EP2881545B1 - Élément d'étanchéité, dispositif d'étanchéité et turbomachine - Google Patents

Élément d'étanchéité, dispositif d'étanchéité et turbomachine Download PDF

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Publication number
EP2881545B1
EP2881545B1 EP13195751.6A EP13195751A EP2881545B1 EP 2881545 B1 EP2881545 B1 EP 2881545B1 EP 13195751 A EP13195751 A EP 13195751A EP 2881545 B1 EP2881545 B1 EP 2881545B1
Authority
EP
European Patent Office
Prior art keywords
mounting
turbomachine
angle
securing
mounting direction
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
EP13195751.6A
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German (de)
English (en)
Other versions
EP2881545A1 (fr
Inventor
Hans Dr. Stricker
Stefan Rauscher
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 AG
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 AG filed Critical MTU Aero Engines AG
Priority to EP13195751.6A priority Critical patent/EP2881545B1/fr
Priority to ES13195751.6T priority patent/ES2628679T3/es
Priority to US14/558,415 priority patent/US9803494B2/en
Publication of EP2881545A1 publication Critical patent/EP2881545A1/fr
Application granted granted Critical
Publication of EP2881545B1 publication Critical patent/EP2881545B1/fr
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Anticipated expiration legal-status Critical

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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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • 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

Definitions

  • the invention relates to a turbomachine according to the preamble of claim 1.
  • turbomachines such as gas turbines and aircraft engines
  • radial gaps between rotor-side blade rows and housing rows surrounding rotor blade rows are regularly sealed or reduced by means of a sealing device.
  • the sealing device is composed of a plurality of sealing elements or ring segments, each having at least one inlet or Anstreifbelag which is attached to a stationary with the housing portion in operative engagement support structure.
  • Known support structures have at least one dimensionally stable holding element, which is arranged in the mounted state of the turbomachine between two axially screwed together sections of the housing portion.
  • the support structures may each have a backup, which may also be referred to as mounting or securing position.
  • the patent EP-2357322 discloses, for example, a seal assembly wherein the support structure is secured in its desired position.
  • a fuse and at least one holding element are arranged one behind the other, wherein the fuse has a latching portion with an assembly angle in the mounting direction employed mounting surface and an employee employed in the opposite direction by a safety angle backup surface.
  • the safety angle is chosen such that a high holding force is achieved.
  • the mounting bracket is adjusted according to the safety angle, so that for mounting the support structure a correspondingly large mounting force must be applied, which can lead to a plastic deformation or deformation of the fuse.
  • the object of the invention is to provide a sealing element of a turbomachine, which eliminates the aforementioned disadvantages and in particular allows easy installation and a reliable position assurance during assembly. Furthermore, it is an object of the invention to provide a sealing device which is easy to assemble and disassemble in a turbomachine, and to provide a turbomachine whose at least one sealing device is held securely on a housing section during assembly or transport.
  • a sealing element according to the invention of a turbomachine for adjusting a radial gap between a blade row and a housing region has a support structure with a front side, to which an inlet lining is attached, and a rear side, is arranged on the at least one dimensionally stable holding element for holding the support structure in a desired position on the housing portion.
  • the support structure has a fuse for securing the support structure in its desired position during assembly or transport.
  • the at least one retaining element and the fuse are arranged one behind the other in the mounting direction, wherein the fuse has a latching section with a mounting surface engaged by a mounting bracket in the mounting direction and a backup surface engaged by a safety angle in the opposite direction.
  • the latching section is also mounted elastically on the rear side via a spring section.
  • the mounting angle is smaller than the safety angle.
  • the fact that the mounting bracket is smaller than the safety angle can be achieved on the one hand a simple installation and on the other a high securing effect and thus a reliable position assurance during assembly.
  • the mounting angle and the safety angle are independent of each other and thus to their respective function - low assembly force or high holding force - optimally adaptable. Damage to the support structure due to an excessive mounting angle is excluded.
  • the mounting of the sealing element on the housing region can be made particularly easily if the at least one retaining element has a holding section extending in the mounting direction for forming a sliding engagement with a corresponding receptacle of the turbomachine.
  • the support structure can be transferred by a linear movement in its desired position.
  • the spring section allows an automatic deflection of the locking portion in a second direction and thus an automatic locking.
  • a further holding element may be provided, wherein the locking portion is preferably then arranged between the holding elements, wherein the further holding element can form a sliding engagement in the mounting direction with a corresponding receptacle of the turbomachine. Due to the sliding engagement of the second holding element in the mounting direction, both holding elements are simultaneously brought into operative engagement with the respective housing receptacle by a linear movement.
  • the spring portion is a profile with two legs arranged one above the other, with respect to a machine longitudinal axis of the turbomachine, outer or radially outer leg merges into the latching portion and the inner or radially inner leg merges into a fastened to the rear mounting portion.
  • a spring portion allows a large deflection or elasticity of the locking portion and is easy to manufacture.
  • Exemplary profiles with two legs are U-profiles, V-profiles and W-profiles.
  • To increase the spring action of the inner leg may be employed by an angle in the mounting direction.
  • the employment causes a change in the mounting bracket during mounting and the safety angle at a load in demounting direction. By this employment, the mounting force can be further reduced.
  • the outer leg preferably extends in the mounting direction and is thus not employed in the mounting direction.
  • the two legs are similar to one asymmetric U-profile to each other employed, which has a positive effect on the reduction of the mounting force and increase the holding force.
  • the mounting angle is smaller by at least 10 °, preferably by 20 ° to 30 °, smaller than a minimum securing angle.
  • the minimum securing angle is the smallest possible safety angle and depends essentially on the coefficient of friction between the housing section and the securing surface.
  • a disassembly of the sealing element can be simplified if the spring section is arranged in front of the latching section in the mounting direction and the latching section merges in the mounting direction in a rear free end portion.
  • the free end portion is arranged in the front dismounting direction and thus freely accessible during disassembly. In this way, for example, with a tool a radially outwardly inwardly directed compression force can be introduced into the spring portion and a radial overlap of the fuse element side backup surface can be reduced with the housing-side support surface.
  • a sealing device according to the invention of a turbomachine has a plurality of sealing elements according to the invention. Such a sealing device can be mounted without damage and is reliably secured during assembly in its desired position.
  • a turbomachine according to the invention has at least one sealing device according to the invention.
  • the turbomachine is characterized by an optimal radial gap in the area of the sealing device, since it is mounted without damage and also in its desired position.
  • FIG. 1 a first embodiment of a sealing element 1 according to the invention is shown in section along a machine longitudinal axis of a turbomachine.
  • the machine longitudinal axis extends in the axial direction.
  • Directional data such as axial or radial refer to the machine longitudinal axis.
  • Directional information such as upstream and downstream or location information such as front and rear, refer to the flow direction of a hot gas flowing through the turbomachine. If directional information and / or location information refer to a mounting direction or disassembly direction, this is explicitly mentioned.
  • the turbomachine is, for example, a gas turbine and in particular an aircraft engine.
  • the sealing element 1 is a ring segment of a sealing device, which is arranged here in a turbine-side housing portion 2 of the turbomachine. In principle, the sealing element 1 can also be arranged on the compressor side.
  • the sealing element 1 or the sealing device consisting of at least one sealing element serves for adjusting and in particular reducing a radial gap between the housing region 2 and a blade row 4 encompassed by the housing region 2.
  • the blade row 4 is arranged to rotate about the machine longitudinal axis in an annular space 6.
  • the annular space 6 is flowed through by the hot gas substantially in the direction of the machine longitudinal axis and here axially from left to right.
  • the housing portion 2 is here composed of two housing sections 8, 10 with annular flanges, which are screwed together as indicated by the dot-dash line 12 in the region of their annular flanges.
  • the housing sections 8, 10 themselves can be subdivided into a lower half and an upper half, which are or are joined in a horizontal plane.
  • the front housing section 8 has a receptacle 14 for interacting with a rear dimensionally stable holding element 16 of the sealing element 1.
  • the receptacle 14 is designed for this purpose as an axial projection extending in the flow direction with a radial contact surface 17.
  • the rear housing portion 10 has an axial circumferential wall 18 extending downstream from the annular flange and a radially inwardly extending annular wall 20 from the peripheral wall 18 downstream of the annular flange.
  • the peripheral wall 18 has such a length or axial extent that in the assembled state of the sealing element 1 or the sealing device between the rear retaining element 16 and the annular wall 20, an axial gap is formed.
  • the annular wall 20 here has such a radial extent or height that it extends slightly radially inwardly beyond the receptacle 14 addition.
  • the sealing element 1 has an inlet or Anstreifbelag 21, which is arranged opposite to each other in the flow direction arranged circumferentially sealing webs 22, 24 of the blade row 4.
  • the sealing element 1 has a supporting structure 26.
  • the supporting structure 26 and the inlet lining 21 are metallic.
  • the inlet lining 21 and the support structure 26 are manufactured separately from each other and added later.
  • the inlet lining 21 can also be manufactured integrally with the supporting structure 26. This can be done, for example, by means of a generative manufacturing process such as laser sintering or a laser melting process and enables the production of the sealing element 1 as a closed ring and thus as a one-piece sealing device.
  • the support structure 26 has an axial base portion 28 and a radially disposed wall portion 30 disposed upstream of the base portion 28.
  • the base section 28 has a hot gas side or annular space side front 32, on which the inlet lining 21 is arranged, and an opposite cooling air side or the housing portion 2 facing rear 34.
  • the back 34 is provided with the rear support member 16, with the housing-side receptacle 14th interacts.
  • the rear support member 16 is here S-shaped with an attached at the back 34 axial leg portion 36, a radially extending from the foot portion 36 radially outwardly web 38 and an upstream of the web 38 extending axial head or holding portion 40th
  • the holding section 40 has in particular an upstream extending in the direction of the annular space 6 facing contact surface 42 for cooperation with the contact surface 17 of the receptacle 14th
  • a front dimensionally stable support member 44 which extends axially upstream of the Wandungsabitess 30 and cooperates with a corresponding stator-side receptacle 46.
  • the front retaining element 44 has an axially extending front-side radial contact surface 48 which cooperates with an axially extending abutment surface 49 of the receptacle 46.
  • the stator-side receptacle 46 is, for example, a rear platform region of an upstream row of guide vanes.
  • the support structure 26 has a fuse 50.
  • the sealing element 1 or the sealing device with its retaining elements 16, 44 in sliding engagement with the receptacles 14, 46, the sliding engagements can be solved by a sufficiently strong disassembly movement in the opposite direction 47, however.
  • a self-release of the sealing member 1 from the front housing portion 8 is prevented due to the fuse 50.
  • this means that the sealing element 1 or the sealing device is secured to the front housing section 8 in its desired position even when the rear housing section 10 is not yet bolted to the front housing section 8.
  • the fuse 50 extends from the rear side 34 between the holding elements 16, 44 and cooperates with a housing-side holding surface 52.
  • the holding surface 52 is an inclined surface that is disposed opposite to receiving the rear holding member 16 on the front housing portion 8 and extending between a radially inner peripheral surface 54 and an upstream radially outer circumferential surface 56 of the front housing portion 8. It thus extends obliquely in the mounting direction 57.
  • the fuse 50 has a latching portion 58 which is connected via a spring portion 60 and a mounting portion 62 on the back 34.
  • the mounting angle .alpha. is smaller than the securing angle .beta. Or .beta the securing angle ⁇ is greater than the mounting angle ⁇ .
  • the backup surface 66 is in the assembled state in abutment with the housing-side holding surface 52.
  • the holding surface 52 is therefore preferably employed by an angle not sketched in the mounting direction, which is equal to the safety angle ⁇ in the opposite direction, ie in the mounting direction 57.
  • the mounting direction 57 is an axial upstream movement.
  • the opposite direction 47 or dismounting direction is thus an axial downstream movement.
  • the spring portion 60 is a longitudinally section in approximately asymmetrical U-shaped profile with a radially inner leg 68, a radially outer leg 70 and a leg 68, 70 interconnecting arc section 72.
  • the inner leg 68 goes with its front end in the mounting portion 62 on which is connected to a large area on the back 34.
  • the inner leg 68 is hired in the mounting direction by an angle of attack ⁇ and merges with its rear end in the arc section 72.
  • the outer leg 70 extends in the mounting direction and connects the arcuate portion 72 with the locking portion 58 located upstream of the arc portion 72.
  • the housing sections 8, 10 are separated from each other.
  • the sealing element 1 is brought in the mounting direction, ie against the flow direction, from back to front by an axial sliding movement into sliding engagement with the front housing section 8.
  • the front retaining element 44 is pushed with its contact surface 48 along the rear platform region 46 of the upstream guide blade row and the rear retaining element 16 is pushed with its contact surface 42 along the axial projection 14.
  • the fuse 50 runs with its mounting surface 64 on the axial projection 14.
  • the fuse 50 Due to the spring action of the spring portion 60, the fuse 50 is elastically compressed from its original shape and / or elastically twisted around the transition region 74 between the inner leg 68 and the attachment portion 62 and the latch portion 58 is moved along the inner peripheral surface 54 of the front housing portion 8, until it returns to its original shape after passing the inner peripheral surface 58 and is in abutment with the support surface 52 with its mounting surface 64.
  • the holding elements 16, 44 are in sliding engagement with the receptacles 14, 46 and the fuse 50 lies with its locking surface 66 flat against the support surface 52.
  • the sealing element 1 is thus secured in the desired position against falling out. Due to the small mounting angle ⁇ only a small axial mounting force is necessary for installation. Due to the large safety angle ⁇ , however, a large axial holding force is achieved, so that on the one hand a reliable self-locking is achieved.
  • the employment of the inner leg 68 reinforces the respective effect. That is, the mounting angle ⁇ is further reduced by the employment of the inner leg 68 during insertion.
  • the front housing section 8 can now be transported, for example, without the risk that the sealing element 1 leaves its desired position on the front housing section 8.
  • the rear housing section 8 thus does not have to be screwed to the front housing section 8 immediately after assembly of the sealing element 1 or the sealing device in order to prevent a change in position of the sealing element 1.
  • the mounting angle ⁇ is at least 10 °, more preferably 20 ° to 30 °, smaller than a minimum securing angle.
  • the minimum securing angle is the smallest possible securing angle ⁇ and substantially dependent on the coefficient of friction between the holding surface 52 and the securing surface 66.
  • FIG. 2 a second embodiment of a sealing element 1 according to the invention is shown in section along a machine longitudinal axis of a turbomachine.
  • the spring portion 60 of the fuse 50 In contrast to the first embodiment according to FIG. 1 is the spring portion 60 of the fuse 50 at its according to the view in FIG. 2 Vertical axis arranged rotated 180 ° and positioned upstream of the latching portion 58.
  • the spring portion 60 is arranged almost inverted.
  • the arcuate portion 72 is disposed upstream of the radially inner leg 68 and upstream of the radially outer leg 70.
  • the orientation of the locking portion 58 has not changed, so that due to the reorientation of the spring portion 60 of the radially outer leg 70 now merges into the mounting surface 64 and not in the locking surface 66 of the locking portion 58.
  • the spring portion 60 is in the mounting direction arranged in the latching portion 58 and in the dismounting direction of the spring portion 60 is disposed behind the latching portion 58. Due to the changed orientation of the spring portion 60, a position of the pitch angle ⁇ of the inner leg 68 has also changed.
  • the latching portion 58 downstream transitions into an axially extending rear free end portion 76 which is radially spaced in the mounted state of the sealing element 1 from the opposite radially inner peripheral surface 54 of the front housing portion 8.
  • the radial spacing creates a receiving space 78 for, for example, a disassembling tool, by means of which, in cooperation with the free end section 76, a compression force directed radially inwardly from the outside toward the lock 50 is introduced.
  • a tool such as a screwdriver, is inserted into the receiving space 78.
  • the tool is brought into abutment with the free end portion 76 and moved radially from outside to inside, whereby the compression force is introduced into the fuse 50, which is such that the spring portion 60 is compressed and thus the coverage of the backup surface 66 with the support surface 52nd the housing portion 8 is reduced, so that the sealing element 1 can be removed simplified in the axial direction.
  • a sealing element for positioning in a turbomachine, wherein for self-assurance of the sealing element in a mounting position whose support structure has a fuse which has a resilient latching portion, the mounting surface is employed at a smaller angle in the mounting direction as a backup surface in the opposite direction, a sealing device, as well a turbomachine.

Claims (8)

  1. Turbomachine comportant un élément d'étanchéité (1) pour régler un intervalle radial entre une série de pales (4) et une zone de boîtier (2), avec une structure portante (26), sur sa face avant (32), une garniture d'entrée (21) et, sur sa face arrière (34), au moins une élément de retenue de forme stable (16) pour retenir la structure portante (26) en position de consigne, dans laquelle, à cet effet, le au moins un élément de retenue de forme stable (16) est agencé, à l'état monté de la turbomachine, entre deux sections (8, 10) vissées l'une à l'autre de la zone de boîtier (2), et une sécurité (50) pour fixer la structure portante (26) dans sa position de consigne est agencée au cours du montage ou du transport de la turbomachine non encore finie, c'est-à-dire alors que les sections de boîtier (8, 10) ne sont pas vissées, dans laquelle le au moins un élément de retenue (16) et la sécurité (50) sont agencés l'un derrière l'autre dans la direction de montage (57) et la sécurité (50) présente une section d'encliquetage (58) avec une surface de montage (64) réglée selon un angle de montage (α) dans la direction de montage (57) et une surface de sécurité (66) réglée selon un angle de sécurité (β) dans la direction contraire, et dans laquelle la section d'encliquetage (58) est montée de manière élastique sur une section à ressort (60), caractérisée en ce que l'angle de montage (α) est plus petit que l'angle de sécurité (β).
  2. Turbomachine selon la revendication 1, dans laquelle le au moins un élément de retenue (16) a une section de retenue (40) s'étendant dans la direction de montage pour former une prise coulissante avec un logement correspondant (14) de la turbomachine.
  3. Turbomachine selon la revendication 1 ou 2, dans laquelle la section d'encliquetage (58) est agencée entre deux éléments de retenue (16, 44) et l'on peut former au moyen du second élément de retenue (44) une prise coulissante dans la direction de montage (57) avec un logement correspondant (46) de la turbomachine.
  4. Turbomachine selon la revendication 1, 2 ou 3, dans laquelle la section à ressort (60) est un profilé avec deux branches (68, 70) agencées l'une au-dessus de l'autre, dans laquelle la branche externe (70) se fond dans la section d'encliquetage (58) et la branche interne (68) se fond dans une section de fixation (62) liée à la face arrière (34).
  5. Turbomachine selon la revendication 4, dans laquelle la branche interne (68) est réglée selon un angle de réglage (γ) dans la direction de montage (57).
  6. Turbomachine selon la revendication 4 ou 5, dans laquelle la branche externe (70) s'étend dans la direction de montage (57).
  7. Turbomachine selon l'une quelconque des revendications précédentes, dans laquelle l'angle de montage (α) est inférieur d'au moins 10°, de préférence de 20° à 30°, à un angle de sécurité minimal.
  8. Turbomachine selon l'une quelconque des revendications 4 à 7, dans laquelle la section à ressort (60) est agencée devant la section d'encliquetage (58) dans la direction de montage et la section d'encliquetage (58) se fond dans une section d'extrémité arrière libre (76) dans la direction de montage.
EP13195751.6A 2013-12-04 2013-12-04 Élément d'étanchéité, dispositif d'étanchéité et turbomachine Active EP2881545B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP13195751.6A EP2881545B1 (fr) 2013-12-04 2013-12-04 Élément d'étanchéité, dispositif d'étanchéité et turbomachine
ES13195751.6T ES2628679T3 (es) 2013-12-04 2013-12-04 Elemento de estanqueidad, dispositivo de estanqueidad y turbomáquina
US14/558,415 US9803494B2 (en) 2013-12-04 2014-12-02 Sealing element, sealing unit, and turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13195751.6A EP2881545B1 (fr) 2013-12-04 2013-12-04 Élément d'étanchéité, dispositif d'étanchéité et turbomachine

Publications (2)

Publication Number Publication Date
EP2881545A1 EP2881545A1 (fr) 2015-06-10
EP2881545B1 true EP2881545B1 (fr) 2017-05-31

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EP13195751.6A Active EP2881545B1 (fr) 2013-12-04 2013-12-04 Élément d'étanchéité, dispositif d'étanchéité et turbomachine

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US (1) US9803494B2 (fr)
EP (1) EP2881545B1 (fr)
ES (1) ES2628679T3 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017211316A1 (de) 2017-07-04 2019-01-10 MTU Aero Engines AG Turbomaschinen-Dichtring
US11898450B2 (en) * 2021-05-18 2024-02-13 Rtx Corporation Flowpath assembly for gas turbine engine

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US3730640A (en) * 1971-06-28 1973-05-01 United Aircraft Corp Seal ring for gas turbine
US4053254A (en) * 1976-03-26 1977-10-11 United Technologies Corporation Turbine case cooling system
US4303371A (en) * 1978-06-05 1981-12-01 General Electric Company Shroud support with impingement baffle
DE3316535A1 (de) * 1983-05-06 1984-11-08 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Turboverdichter mit einlaufbelag
GB2226365B (en) * 1988-12-22 1993-03-10 Rolls Royce Plc Turbomachine clearance control
GB2313161B (en) * 1996-05-14 2000-05-31 Rolls Royce Plc Gas turbine engine casing
US6120242A (en) * 1998-11-13 2000-09-19 General Electric Company Blade containing turbine shroud
US6652226B2 (en) * 2001-02-09 2003-11-25 General Electric Co. Methods and apparatus for reducing seal teeth wear
DE10122464C1 (de) * 2001-05-09 2002-03-07 Mtu Aero Engines Gmbh Mantelring
US7291946B2 (en) * 2003-01-27 2007-11-06 United Technologies Corporation Damper for stator assembly
US8079807B2 (en) * 2010-01-29 2011-12-20 General Electric Company Mounting apparatus for low-ductility turbine shroud
ES2581511T3 (es) * 2013-07-15 2016-09-06 Mtu Aero Engines Gmbh Turbomáquina, segmento de sellado y segmento de álabe de guía

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Also Published As

Publication number Publication date
ES2628679T3 (es) 2017-08-03
US20150152742A1 (en) 2015-06-04
US9803494B2 (en) 2017-10-31
EP2881545A1 (fr) 2015-06-10

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