EP2818643B1 - Dispositif d'étanchéité et turbomachine - Google Patents

Dispositif d'étanchéité et turbomachine Download PDF

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Publication number
EP2818643B1
EP2818643B1 EP14172050.8A EP14172050A EP2818643B1 EP 2818643 B1 EP2818643 B1 EP 2818643B1 EP 14172050 A EP14172050 A EP 14172050A EP 2818643 B1 EP2818643 B1 EP 2818643B1
Authority
EP
European Patent Office
Prior art keywords
ring
sealing device
sealing
wall
downstream
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.)
Active
Application number
EP14172050.8A
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German (de)
English (en)
Other versions
EP2818643A1 (fr
Inventor
Manfred Feldmann
Thomas Hess
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
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MTU Aero Engines AG
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Publication of EP2818643A1 publication Critical patent/EP2818643A1/fr
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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F05D2230/30—Manufacture with deposition of material

Definitions

  • the invention relates to a sealing device for a turbomachine according to the preamble of patent claim 1, as for example from the WO 2009/118490 A2 is known, and a turbomachine.
  • the two stator rings conventionally have very different temperatures, so that the fish mouth seals must be designed such that resulting thermal strains are kept or reduced to an acceptable level of stress.
  • the two following constructions for forming the fishmouth seals are known:
  • the inner stator ring is formed integrally with the outer stator ring of the vane ring.
  • this construction often leads to crack formation in the hot transition region between the stator rings.
  • the inner stator ring is bolted to a forward radial flange of the vane ring.
  • the second construction shows a better behavior with respect to the thermally induced stresses in the fish mouth seal, it creates a potentially large leakage area by the arrangement of the inner stator ring on the vane ring.
  • the object of the invention is to provide a sealing device for sealing a radially inner gas channel between a vane ring and a rotor of a turbomachine such as a gas turbine, which eliminates the aforementioned disadvantages and allows a radial thermal expansion compensation.
  • a turbomachine with an improved seal of an inner gas channel between a vane ring and a rotor.
  • the sealing device has an outer radial flange for connection to the integral inner ring of the vane ring and a double-walled cylinder with an oriented in a first direction outer wall and with an oriented in an opposite direction inner wall, which are interconnected via an annular arc, wherein the radial flange in the outer wall goes over and the cylinder forms the sealing ring.
  • the inner wall passes over an annular web in at least one parallel to the first direction or the opposite direction oriented inner body portion for radially inner receiving a sealing structure, wherein the sealing device via their individual, integrally formed sections a uniform, preferably relatively small, wall thickness has, so that the sealing device is resilient within certain limits, in particular, the annular arc and the annular web act as radial spring elements.
  • the sealing device can be cohesively, for example by means of soldering, or non-positively and / or positively be connected to the vane ring.
  • the frictional connection or positive force fit, for example by means of a screw connection, is such that leakage flows in the connection region between the guide vane ring and the radial flange of the sealing device are prevented.
  • the inner wall via an annular ridge in at least one parallel to the first direction or to the opposite direction oriented inner body portion for radially inner receiving a sealing structure over.
  • the double-walled cylinder and the at least one inner body portion form a kind of three-walled cylinder.
  • the annular web is preferably relatively thin-walled.
  • the sealing ring forms a bearing element of the cylinder.
  • outer wall may extend downstream and the inner wall upstream, wherein the sealing ring is an integral portion of the outer wall.
  • the sealing device may have only one downstream body portion for receiving a sealing structure.
  • the inner wall forms the sealing ring.
  • the outer wall may for this purpose be directed upstream, whereas the inner wall is directed downstream.
  • the sealing ring is not a supporting structure of the cylinder, so that the sealing ring can have an optimally adapted to its actual sealing task geometry.
  • the sealing means may also include an upstream inner body portion and a downstream inner body portion for receiving a sealing structure. Characterized in that extends from the annular land a body portion downstream and a body portion upstream, it is loaded by the body portions substantially symmetrically or evenly.
  • the sealing device can be optimally adapted to the respective rotor and stator geometry if it is produced generatively.
  • the production costs and / or the production costs are / are reduced by the generative production, since a joining of a plurality of individual parts is eliminated.
  • the sealing structure may be integrally formed with the body portions so that it may also have an optimum shape and material structure and, moreover, need not be fixed to the sealing means in a separate assembly step.
  • a preferred turbomachine has at least one sealing device according to the invention for sealing a radially inner gas channel.
  • the sealing device can be cohesively, for example by means of soldering or non-positively and / or positively, for example by means of a screw, be connected to the inner ring of a vane ring. Due to the radial thermal expansion compensation, the inner gas channel is better sealed compared to known sealing devices for hot gas flow.
  • FIG. 1 shows a first embodiment of a sealing device 1 according to the invention for sealing a radially inner gas channel 2 between a vane ring 4 and a rotor 6 of a turbomachine such as a gas turbine and in particular an aircraft engine shown.
  • the sealing device 1 has a sealing ring 8 for forming a sealing space 10 with a rear portion of an integral inner ring 12 of the vane ring 4.
  • the sealing device 1 has for connection to the inner ring 12 an outwardly oriented radial flange 18 and the inner ring 12 has to receive the sealing device 1 an inwardly directed annular flange 20.
  • the sealing device 1 by means of a plurality of holes 22 through the radial flange 18 and the annular flange 20 guided fasteners 24 connected as screw-nut systems.
  • the radial flange 18 is pressed so strong against the annular flange 20 that no leakage current can form between them.
  • the sealing device 1 can be bonded to the inner ring 12 by material bonding, for example by means of soldering.
  • an abutment region between the radial flange 18 and the annular flange 20 is provided at an angle with an axial abutment boundary 25 and a radial abutment boundary 27.
  • the sealing device 1 has a double-walled cylinder 26, which runs approximately coaxially with the axial direction of the turbomachine in the mounted state.
  • the cylinder 26 has an outer wall 28 and an inner wall 30, which are connected to each other via an annular arc 32.
  • the cylinder 26 thus has a U-shaped or hairpin-like cross section, whereby different radial thermal expansions of the vane ring 4 to the sealing ring 8 can be compensated without excessive tension.
  • the sealing ring 8 is formed as an integral portion of the outer wall 28. Due to the Koaxiltician of the cylinder 26 of the sealing ring 8 forming portion or the sealing ring 8 extends approximately parallel to the rear portion of the inner ring 12th
  • the outer wall 28 forming the sealing ring 8 extends starting from the radial flange 18 in a first direction, as shown in FIG FIG. 1 downstream, and the inner wall 30 extends in an opposite direction, as shown in FIG FIG. 1 upstream of the main stream.
  • the inner wall 30 is arranged radially inward to the outer wall 28 and has a radially outwardly offset wall portion 34 which extends approximately to the radial height of the outer wall 28.
  • the wall portion 34 goes into a radially inwardly annular ridge 36 via, which merges into a downstream inner body portion 38.
  • the sealing device 1 has an approximately S-shaped cross-section.
  • the inner body portion 38 is disposed radially inward of the inner wall 30 and terminates short of an axial position of the annular arc 32. In the embodiment shown, it is designed stepwise and provided in its one rotor drum 39 side facing with a sealing structure or inlet structure 40.
  • the sealing structure 40 acts in combination with rotor-side sealing fins 42 as a labyrinth seal, by means of which a flow around the vane ring 4 in the region of its rotor drum 29 facing blade ends is prevented.
  • the sealing device 1 via its individual integral sections - radial flange 18, cylinder 26 with sealing ring 8, ring land 36 and inner body portion 38 - preferably a uniform wall thickness.
  • the wall thickness is relatively low, whereby the sealing means 1 is not rigid, but also has resilient or elastic properties.
  • the ring bottom 32 and the annular web 36 act as radial spring elements.
  • the radial flange 18 is located approximately centrally between an axial position of the annular web 36 and the axial position of the annular arc 32.
  • the sealing device 1 is produced generatively, for example by means of a laser sintering process or a selective laser melting process.
  • the sealing device 1 is thus preferably produced as a single part in a single process.
  • FIG. 2 a second embodiment of the sealing device 1 of a flow machine according to the invention is shown.
  • This exemplary embodiment likewise has a sealing ring 8, a radial flange 18, a double-walled cylinder 26 running coaxially in the mounted state relative to the axial direction of the turbomachine, an annular web 36 and a sealing structure 40.
  • the sealing ring 8 is not formed in this embodiment as an integral portion of the outer wall 28, but as an integral portion which extends from a free end of the inner wall 30 to the front.
  • the sealing ring 8 is provided in a stepped manner with a free peripheral edge 46 lying radially outwards relative to the inner wall 30 to a radial height of the outer wall 28.
  • the sealing ring 8 extends with its outwardly offset and the peripheral edge 46 forming annular portion 48 approximately parallel to the rear portion of the inner ring 12 of the vane ring 4th
  • the sealing device 1 in addition to an inner body portion 38 extending upstream from an annular ridge 36, an upstream extending inner body portion 50, which are provided together with a continuous sealing structure 40.
  • the sealing device 1 after FIG. 2 preferably a uniform relatively small wall thickness over its individual integral sections - radial flange 18, cylinder 26 with sealing ring 8, annular web 36 and inner body sections 38, 50 - and is thus resilient under certain limits.
  • the ring bottom 32 and the annular web 36 act as radial spring elements.
  • the radial flange 18 is located approximately centrally between an axial position of the annular arc 32 and an axial position of the free peripheral edge 46 of the sealing ring 8.
  • a front Fischmauldichtung and thus a hub-side sealing space between an upstream or front blade row and the vane ring 4 are formed.
  • the front sealing space between the inner wall portion 34 and the outer inner ring 12 may be formed, in which case the front guide blade row is immersed with a rear platform ring overhang in this front sealing space.
  • a sealing device for sealing a radially inner gas channel between a vane ring and a rotor of a turbomachine
  • the sealing device has a sealing ring for forming a sealing space with a directed towards a main flow rear portion of an integral inner ring of the vane ring into which a front platform overhang ring a immersed downstream row of blades
  • the sealing means has an outer radial flange for connection to the integral inner ring of the vane ring and a double-walled cylinder having a oriented in a first direction outer wall and with an oriented in an opposite direction inner wall, which are interconnected via a ring arc the radial flange merges into the outer wall of the cylinder and the cylinder forms the sealing ring, as well as a turbomachine.

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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 (8)

  1. Dispositif d'étanchéité (1) destiné à rendre étanche un conduit de gaz radialement intérieur (2) situé entre une couronne d'aubes directrices (4) et un rotor (6) d'une turbomachine, le dispositif d'étanchéité (1) comportant une bague d'étanchéité (8) destinée à former un espace d'étanchéité (10) avec une partie arrière, par référence à la direction d'écoulement principal, d'une bague intérieure intégrale (12) de la couronne d'aubes directrices (4), dans laquelle pénètre une bague avant (14), en porte-à-faux de plate-forme, d'une rangée d'aubes directrices aval (16) et le dispositif d'étanchéité (1) comprenant une bride radiale extérieure (18) destinée à être reliée à la bague intérieur intégrale (12) et un cylindre (26) à double paroi pourvu d'une paroi extérieure (28) orientée dans une première direction et d'une paroi intérieure (30) orientée dans une direction opposée, lesquelles sont reliées entre elles par un élément incurvé annulaire (32) à l'autre, la bride radiale (18) se transformant en la paroi extérieure (28) et le cylindre (26) formant la bague d'étanchéité (8).
    caractérisé en ce que la paroi intérieure (30) se transforme par le biais d'une nervure annulaire (36) en au moins une partie de corps intérieure (38, 50), orientée parallèlement à la première direction ou à la direction opposée, pour recevoir intérieurement et radialement une structure d'étanchéité (40),
    le dispositif d'étanchéité (1) ayant une épaisseur de paroi uniforme, de préférence relativement petite, sur ses parties individuelles formées intégralement les unes avec les autres, de sorte que le dispositif d'étanchéité (1) est élastique dans une certaine mesure, l'élément incurvé annulaire (32) et la nervure annulaire (36) agissant comme des éléments à ressort radiaux.
  2. Dispositif d'étanchéité selon la revendication 1, dans lequel la paroi extérieure (28) forme la bague d'étanchéité (8) et la paroi extérieure (28) est dirigée vers l'aval et la paroi intérieure (30) est dirigée vers l'amont.
  3. Dispositif d'étanchéité selon la revendication 2, dans lequel l'au moins une partie de corps intérieure (38) est dirigée vers l'aval lorsque l'on regarde depuis la nervure annulaire (36).
  4. Dispositif d'étanchéité selon la revendication 1, dans lequel la bague d'étanchéité (8) est formée sur la paroi intérieure (30) et la paroi extérieure (28) est dirigée vers l'amont et la paroi intérieure (30) est dirigée vers l'aval.
  5. Dispositif d'étanchéité selon la revendication 4, dans lequel une partie de corps intérieure (38) est dirigée vers l'aval lorsque l'on regarde depuis la zone annulaire (36) et une autre partie de corps intérieure (50) est dirigée vers l'aval lorsque l'on regarde depuis la zone annulaire (36).
  6. Dispositif d'étanchéité selon l'une des revendications précédentes, dans lequel la bride radiale (18) est disposée approximativement au centre du dispositif d'étanchéité (1) lorsque l'on regarde dans la direction axiale.
  7. Dispositif d'étanchéité selon l'une des revendications précédentes, dans lequel le dispositif d'étanchéité (1) est fabriqué de manière générative.
  8. Turbomachine comprenant au moins un dispositif d'étanchéité (1) selon l'une des revendications précédentes.
EP14172050.8A 2013-06-27 2014-06-12 Dispositif d'étanchéité et turbomachine Active EP2818643B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102013212480 2013-06-27

Publications (2)

Publication Number Publication Date
EP2818643A1 EP2818643A1 (fr) 2014-12-31
EP2818643B1 true EP2818643B1 (fr) 2018-08-08

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EP14172050.8A Active EP2818643B1 (fr) 2013-06-27 2014-06-12 Dispositif d'étanchéité et turbomachine

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US (1) US9664059B2 (fr)
EP (1) EP2818643B1 (fr)
ES (1) ES2684775T3 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10221859B2 (en) 2016-02-08 2019-03-05 General Electric Company Turbine engine compressor blade
EP3228826B1 (fr) * 2016-04-05 2021-03-17 MTU Aero Engines GmbH Agencement de segments d'étanchéité ayant un connecteur, moteur à turbine à gaz et procédé de fabrication associé
DE102017211316A1 (de) 2017-07-04 2019-01-10 MTU Aero Engines AG Turbomaschinen-Dichtring
DE102018201295A1 (de) 2018-01-29 2019-08-01 MTU Aero Engines AG Modul für eine strömungsmaschine
US10844745B2 (en) 2019-03-29 2020-11-24 Pratt & Whitney Canada Corp. Bearing assembly
US11492926B2 (en) 2020-12-17 2022-11-08 Pratt & Whitney Canada Corp. Bearing housing with slip joint

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Also Published As

Publication number Publication date
ES2684775T3 (es) 2018-10-04
EP2818643A1 (fr) 2014-12-31
US9664059B2 (en) 2017-05-30
US20150001811A1 (en) 2015-01-01

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