects a plastic diaphragm vane construction, in which the blades are attached to a closed, inner torus are and form a self-supporting wreath with this.
  • the outer blade tips are deckbandless and directly in recesses of a metallic Glued housing, the elasticity of the bond small relative displacements compensates / receives. It is obvious that this construction is for higher temperatures is completely unusable and at best in fan or Niederbuchverêtr Schl.
  • a turbomachine with rotor and stator and with at least e-stens a, each having an outer and an inner shroud having vane ring which, in all operating states, can be achieved by an optimum gap attitude, i.e. by particularly low, little varying and mathematically well detectable Leakage losses, thus a high efficiency, as well as by a relative simple, cost-effective and low-weight, durable and easy to maintain design without the requirement of an active gap control system (ACC's) and also with great performances and dimensions executable and functional is.
  • ACC's active gap control system
  • the invention is thus in the thermal decoupling of housing and vanes by means of a special design and storage / centering at least a Leitschaufelkranzes and by air cooling of the housing.
  • the - at least e-stens one - vane ring is a self-supporting component with a reinforcement executed on the inner shroud, which stiffens him against everting axial deformation. Starting from an approximately flat, radial alignment of the blade axes in the unloaded state these are due to the static pressure difference before / behind the guide vane ring at deflection "zero" on the housing towards the Kranzmitte z u-taking axially deflected and u.U. also curved.
  • the vane ring mechanically comparable to a disc spring, its inner edge (Hole edge) the inner shroud, and the outer edge of the outer shroud forms.
  • the inner shroud is displaced both axially and through the Shovel-induced moments twisted / staggered. That is, in radial-axial sections visible material cross-sections of the shroud are gedac h-te, perpendicular to the cutting surface, depending on the stiffness / reinforcement more or less twisted.
  • the inventive reinforcement of the inner shroud against said buckling also reduces the axial deflection of the blade axes and thus the gesa m te Deformation of the vane ring under load. This improves the dimensional stability the static component of "Inner Airseal".
  • This shows a partial longitudinal section through the low-pressure turbine of a turbojet engine.
  • the present invention is generally applicable to turbomachinery with rotor and stator, i.e. for compressors and turbines, suitable, which at least partially in Axial design, i. with predominantly axial flow, are executed.
  • thermodynamic and dimensionally likely low pressure turbines medium to large Gas turbine engines represent preferred use cases, which is why the figure Example from this area shows.
  • the low-pressure turbine 1 From the low-pressure turbine 1 are the first two stages and this in turn The relevant elements of the upper half are shown, with the turbines / engine axis would be horizontally below the representation.
  • the flow direction of the working gas runs from left to right, i. first through the vane ring 14, then through the area of the blades 3, anschli- Hd through the vane ring 15 and through the region of the rotor blades 4, where still further stages (guidance, running) can follow.
  • the outer engine shell forms the housing 13 in which the vane rings 14,15 radially centered and are mounted axially fixed. Both the blades 3,4 and the vane rings 14,15 are executed with inner and outer shrouds 5 to 8 and 16 to 19, the inner and outer blade shrouds each between the blades have parting lines, u.a. damaged blades can be individually replaced are.
  • the vane rings 14,15 are designed as self-supporting components, wherein their mechanical stability predominantly in the area of the inner shrouds 16,17 is achieved. There are circumferentially closed, i. "Encircling” Reinforcements 20,21 arranged, which also the thermal behavior (dimensional and Shape changes) of the Leitschaufelkränze 14,15 decisively influence.
  • the Gas forces during operation cause u.a. an everting axial deformation of the vane rings, i.e. a from the outer to the inner shroud increasing axial deflection with a certain twist of the shrouds in itself.
  • This "plate spring-like" deformation can be about the reinforcements on the inner Reduce shrouds considerably.
  • reinforcements are the illustrated toroidal hollow body, axially spaced rings, combinations of Hollow and solid profiles, etc. suitable, whereby the space is a role play.
  • the reinforcements should in any case - in axial / radial section - a possible large area moment of inertia about a radial axis, e.g. through the centroid have, what by sufficient, axially spaced surface portions is reachable.
  • the surface portions of the shroud are to be considered here.
  • a reinforcing material with a high modulus of elasticity is advantageous.
  • Overall should be at As small as possible increase in mass an optimum increase in stiffness can be achieved. The determination of the stresses and deformations in the "everting" is more than appropriate Calculation method possible.
  • the reinforcement 20 is positively connected to the shroud 16, wherein the Leitschaufelkranz 14 may consist of several segments, which on the Ve r-strengthening held together.
  • the gain 21, however, is in the Dec k band 17 integrated, i. cohesively joined with this. Again, here you can Leitschaufelsegmente be the output parts, which by welding or Soldering in the area of the inner Deckba / the reinforcement are connected.
  • outer shrouds 18,19 are still segmented in the installed state be, i. have several joints on the circumference to thermoelectric voltages too minimize.
  • the "Inner Airseal” is here - at least predominantly - executed with brush seals, wherein in the region of the vane ring reinforcements fixed brushes 22,23 run against connected to the rotor 2 rings 11,12, which axial stops for form the blades 3,4.
  • the "Outer Airseal" is realized here with labyrinth seals, ring-like Dense tips run 9,10 against honeycomb structures, which on honeycomb carrier 28,29 are applied.
  • the honeycomb carriers 28,29 are in turn on the vane rings 14,15 stored and thereby aligned in the deformation behavior of these.
  • the Leitschaufelkränze provided which constructively but not so much consuming, like an ACC system.
  • the Leitschaufelkränze provided which constructively but not so much consuming, like an ACC system.
  • the entrance The generally branched off from the compressor cooling air via bores 35 in a first chamber 33.
  • Wall elements 36, 38 are arranged, which working gas secondary flows, i. -losses, to prevent these passages. For cooling reasons, these are also Wall elements 36,38 deliberately carried something gas permeable or fixed.

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

Claims (6)

  1. Turbomachine comprenant un rotor et un stator, au moins d'un type partiellement axial concernant la technique des turbomachines, turbomachine dont le rotor comprend des aubes mobiles et dont le stator comprend une carcasse dotée d'aubes fixes, où les aubes fixes sont configurées comme au moins une couronne d'aubes fixes comprenant un feuillard de recouvrement intérieur, dans le sens radial, et un feuillard de recouvrement extérieur, dans le sens radial, en particulier une turbine basse pression axiale caractérisée par la combinaison des caractéristiques suivantes :
    (A) au moins une couronne d'aubes fixes (14, 15) est conçue comme un élément autoporteur comprenant un renfort (20, 21), sur le feuillard de recouvrement intérieur (16, 17), rigidifiant l'élément contre une déformation axiale due à l'enfoncement, ce renfort étant au moins largement symétrique en rotation et fermé dans la direction périphérique,
    (B) la au moins une couronne d'aubes fixes (14, 15) comprend un feuillard de recouvrement (18, 19) extérieur segmenté comportant plusieurs joints de séparation répartis sur sa périphérie, et
    (C) la couronne d'aubes fixes est positionnée, dans la carcasse (13), au moyen à chaque fois d'une unité de palier (24, 25, 26, 27) permettant, localement, des mouvements relatifs dans le sens radial, par au moins trois segments du feuillard de recouvrement extérieur (18, 19), c'est-à-dire qu'elle est positionnée, dans l'ensemble, par ce que l'on appelle un centrage des rayons, avec au moins trois rayons, et
    (D) une coque de guidage d'air (30) est disposée entre la carcasse (13) et le feuillard de recouvrement extérieur (18, 19) de la au moins une couronne d'aubes fixes (14, 15), laquelle coque de guidage d'air guide un flux d'air froid le long du côté intérieur de la carcasse et est dotée d'ouvertures (31, 32) pour les éléments de palier (26, 27), solidaires de la carcasse, de la au moins une couronne d'aubes fixes (14, 15), où les ouvertures (31, 32) laissent passer une partie de l'air froid circulant jusqu'au feuillard de recouvrement (18, 19).
  2. Turbomachine selon la revendication 1, caractérisée en ce que le renfort (20, 21) d'au moins une couronne d'aubes fixes (14, 15) est configuré comme un corps creux de forme torique ou sous la forme d'au moins deux anneaux espacés axialement et est intégré, de façon compatible concernant les matériaux, dans le feuillard de recouvrement intérieur (17) ou est relié, par sûreté de forme, à celui-ci (16).
  3. Turbomachine selon la revendication 2 comprenant une jonction, par sûreté de forme, entre le renfort et le feuillard de recouvrement intérieur d'au moins une couronne d'aubes fixes, caractérisée en ce qu'au moins une couronne d'aubes fixes (14) se compose de plusieurs segments d'aubes fixes, lesquels segments sont assemblés, au moyen du renfort (20), pour former un élément autoporteur.
  4. Turbomachine selon l'une quelconque ou plusieurs des revendications 1 à 3, caractérisée en ce que le renfort (20, 21) d'au moins une couronne d'aubes fixes (14, 15) supporte l'élément statique d'une garniture étanche de l'arbre, en particulier la brosse (22, 23) d'une garniture étanche de brosse ou le revêtement d'entrée ou la structure alvéolaire d'un joint à labyrinthe.
  5. Turbomachine selon l'une quelconque ou plusieurs des revendications 1 à 4, caractérisée en ce que chaque unité de palier d'au moins une couronne d'aubes fixes (14, 15) se compose d'un tourillon (26, 27), solidaire de la carcasse, comprenant une surface de contact bombée, et d'un coussinet (24, 25), solidaire du feuillard de recouvrement, comprenant une surface de contact cylindrique.
  6. Turbomachine selon l'une quelconque ou plusieurs des revendications 1 à 5, caractérisé en ce que le conduit d'écoulement du flux d'air froid, entre la carcasse (13) et la coque de guidage d'air (30), est réparti dans plusieurs chambres (33, 34) traversées par l'écoulement les unes après les autres, la pression intérieure diminuant d'une chambre à l'autre, où chaque chambre (33, 34) est conçue pour une pression de fonctionnement qui est au moins légèrement supérieure à la pression dans la zone du conduit d'écoulement, à chaque fois voisin, du milieu utilisé.
EP99103156A 1998-02-20 1999-02-18 Configuration des aubes de guidage pour une turbomachine axiale Expired - Lifetime EP0937864B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19807247A DE19807247C2 (de) 1998-02-20 1998-02-20 Strömungsmaschine mit Rotor und Stator
DE19807247 1998-02-20

Publications (3)

Publication Number Publication Date
EP0937864A2 EP0937864A2 (fr) 1999-08-25
EP0937864A3 EP0937864A3 (fr) 2000-10-25
EP0937864B1 true EP0937864B1 (fr) 2003-08-13

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EP99103156A Expired - Lifetime EP0937864B1 (fr) 1998-02-20 1999-02-18 Configuration des aubes de guidage pour une turbomachine axiale

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US (1) US6139263A (fr)
EP (1) EP0937864B1 (fr)
JP (1) JP4230040B2 (fr)
DE (2) DE19807247C2 (fr)

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EP2647795B1 (fr) 2012-04-04 2018-11-07 MTU Aero Engines AG Système d'étanchéité pour turbomachine
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CN103482219B (zh) * 2013-09-16 2016-06-01 沈阳黎明航空发动机(集团)有限责任公司 一种燃气轮机运输过程中对转子进行轴、径向定位方法
DE102014209057A1 (de) * 2014-05-14 2015-11-19 MTU Aero Engines AG Gasturbinengehäuseanordnung
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IT201900014736A1 (it) 2019-08-13 2021-02-13 Ge Avio Srl Elementi di tenuta integrali per pale trattenute in un rotore a tamburo esterno anulare girevole in una turbomacchina.
IT201900014724A1 (it) 2019-08-13 2021-02-13 Ge Avio Srl Elementi di trattenimento delle pale per turbomacchine.
IT201900014739A1 (it) 2019-08-13 2021-02-13 Ge Avio Srl Elementi di trattenimento delle pale per turbomacchine.
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Also Published As

Publication number Publication date
JP4230040B2 (ja) 2009-02-25
JPH11294103A (ja) 1999-10-26
DE59906550D1 (de) 2003-09-18
US6139263A (en) 2000-10-31
EP0937864A2 (fr) 1999-08-25
DE19807247C2 (de) 2000-04-20
EP0937864A3 (fr) 2000-10-25
DE19807247A1 (de) 1999-09-09

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