EP3517734A1 - Module d'étanchéité pour une turbomachine - Google Patents

Module d'étanchéité pour une turbomachine Download PDF

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Publication number
EP3517734A1
EP3517734A1 EP19152157.4A EP19152157A EP3517734A1 EP 3517734 A1 EP3517734 A1 EP 3517734A1 EP 19152157 A EP19152157 A EP 19152157A EP 3517734 A1 EP3517734 A1 EP 3517734A1
Authority
EP
European Patent Office
Prior art keywords
module
seal
seal carrier
wall
sealing
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.)
Withdrawn
Application number
EP19152157.4A
Other languages
German (de)
English (en)
Inventor
Christoph Lauer
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
Publication of EP3517734A1 publication Critical patent/EP3517734A1/fr
Withdrawn legal-status Critical Current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
    • 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
    • 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
    • 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
    • F05D2230/31—Layer deposition
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals

Definitions

  • the present invention relates to a module for a turbomachine.
  • turbomachine may, for example.
  • the turbomachine is divided into compressor, combustion chamber and turbine.
  • the turbomachine is divided into compressor, combustion chamber and turbine.
  • sucked air is compressed by the compressor and burned in the downstream combustion chamber with added kerosene.
  • the resulting hot gas a mixture of combustion gas and air, flows through the downstream turbine and is thereby expanded.
  • the turbine also proportionally extracts energy from the hot gas in order to drive the compressor.
  • the turbine and the compressor are i.d.R. each constructed in multiple stages, with one stage each having a guide and a blade ring. In the case of the turbine in each case the blade ring is arranged downstream of the guide vane ring.
  • the subject of the present invention is a module with a vane assembly and a seal carrier.
  • the vanes of the vane assembly extend radially between a radially outer outer platform and a radially inner inner platform.
  • the seal carrier is arranged radially inside this inner platform, it forms part of the so-called Inner Air Seal (IAS).
  • IAS Inner Air Seal
  • the seal carrier helps to reduce or avoid gas losses, which is advantageous for the efficiency of the turbomachine. It should flow as much as possible or as far as possible the entire fluid or gas through the gas duct of the turbomachine.
  • the present invention is based on the technical problem of specifying a particularly advantageous module for a turbomachine.
  • Its seal carrier has a sealing ridge, which forms a labyrinth seal.
  • the sealing web is arranged on a seal carrier wall, which in turn extends radially. From this away, the sealing bar extends either axially forward (upstream, based on the gas in the gas channel) or axially behind (downstream).
  • the labyrinth seal forms the sealing ridge together with the inner platform of the vane assembly and additionally, depending on either the inner platform of an immediately upstream or an immediately downstream blade arrangement, cf. also the axial section according to Fig. 2 for illustration.
  • the seal carrier wall and the seal stay are / are jointly constructed generatively; they are as a generatively constructed part in one piece with each other, so not non-destructively separable from each other.
  • the production of seal carrier wall and sealing bar is based on a data model by selective selective solidification of a previously informal or form-neutral substance (see below in detail), which is also referred to as 3D printing.
  • the seal carrier wall as a casting and the sealing ridge as a metal sheet, and a subsequent bonding, such as by riveting
  • the generative production can already help reduce effort and costs.
  • the one-piece design according to the invention can also be advantageous in terms of durability or reliability. The inventors have found that vibrations can be coupled into a corresponding rivet via the sealing web, which can result in material fatigue. The rivet / rivet head or the sealing bar could then loosen and cause considerable damage.
  • the sealing web has considered its axial extent in an axial section, but need not necessarily extend exclusively axially. A proportional extension in addition in the radial direction may even be preferred, the sealing web can therefore be inclined to the longitudinal axis of the module and / or be provided with steps, see. also the embodiment for illustration. With a corresponding shaping, the sealing web can on the one hand be optimized for the functionality "labyrinth seal", on the other hand the generative production advantageously making a variety of geometries accessible.
  • the gasket carrier wall also generally does not have to extend exclusively radially in the axial section. However, this is preferred, the seal carrier wall thus preferably extends perpendicular to the longitudinal axis of the module. As far as the extent of, for example, the seal carrier wall or the sealing web is described in general terms, this refers to the areal extent of the respective component or area, so that the respective thickness is not taken into account insofar. For illustration: In Fig. 2 the seal carrier wall has its surface extension in the radial direction, the thickness is taken axially.
  • axial or “axial direction” refer to the longitudinal axis of the module, that is to say the longitudinal axis of the turbomachine.
  • this longitudinal axis may coincide with a rotational axis about which the blades associated with the vane assembly rotate during operation.
  • Ring refers to the perpendicular to the longitudinal axis pointing away radial directions
  • the “circulation or the” direction of rotation refer to a rotation about the longitudinal axis have the longitudinal axis of the module-containing cutting plane
  • the described components or areas have Of course, in addition an extension in the direction of rotation, in this regard, a rotationally or rotationally symmetrical structure may be preferred.
  • the seal carrier may also have another sealing ridge, which is even preferred (see below).
  • a plurality of sealing webs are also conceivable, which extend axially away from the seal carrier wall in the same direction (to the front or to the rear), but are radially offset relative to one another.
  • a sealing strip is provided on the remaining seal carrier according to the axial front and a sealing web extending axially rearward, more preferably exactly one in each case.
  • the sealing ridge has a varying thickness over its axial extent.
  • the thickness of the sealing web is taken perpendicular to its surface extension;
  • the sealing bar can not only be formed with steps, etc., but, for example, be locally thickened and / or thinned.
  • this varying thickness is implemented in detail, for example, as a result of structural or vibratory mechanical simulations, it may result in minimizing or suppressing natural frequency excitations with the varying thickness.
  • one or more local thickenings may be provided.
  • a corresponding shaping which is made possible by the generative production, can thus for example help to reduce a load profile (vibration coupling) discussed at the beginning in the context of rivet failure.
  • the seal carrier wall has a varying thickness over its radial extent.
  • the thickness is taken perpendicular to the surface extension of the seal carrier wall, in the case of the longitudinal axis preferably perpendicular to the seal carrier wall in the axial direction.
  • the thickness can be adjusted on the basis of structural mechanical simulations or optimizations depending on the force input. For example, the thickness may increase over at least a portion from radially outside to radially inside.
  • the seal carrier preferably takes over not only a sealing, but also a mechanical support function.
  • the guide vane assembly on one or more guide pins, which are arranged radially opposite to the inside of the guide vanes on the inner platform. These guide pins form a so-called. Spacing centering and engage in a radially outwardly open receptacle of the seal carrier, which is bounded axially by the seal carrier wall.
  • a slider is arranged, on which the guide pin or rest in the direction of rotation.
  • this slider is formed integrally with the seal carrier wall, namely, the two are generative together generative.
  • This may be advantageous insofar as the sliding body then does not have to be manufactured / fixed separately as an integral part, that is to say that riveting is also not necessary at this point, for example. If, however, a separate slider placed in the limited by the seal carrier wall recording, he must usually have some undersize (so that it can be brought between the or the seal carrier walls in its mounting position). When riveting itself, the walls are then slightly compressed axially before closing the rivet, which in turn can result in an initial stress of the rivet after removal of the riveting tool (bias by spring effect of the seal carrier walls). This problem can be prevented by the one-piece design.
  • the first guide pin engages around the slider with respect to the direction of rotation together with a second guide pin.
  • the slider is thus held circumferentially between the guide pin, which is why this arrangement is also referred to as Tang ("pliers").
  • the guide pin and the slider can still slide radially together.
  • the two guide pins find their respective system on circumferentially opposite side surfaces of the slider, the arrangement represents a spoke centering.
  • the seal carrier wall forms in a preferred embodiment, together with a further seal carrier wall in an axial section considered a U-profile.
  • the Seal carrier walls which are also referred to as bulkhead walls, preferably have their areal extent radially and in the direction of rotation, axially their respective thickness is taken.
  • the seal carrier walls are parallel to each other and each perpendicular to the longitudinal axis (based on their areal extent).
  • the slider is integrally formed with two seal carrier walls.
  • the slider could also be provided only one piece with one of the seal carrier walls, the other seal carrier wall could then, for example, be designed as a sheet metal.
  • the two seal carrier walls could also be produced in each case generatively and thus be multi-piece to each other.
  • the seal carrier on a further sealing ridge which extends axially opposite to the first sealing ridge.
  • the sealing webs are arranged on the same seal carrier wall, that is, a sealing ridge on the front side and the other on the rear side (in each case relative to the axial direction).
  • a sealing web is arranged on the axially front wall and extends axially forwardly and the other sealing web is arranged on the axially rear wall and extends axially rearward.
  • the further sealing web is integral with the corresponding seal carrier wall, so the two are so generative together.
  • the entire unit of the two seal carrier walls, on each of which a sealing web is arranged, is generatively constructed together generatively (ie in the same process).
  • the seal carrier has a sealing element radially inward.
  • This can in general, for example. Also separately prepared and attached to the seal carrier, such as in the case of a so-called. Brush seal. Regardless of the design in detail seals the radially inwardly arranged Seal member then to a sealing structure, which rotates in operation together with the shaft or the blades.
  • the sealing element is provided as a so-called honeycomb seal, that is to say it has a honeycomb shape in the radial direction.
  • a sealing element is also referred to as inlet lining.
  • the sealing element in particular the honeycomb seal, is provided integrally with the seal carrier wall, namely together with it generatively constructed. Particularly preferred may therefore be a completely integral, so generatively constructed overall seal carrier.
  • the inlet lining does not have to have a honeycomb shape in the strictly mathematical sense, but the degrees of freedom of the generative production can also be used in this respect for adapting or optimizing the shape.
  • the invention also relates to a turbomachine with a module disclosed herein.
  • the module is generally preferably a turbine module or section of the turbine.
  • the invention also relates to a method for producing a module disclosed herein, wherein the seal carrier wall and the sealing ridge are generatively constructed together.
  • the two are thus produced generatively in the same process.
  • the other parts discussed above slidinger, etc.
  • the entire seal carrier is produced generatively (all parts in the same process).
  • the generative building is carried out in a preferred embodiment in a powder bed process.
  • the corresponding material for example titanium aluminide, is thus applied sequentially in powder form, layer by layer, wherein each layer selectively solidifies a predetermined region on the basis of the data model (the component geometry).
  • the solidification is carried out by melting by means of a beam source, wherein in general, for example, an electron beam source is conceivable. Prefers If you melt with a laser source, ie a laser beam, then generative building is a selective laser melting (SLM).
  • SLM selective laser melting
  • Fig. 1 shows a turbomachine 1 in a schematic view, specifically a jet engine.
  • the turbomachine 1 is functionally divided into compressor 1a, combustion chamber 1b and turbine 1c.
  • both the compressor 1a and the turbine 1c are each constructed of several stages, each stage is composed of a guide and a blade ring.
  • the blade ring is arranged downstream of the associated stator blade ring. In operation, the blades rotate about the longitudinal axis 2.
  • Fig. 2 shows as a module 20 a section of the turbine 1c, again in an axial section.
  • a vane assembly 21 with a vane 21a, an inner platform 21b, as well as a first and a second guide pin 21c, d can be seen.
  • the vane 21a is disposed radially outward on the inner platform 21b, the guide pins 21c, d radially inward.
  • the guide pins 21c, d extend radially inward into a receptacle 22, which forms the seal carrier 23.
  • the receptacle 22 is bounded axially between a front seal support wall 23a and a rear seal support wall 23b of the seal carrier 23; the two walls 23a, b of the seal carrier 23 form in the axial section a radially outwardly open U-profile.
  • the seal carrier 23 has a sealing element 23f, namely a honeycomb seal.
  • the guide pins 21c, d are held axially in position between the walls 23a, b, but still radially displaceable, so not clamped.
  • the sectional plane of the axial section is according to Fig. 2 circumferentially between the two guide pins 21c, d.
  • the following is therefore supplementary to Fig. 3 Reference is made, from which it is apparent how the guide pins 21c, d (indicated by dashed lines) relative to a circumferential direction 35 together enclose a slider 23c.
  • This arrangement also referred to as Tang , forms the so-called spoke centering, which still allows a certain radial offset (to compensate for differently sized thermally induced expansion during operation).
  • the guide pins 21c, d so to speak forked together, which in the section according to Fig. 2 can be seen.
  • Fig. 3 shows a sectioned axial view, the cutting plane is perpendicular to the longitudinal axis 2 and divides the receptacle 22 in the center.
  • the front wall 23a is out of the plane of the drawing, the view is incident on the rear wall 23b of the seal carrier 23.
  • the slider 23c is integrally formed with the seal support walls 23a, b, namely built up together therewith in a powder bed process by SLM.
  • the sealing webs 23d, e each form a labyrinth seal.
  • the labyrinth seal is formed together with a trailing edge portion 30 of the inner platform of the upstream blade ring; in the case of the axially rearward seal land 23e together with a leading edge portion 31 of the inner platform of the downstream blade ring.
  • the trailing edge or leading edge portion 30, 31 is arranged radially between the respective sealing web 23d, e and the inner platform 21b of the vane assembly 21, this structure is also referred to as "Fischmauldichtung".
  • the sealing element 23f seals against sealing structures 32 which rotate together with the shaft or blades.
  • This arrangement with the seal carrier 23 is also referred to as inner air seal . Overall, this allows radial losses from the hot gas duct to be reduced or suppressed.
  • the seal carrier walls 23a, b have a varying thickness over their radial extent (increasing from radially outward to radially inward). This varying thickness, which can be implemented well due to the generative production, is adapted to the introduction of force (using structural mechanical simulations).
  • the thickness of the axially rear sealing web 23e varies. The thickness first decreases away from the seal support wall 23b, then the seal land 23e is locally formed with a thickening 23ee. This thickening 23ee serves to detune, thus suppressing critical natural frequency excitations.
  • the axially front sealing ridge 23d may be formed with variable thickness, which is not shown in detail.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP19152157.4A 2018-01-29 2019-01-16 Module d'étanchéité pour une turbomachine Withdrawn EP3517734A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102018201295.4A DE102018201295A1 (de) 2018-01-29 2018-01-29 Modul für eine strömungsmaschine

Publications (1)

Publication Number Publication Date
EP3517734A1 true EP3517734A1 (fr) 2019-07-31

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP19152157.4A Withdrawn EP3517734A1 (fr) 2018-01-29 2019-01-16 Module d'étanchéité pour une turbomachine

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US (1) US10844737B2 (fr)
EP (1) EP3517734A1 (fr)
DE (1) DE102018201295A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2606552B (en) * 2021-05-13 2023-11-22 Itp Next Generation Turbines S L Sealing system for gas turbine engine
DE102022124401A1 (de) * 2022-09-22 2024-03-28 MTU Aero Engines AG Modul für eine strömungsmaschine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1148209A2 (fr) * 2000-04-19 2001-10-24 Rolls-Royce Deutschland Ltd & Co KG Configuration de joint inter-étages
EP2360352A2 (fr) * 2010-02-12 2011-08-24 Rolls-Royce Deutschland Ltd & Co KG Joint d'étanchéité sans vis d'une turbine à gaz
EP2722486A1 (fr) * 2012-10-17 2014-04-23 MTU Aero Engines GmbH Support d'étanchéité pour ensemble statorique
EP3109520A1 (fr) * 2015-06-24 2016-12-28 MTU Aero Engines GmbH Support d'étanchéité, stator et turbomachine

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DE2861779D1 (en) * 1977-07-07 1982-06-24 Ciba Geigy Ag Cyclic aromatic diesters of phosphonous acid and the organic materials stabilized by them
GB2110768A (en) * 1981-12-01 1983-06-22 Rolls Royce Fixings for stator vanes
US5351971A (en) * 1993-05-21 1994-10-04 Eg&G Sealol, Inc. Brush seal device having a floating backplate
DE102006016147A1 (de) 2006-04-06 2007-10-11 Mtu Aero Engines Gmbh Verfahren zum Herstellen einer Wabendichtung
DE102012201050B4 (de) * 2012-01-25 2017-11-30 MTU Aero Engines AG Dichtungsanordnung, Verfahren sowie Strömungsmaschine
WO2014158600A1 (fr) 2013-03-14 2014-10-02 United Technologies Corporation Ensemble d'encliquetage pour carter de compresseur
DE102013209746B4 (de) * 2013-05-27 2014-12-18 MTU Aero Engines AG Turbinenstufe mit einer Ausblasanordnung und Verfahren zum Ausblasen einer Sperrgasströmung
DE102013212465B4 (de) * 2013-06-27 2015-03-12 MTU Aero Engines AG Dichtanordnung für eine Strömungsmaschine, eine Leitschaufelanordnung und eine Strömungsmaschine mit einer derartigen Dichtanordnung
EP2818643B1 (fr) * 2013-06-27 2018-08-08 MTU Aero Engines GmbH Dispositif d'étanchéité et turbomachine
DE102014208801A1 (de) * 2014-05-09 2015-11-12 MTU Aero Engines AG Dichtung, Verfahren zur Herstellung einer Dichtung und Strömungsmaschine
US10145252B2 (en) * 2015-12-09 2018-12-04 General Electric Company Abradable compositions and methods for CMC shrouds
EP3290649A1 (fr) 2016-09-06 2018-03-07 MTU Aero Engines GmbH Garniture de rodage et procede de fabrication d'une garniture de rodage destine a etancheifier un interstice entre un rotor et un stator d'une turbomachine
PL3409897T3 (pl) * 2017-05-29 2020-04-30 MTU Aero Engines AG Uszczelka maszyny przepływowej, sposób wytwarzania uszczelki oraz maszyna przepływowa
DE102017221660A1 (de) * 2017-12-01 2019-06-06 MTU Aero Engines AG Modul für eine Strömungsmaschine
DE102018218604A1 (de) * 2018-10-30 2020-04-30 MTU Aero Engines AG Dichtanordnung für eine Strömungsmaschine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1148209A2 (fr) * 2000-04-19 2001-10-24 Rolls-Royce Deutschland Ltd & Co KG Configuration de joint inter-étages
EP2360352A2 (fr) * 2010-02-12 2011-08-24 Rolls-Royce Deutschland Ltd & Co KG Joint d'étanchéité sans vis d'une turbine à gaz
EP2722486A1 (fr) * 2012-10-17 2014-04-23 MTU Aero Engines GmbH Support d'étanchéité pour ensemble statorique
EP3109520A1 (fr) * 2015-06-24 2016-12-28 MTU Aero Engines GmbH Support d'étanchéité, stator et turbomachine

Also Published As

Publication number Publication date
US10844737B2 (en) 2020-11-24
DE102018201295A1 (de) 2019-08-01
US20190234225A1 (en) 2019-08-01

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