EP0485556B1 - Couronne directrice d'une turbine d'un groupe propulseur a turbine a gas - Google Patents

Couronne directrice d'une turbine d'un groupe propulseur a turbine a gas Download PDF

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Publication number
EP0485556B1
EP0485556B1 EP91909879A EP91909879A EP0485556B1 EP 0485556 B1 EP0485556 B1 EP 0485556B1 EP 91909879 A EP91909879 A EP 91909879A EP 91909879 A EP91909879 A EP 91909879A EP 0485556 B1 EP0485556 B1 EP 0485556B1
Authority
EP
European Patent Office
Prior art keywords
ring
guide
elements
vane
vane ring
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
EP91909879A
Other languages
German (de)
English (en)
Other versions
EP0485556A1 (fr
Inventor
Oskar Ostermeir
Wolfgang Krüger
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 GmbH
Original Assignee
MTU Motoren und Turbinen Union Muenchen 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 Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of EP0485556A1 publication Critical patent/EP0485556A1/fr
Application granted granted Critical
Publication of EP0485556B1 publication Critical patent/EP0485556B1/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
    • F01D9/041—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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics

Definitions

  • the invention relates to a guide ring according to the preamble of patent claim 1.
  • Such a guide ring is known from DE-PS 37 38 439. It is a so-called “semi-integral guide ring", in which either one ring (outer ring) or the other ring (inner ring) is manufactured separately from the blades and is not directly an integral part of the guide grill; this guide ring is preferably used in a gas turbine in the high-pressure turbine. Due to the high temperature differences occurring there, the guide rings expand, which leads to significant shifts in the radial direction. Furthermore, axial displacements occur due to the different thermal expansions between the inner and outer housing, which have to be mastered for a guide ring which is connected to the two housings via the rings in question, in order to prevent tension or even component breaks.
  • the separate or other ring or the ring fixed to the guide vanes should be arranged axially displaceably and pressed against one another by means of a tensioning device.
  • the disadvantage of this arrangement is that in addition to the aforementioned leaks, relatively complex guide devices for the axially movable part are to be provided, with extremely different component temperatures and expansions being problematic for the precise guidance required.
  • the object of the present invention is to provide a generic guide ring which, on the one hand, does not hinder the axial relative displacements and, on the other hand, drastically minimizes leakages between the free blade ends and the separate sealing ring, and can be implemented with the simplest possible design.
  • the main advantages of the invention are that the axial relative displacements between the outer and inner housing or the relevant sections of this housing and the associated one and the other ring (outer and inner ring) can be completely compensated by the free blade tips on the slotted piston ring-like elements can slide. At least two ring elements arranged axially one behind the other form a cylindrical sliding surface for the blade tips, so that thermal displacements in the axial direction are possible without hindrance.
  • axially slotted is understood to mean that a ring element, similar to a piston ring of a reciprocating piston engine, is interrupted at one point, so that certain deformations of the ring element are possible while changing the gap width in the circumferential direction.
  • the gap of a ring element in the cold state is preferably about 1-5 mm, in particular 2-3 mm, the size and shape depending on the individual case from the geometries, materials and temperatures.
  • the slotted ring elements are arranged such that the axial gaps of the rings are offset from one another in the circumferential direction.
  • the design according to the invention is equally applicable to a radially outer or radially inner ring which is held separately from the blades.
  • non-blade-resistant other ring can consist of several, e.g. operate two, three or four piston ring-like elements arranged axially one behind the other. This has the advantage that the gaps are interrupted in the axial direction, and a possibly non-uniform contact pressure of the individual ring elements is divided over several blades.
  • the design according to the invention is particularly suitable for ceramic components, ie the semi-integral guide ring is made of ceramic materials. Ceramics offer many advantages over metallic materials such as less wear due to high hardness and high chemical resistance, great shape retention in a wide temperature range, and any availability of raw materials.
  • the guide ring is preferably made of sintered silicon carbide (SSiC) because it retains its flexural strength up to about 1850 K and is characterized by low thermal expansion, high thermal conductivity and high sensitivity to thermal shock.
  • the guide ring or guide vanes can also be made of metal, however, wear protection layers should be provided on the tips rubbing with the slotted ring elements.
  • the guide vanes can be solid or designed as hollow blades.
  • the slotted ring elements are preferably made of ZrO2, because this material is characterized on the one hand by a low heat conduction, and on the other hand by a low modulus of elasticity, which makes the spring travel longer than, for example, when using SiC.
  • the ring elements are arranged on a support ring, likewise slotted in the axial direction, on which the tensioning device is supported.
  • the tensioning device acts in the radial direction in order to press the slotted ring elements against the free blade tips.
  • the tensioning device is designed as a spring ring corrugated in the circumferential direction.
  • This training is structurally particularly simple.
  • other embodiments of the invention are also conceivable, such as single leaf springs or a metallic and thin-walled ring that is pressurized on the inside.
  • this is preferably arranged between a housing section of the flow channel and the support ring.
  • a ceramic guide ring provides that between the one, for example radially outer ring of the guide ring and associated housing sections, a further spring element is provided.
  • This is designed in particular as a metallic wire mesh.
  • a ceramic guide ring 1 of a turbine stage of a gas turbine engine which essentially ends from the one radially outer ring 2a with integral molded, distributed over the circumference guide vanes 3, and the other, radially inner end of the blade seated ring 4a.
  • the guide ring 1 is arranged in an annular flow channel 5, upstream of the blades 6 of the turbine stage in question.
  • the ring 2a is fixed in a radially thermally compatible manner with a circumferential web 8 in a circumferential groove, which is created between the housing section 7 and a further housing section 10, which is connected to it via rivets 9 and is designed as a support ring 10.
  • the one ring 2a is held over a segmented, ceramic insulating ring 11 and a wire mesh 12 arranged between the insulating ring 11 and the section 10, which is loosened on both elements 10, 11.
  • knobs or the like are provided between the insulating ring 11 and the web 8; e.g.
  • a key-like member could also be provided, engaging in corresponding axial grooves of the ring 11 and the web 8.
  • the insulating ring 11 can be segmented in order to provide elastic support for the one, here e.g. to enable radially outer ring 2a.
  • further housing elements 13a and 13b are provided and a sealing ring downstream of the housing section 10 is designated by 14.
  • the radially inner other ring 4a consists of three ceramic piston-like elements 15a, 15b and 15c arranged axially one behind the other and slotted in the axial direction. These are supported on one side on a support ring 16, which is located between two sections 17a, 17b, which are designed as circumferential guide flanges, of the radially inner side lying housing is fitted.
  • the support ring 16 is made, for example, of a metallic material, a ceramic insulating layer 18 advantageously being applied to its outer circumference.
  • the support ring 16 is also axially slotted to enable radial movements.
  • a clamping device 19 is located between the support ring 16 and the one radially inner section 20 of the housing in order to apply a radially outward clamping force to the support ring 16, so that the slotted piston ring-like elements 15a, 15b, 15c against the outer free ends or Blade tips 21 of the guide vanes 3 are pressed, whereby a low-leakage connection between the tips 21 of the guide vanes 3 and the other ring 4a is made possible over the entire free blade length.
  • the clamping device 19 is e.g. formed as a corrugated spring ring 19 '. Cooling air, e.g. supplied from the compressor in order to keep the metallic spring parts, in particular thus the spring ring 19 'at a low temperature and thus to ensure perfect elasticity over a comparatively long operating time.
  • the guide ring 1 according to the invention is shown in an axial view, the one radially outer ring 2a, the guide vanes 3 and the other ring 4a produced as a separate component of the guide ring 1 being shown.
  • the foremost of the rings 15a slotted in the axial direction can be seen with its axial slot 22a.
  • the axial slots of the other slotted rings 15b and 15c are offset in the circumferential direction with respect to the axial slot 22a.
  • the ring 15a sits on the support ring 16, which also has an axial slot 23.
  • the tensioning device 19 designed as a spring ring 19 'can be clearly seen, the spring ring 19 'runs corrugated in the circumferential direction between the support ring 16 and the section 20 of the radially inner housing.
  • the other ring 4b lying radially on the inside consists of only two slotted rings 15d, 15e arranged axially one behind the other, which e.g. are made of a metallic material.
  • Spring washer, radially inner portion of the housing and support ring are provided according to FIG. 1 and designated 19 ', 20 and 16.
  • the radially outer ring 2a is fixedly connected to the guide vanes 3 and directly fixed to a radially outer wall section 22 of the housing for the flow channel 5.
  • the other radially outer ring 2b has a plurality of ring-shaped elements, while the guide vanes 3 are integrally formed on the radially inner ring 4c.
  • This one ring 4c is directly and firmly connected to a radially inner wall section 22 'of the housing for the flow channel 5.
  • an elastic design similar to the wire mesh 12 shown in FIG. 1 can also be used in this embodiment, on the side facing the one ring 4c.
  • the relevant other ring 2b in FIG. 4 consists of four piston ring-like elements 23a, b, c, d arranged axially one behind the other, all of which are arranged on the support ring 24.
  • the tensioning device acts with the spring ring 19 'between the support ring 24 and the relevant radially outer section 7 of the housing.
  • a number of guide vanes 3 can be seen which are seated on the radially inner other ring 4a consisting of three slotted piston ring-like elements 15a, 15b and 15c.
  • all axial slots 22a, 22b and 22c have been rotated into the area shown, while these slots should in fact preferably be distributed uniformly over the circumference and offset relative to one another.
  • three different embodiments of axial slots 22 are shown, all of which are included in the subject matter of the invention. In practice, the same slot configuration will be expediently chosen for all three ring elements 15a, 15b and 15c for reasons of simplification.
  • the axial slot 22a of the ring element 15a runs exactly in the axial direction.
  • the axial slot 22b of the second ring element 15b is oriented at an angle to the axial direction, an angle which approximately corresponds to the direction of flow of the gas in this section of the guide ring expediently being chosen to minimize flow losses;
  • the slot shape 22c shown in the third ring element 15c has a step-like shoulder 24.

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

Abstract

Couronne directrice munie d'aubes directrices (3) sur deux anneaux (2a, 4a) disposés coaxialement avec un certain écart radial entre eux, ceux-ci devant être maintenus sur des tronçons associés du bâti (10, 7; 20, 17a, 17b) exposés à des dilatations thermiques différentes; l'un des anneaux (2a) doit être solidaire des aubes directrices (3), tandis que l'autre anneau (4a) doit être relié aux extrémités libres des aubes directrices (3) par une force de pression exercée par un dispositif de serrage (19); en outre, l' autre anneau (4a) doit être décomposé en plusieurs éléments (15a, 15b, 15c) du type bague de piston, en succession axiale, chacun de ces éléments étant rainuré sensiblement axialement et formant une surface de glissement cylindrique pour l'ensemble des extrémités libres des aubes (3). Le dispositif de serrage (19) doit être conçu de façon qu'il exerce une force de pression répartie radialement uniformément sur les éléments (15a ... 15c), et qu'il soit monté sur l'un des tronçons associés (20, 17a, 17b) du bâti.

Claims (14)

  1. Couronne directrice (1) d'une turbine d'un groupe propulseur à turbine à gaz, avec des aubes directrices (3) sur deux anneaux (2a, 4a) disposés coaxialement et radialement à une certaine distance l'un de l'autre, et qui sont maintenus sur des parties d'enveloppe associées (10,7 ;20, 17a, 17b) exposées à des dilatations thermiques différentes, dans laquelle le premier anneau (2a) est relié de façon inamovible aux aubes directrices (3), l'autre anneau (4a) étant relié aux extrémités libres des aubes directrices (3) par l'effort d'application de pression d'un dispositif de serrage (19) qui est disposé sur une des parties associées (10,7 ;20, 17a, 17b) de l'enveloppe, couronne directrice caractérisée en ce que :
    - l'autre anneau (4a) est décomposé en plusieurs éléments (15a, 15b, 15c) en forme de segments annulaires se succédant axialement, qui sont respectivement fendus à peu près axialement et qui forment une surface de glissement cylindrique sur laquelle les aubes directrices (3) reposent par l'ensemble de leurs extrémités libres, en étant susceptibles de se déplacer axialement,
    - le dispositif de serrage (19) est réalisé d'une façon telle qu'il exerce un effort de pression radial uniformément réparti sur les éléments.
  2. Couronne directrice selon la revendication 1, caractérisée en ce que les fentes essentiellement axiales (22a, 22b, 22c) des éléments en forme de segments annulaires (15a, 15b, 15c) sont décalées uniformément les unes par rapport aux autres en direction périphérique.
  3. Couronne directrice selon la revendication 1 ou la revendication 2, caractérisée en ce que les éléments en forme de segments annulaires (15a, 15b, 15c ; 23a, ... 23d) et le dispositif de serrage (19) sont disposés radialement à l'intérieur ou radialement à l'extérieur sur les parties associées (20, 17a, 17b ;7) de l'enveloppe.
  4. Couronne directrice selon l'une des revendications 1 à 3, caractérisée en ce que les anneaux (2a, 4a) ou bien les éléments en forme de segments annulaires (15a, 15b, 15c) sont fabriqués en un matériau céramique.
  5. Couronne directrice selon l'une ou plusieurs des revendications 1 à 4, caractérisée en ce que les aubes directrices (3) sont fabriquées en un matériau céramique.
  6. Couronne directrice selon la revendication 1 ou 2, caractérisée en ce que les éléments en forme de segments annulaires (15a ... 15c ; 23a ... 23d) sont disposés sur un anneau de soutien (16, 24) également fendu en direction axiale, sur lequel prend appui le dispositif de serrage vis-à-vis de la partie considérée (20 ; 7) de l'enveloppe.
  7. Couronne directrice selon l'une ou plusieurs des revendications 1 à 6, caractérisée en ce que l'effort de pression du dispositif de serrage (19) est produit par un élément élastique.
  8. Couronne directrice selon la revendication 7, caractérisée en ce que l'élément élastique est un anneau élastique ondulé (19').
  9. Couronne directrice selon l'une ou plusieurs des revendications 1 à 8, caractérisée en ce que le premier anneau (2a) placé en face des éléments en forme de segments annulaires (15a, 15b, 15c) et relié de façon inamovible aux aubes directrices (3), est relié par l'intermédiaire d'un autre élément élastique (12) en direction radiale, de façon thermiquement compatible, aux premières parties d'enveloppe (7, 10).
  10. Couronne directrice selon la revendication 9, caractérisée en ce que les premières parties d'enveloppe (7, 10) forment une gorge périphérique dans laquelle le premier anneau (2a) est maintenu et centré par une nervure (8) et vient en prise par adhérence et engagement positif sur un anneau isolant (11) en céramique, qui est relié à l'élément élastique (12) dans la gorge périphérique.
  11. Couronne directrice selon la revendication 9, caractérisée en ce que l'autre élément élastique (12) est réalisé sous la forme d'un treillis en fil métallique.
  12. Couronne directrice selon l'une ou plusieurs des précédentes revendications, caractérisée en ce que les éléments élastiques (12, 19') sont balayés par de l'air froid.
  13. Couronne directrice selon la revendication 1, caractérisée en ce qu'elle est disposée dans un canal d'écoulement annulaire (5), en amont des aubes mobiles (6) d'un étage de turbine, tandis que le premier anneau et l'autre anneau (2a, 4a) sont respectivement des prolongements ou des parties constitutives des parois radialement externes ou bien radialement internes du canal d'écoulement (5).
  14. Couronne directrice selon la revendication 13, caractérisée en ce que le premier anneau (2a, 4c) relié de façon inamovible aux aubes directrices (3), est directement relié de façon inamovible à une partie de paroi radialement externe ou radialement interne (22, 22') de l'enveloppe pour le canal d'écoulement (5).
EP91909879A 1990-06-02 1991-05-28 Couronne directrice d'une turbine d'un groupe propulseur a turbine a gas Expired - Lifetime EP0485556B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE4017861A DE4017861A1 (de) 1990-06-02 1990-06-02 Leitkranz fuer eine gasturbine
DE4017861 1990-06-02
PCT/DE1991/000458 WO1991019078A1 (fr) 1990-06-02 1991-05-28 Couronne directrice d'une turbine d'un groupe propulseur a turbine a gas

Publications (2)

Publication Number Publication Date
EP0485556A1 EP0485556A1 (fr) 1992-05-20
EP0485556B1 true EP0485556B1 (fr) 1995-08-09

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP91909879A Expired - Lifetime EP0485556B1 (fr) 1990-06-02 1991-05-28 Couronne directrice d'une turbine d'un groupe propulseur a turbine a gas

Country Status (5)

Country Link
US (1) US5269651A (fr)
EP (1) EP0485556B1 (fr)
JP (1) JPH05501141A (fr)
DE (2) DE4017861A1 (fr)
WO (1) WO1991019078A1 (fr)

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EP2738356B1 (fr) * 2012-11-29 2019-05-01 Safran Aero Boosters SA Aube de redresseur de turbomachine, redresseur de turbomachine et procédé de montage associé
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Also Published As

Publication number Publication date
DE4017861C2 (fr) 1992-05-14
JPH05501141A (ja) 1993-03-04
DE59106214D1 (de) 1995-09-14
US5269651A (en) 1993-12-14
DE4017861A1 (de) 1991-12-05
WO1991019078A1 (fr) 1991-12-12
EP0485556A1 (fr) 1992-05-20

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