EP4345251A1 - Module pour une turbomachine - Google Patents

Module pour une turbomachine Download PDF

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Publication number
EP4345251A1
EP4345251A1 EP23196083.2A EP23196083A EP4345251A1 EP 4345251 A1 EP4345251 A1 EP 4345251A1 EP 23196083 A EP23196083 A EP 23196083A EP 4345251 A1 EP4345251 A1 EP 4345251A1
Authority
EP
European Patent Office
Prior art keywords
seal carrier
seal
module
wall
radially
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.)
Pending
Application number
EP23196083.2A
Other languages
German (de)
English (en)
Inventor
Manfred Feldmann
Bernd Kislinger
Christoph Nitsch
Markus Schlemmer
Rudolf Stanka
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 EP4345251A1 publication Critical patent/EP4345251A1/fr
Pending 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
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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.
  • the turbomachine can be, for example, a jet engine, e.g. B. a turbofan engine. Functionally, the turbomachine is divided into a compressor, combustion chamber and turbine. In the case of jet engines, for example, air drawn in is compressed by the compressor and burned in the downstream combustion chamber with mixed kerosene. The resulting hot gas, a mixture of combustion gas and air, flows through the downstream turbine and is expanded in the process. The turbine also extracts a proportion of energy from the hot gas to drive the compressor.
  • the turbine and the compressor are usually constructed in multiple stages, with each stage having a guide and a rotor blade ring.
  • the subject of the present invention is a module with a guide vane arrangement and a seal carrier.
  • the vanes of the vane arrangement extend radially between a radially outer outer platform and a radially inner inner platform.
  • the seal carrier is arranged radially within 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 an advantage in terms of the efficiency of the turbomachine. As large a part as possible or, as far as possible, all of the fluid or gas should flow through the gas channel of the turbomachine.
  • the present invention is based on the technical problem of specifying a particularly advantageous module for a turbomachine.
  • the seal carrier and the guide vane arrangement are mounted relative to one another by means of a first and a second seal carrier wall, for which purpose the seal carrier walls axially delimit an intermediate space into which the guide vane arrangement engages from the radial outside with one or two guide pins.
  • the second seal carrier wall is provided in several pieces with the first seal carrier wall, i.e. as a previously separate part it is assembled with the first seal carrier wall and fastened to it.
  • This fastening is implemented with a connecting element, with a sliding body arranged in the intermediate space keeping the seal carrier walls at the defined distance so that they delimit the intermediate space.
  • the radially inner section should be in frictional contact with the seal carrier (see below in detail), but is not, for example, materially connected to it.
  • the radially inner section can only be in frictional contact and not directly connected to the seal carrier, e.g. materially and/or positively connected.
  • the radially inner section can be free and/or unconnected.
  • the radially inner section can be in frictional contact, in particular axially and/or radially, and/or can otherwise extend freely. This can, for example, reduce stresses in the components, in particular in the seal carrier, and there is no need to close assembly play by deformation, for example.
  • the multi-piece nature of the seal carrier walls can be advantageous in terms of production, for example because, for example, for comparison with two seal carrier walls formed monolithically with the seal carrier and a material-removing production the gap would have to be exposed by a relatively deep cut. Irrespective of this, the multiple pieces can also open up possibilities in the choice of material and thickness, for example the second seal carrier wall can be made thinner and in particular in the form of a sheet metal, thus creating scope for weight optimization.
  • axial refers to the longitudinal axis of the module, i.e. the longitudinal axis of the turbomachine.
  • This longitudinal axis can, for example, coincide with an axis of rotation around which the blades assigned to the guide vane arrangement rotate during operation.
  • “Radial” refers to the radial directions perpendicular to it and pointing away from the longitudinal axis
  • the “circulation” or “direction of rotation” refers to a rotation about the longitudinal axis.
  • Inner and “outer” refer to the radial direction without any explicit statement to the contrary, so “inside” is closer to the longitudinal axis than “outside”. If reference is made to an axial section, this refers to a cutting plane containing the longitudinal axis.
  • first seal support wall is arranged at the front and the second seal support wall at the rear, i.e. the first upstream and the second downstream.
  • the seal carrier can carry a sealing element radially inward, for example, which can seal inwards to a sealing structure, such as a sealing tip or sealing fin, which rotates together with the shaft or the rotor blades during operation.
  • a sealing structure such as a sealing tip or sealing fin
  • a brush seal or a so-called honeycomb seal or, in general terms, a run-in coating can be provided as a sealing element.
  • the first seal carrier wall can preferably be formed monolithically with the seal carrier, whereby the two can then form a T-shape in particular when viewed in an axial section (the first seal carrier wall is therefore spaced from the axial ends of the seal carrier).
  • the connecting element can generally also be a screw or a screw bolt, for example, but is preferably implemented in the form of a rivet.
  • the seal support walls can be fastened to one another with several connecting elements (and sliding bodies) distributed over the circulation, and these sliding bodies can in particular form a so-called spoke centering, see below in detail.
  • connecting elements and sliding bodies
  • spoke centering see below in detail.
  • the "radially inner section" of the second seal carrier wall can in particular be located radially inside the connecting element or be formed at the radially inner end of the second seal carrier wall.
  • there is a frictional engagement i.e. the second seal carrier wall is held in contact with the seal carrier with a contact force, but is not fixed in this contact in a form-fitting and/or material-fitting manner.
  • the frictional engagement which is implemented with a certain pre-tension, can be advantageous, for example, in terms of damping, such as reducing vibrations of the seal carrier.
  • the frictional contact is designed as a radial contact between a side surface of the second seal carrier wall facing the first seal carrier wall and a contact surface of the seal carrier.
  • This contact surface is preferably formed on a step in an outwardly facing top surface of the seal carrier, with the radially inner end of the second seal carrier wall not resting. Instead is between the A gap is formed on the top surface and this end, which allows radial play.
  • the second seal support wall and the seal support then preferably rest against each other exclusively in the contact surface on the step, so there is no further contact surface(s).
  • the radially inner section of the second seal carrier wall extends obliquely radially inwards when viewed in an axial section, i.e. proportionally axially and radially.
  • An oblique extension inwards and at the same time away from the first seal carrier wall is preferred.
  • the oblique inner section can act as a spring element, i.e. ensure a certain contact pressure.
  • the second seal carrier wall rests exclusively with its radially inner end on the seal carrier and the oblique radially inner section extends freely apart from that, i.e. at a distance from the upper side surface of the seal carrier.
  • a sealing web is arranged on at least one of the seal support walls, which, viewed in an axial section, extends away from this at least one seal support wall and the intermediate space.
  • the sealing web In the case of the first/front seal support wall, the sealing web extends axially forward, whereas in the case of the second/rear seal support wall it extends axially rearward away from it.
  • the sealing web together with the inner platform of the guide vane arrangement, forms a so-called labyrinth or fishmouth seal.
  • This can also be formed proportionally together with the inner platform of a rotor blade arrangement which is immediately upstream in the case of the front sealing web or immediately downstream in the case of the rear sealing web.
  • the inner platform of the blade assembly can then be arranged at a radial position between the inner platform and the sealing land.
  • a front sealing web is preferably arranged on the front seal support wall and/or a rear sealing web is arranged on the rear seal support wall, particularly preferably both.
  • the sealing web is provided in several pieces with the seal carrier wall and is attached to the seal carrier wall via the connecting element.
  • the sealing web is formed monolithically with the seal carrier wall, i.e. integrally from the same continuous material.
  • the second seal carrier wall is provided as sheet metal (see below in detail), for example a radially outer section thereof can be bent accordingly (and extend at least partially axially when viewed in an axial section).
  • the front sealing web can be provided in several pieces and attached to the front seal carrier wall with the connecting element, with the rear sealing web either also being formed in several pieces with the rear seal carrier wall or monolithically with it in the manner just described.
  • the sliding body can, for example, also be provided monolithically with one of the seal support walls, i.e. the first or in particular second seal support wall.
  • the connecting element passes through it axially.
  • the latter is also preferred in the case of a monolithic design, but not mandatory.
  • the connecting element which passes through the multi-piece sliding body, holds it in a radially positive manner between the seal support walls, and the sliding body is then additionally clamped axially, for example.
  • the second seal support wall has a smaller thickness than the first seal support wall, so the multi-piece design is used to optimize weight.
  • the thicknesses are each viewed in an axial section, whereby an average value is used as a basis in the case of a thickness that varies over the extent of the respective seal support wall.
  • the second seal carrier wall is formed from a sheet metal, which allows a particularly thin design and/or simple Production can be permitted.
  • the sheet can generally be segmented in the direction of rotation, i.e. provided in several parts. However, a continuous design in the direction of rotation, i.e. not divided/segmented, is preferred.
  • the first seal carrier wall is formed monolithically with the seal carrier in a preferred embodiment, i.e. from the same uninterrupted, continuous material. Since the second seal carrier wall is attached separately and the gap does not have to be taken into account when producing the seal carrier, the monolithic production of the seal carrier and the first seal carrier wall can be simplified, for example by casting.
  • the guide pin with which the guide vane arrangement engages in the intermediate space, extends radially inwards from its inner platform.
  • the guide pin preferably rests on the sliding body, i.e. on the circumferential side.
  • it encloses the sliding body together with another guide pin, which rests on the opposite side of the sliding body in the direction of rotation. This is therefore held between the guide pins, which is also referred to as a tang ("pincer").
  • the guide pins and the sliding body can still slide radially against each other, with several correspondingly held sliding bodies distributed all around, so the arrangement represents a spoke centering.
  • the invention also relates to a turbine for a turbomachine, in particular for an aircraft engine, which has a module disclosed here.
  • 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 made up of several stages, each stage consists of a guide vane and a rotor blade ring.
  • the rotor blade ring is arranged downstream of the associated guide vane ring.
  • the rotor blades rotate around the longitudinal axis 2.
  • Fig.2 shows a section of the turbine 1c as module 20, again in an axial section.
  • a guide vane arrangement 21 with a guide vane blade 21a and an inner platform 21b, as well as a guide pin 21c can be seen.
  • the guide vane blade 21a is arranged radially on the outside of the inner platform 21b, the guide pin 21c extends radially inside it into an intermediate space 22.
  • This intermediate space 22 is axially delimited between a first, front seal carrier wall 31 and a second, rear seal carrier wall 32.
  • the first seal carrier wall 31 is upstream in relation to a flow 15 of the module 20 and the second seal carrier wall 32 is downstream.
  • the first seal carrier wall 31 is monolithically formed with a seal carrier 41, the two can be manufactured as a cast part, for example.
  • a sealing element 42 is provided radially on the inside of the seal carrier 41, for example a honeycomb seal and/or a run-in coating, in particular for a run-in structure, such as a sealing fin.
  • the sealing element 42 seals against a sealing structure 43, which is only shown schematically as a contour here and rotates together with the shaft during operation.
  • the sealing structure 43 can comprise a run-in structure, which in turn can comprise sealing fins.
  • the sealing structure 43 comprises two sealing fins.
  • the second seal carrier wall 32 is provided in several pieces to the first seal carrier wall 31 and is attached to it via a connecting element 35, in this case a rivet.
  • the connecting element 35 passes through a sliding body 36, which holds the seal carrier walls 31, 32 at the defined axial distance.
  • the second seal carrier wall 32 specifically a radially inner section 32.1 thereof, does indeed rest against the seal carrier 41 with a side surface 32a facing the first seal carrier wall 31, but has radial play. This is achieved by a frictional axial contact with a step 45 formed in the top surface 41a of the seal carrier 41, whereby despite this contact a gap 46 still remains between the second seal carrier wall 32 and the top surface 41a.
  • Figure 3 shows a Figure 2 alternative design, whereby the following illustration primarily emphasizes the differences and otherwise reference is made to the above description.
  • the same reference symbols designate the same parts or parts with the same function and reference is always made to the description of the other figures.
  • the inner section 32.1 extends obliquely to the longitudinal axis (not shown) inwards and rests only with its radially inner end 32.1.1 on the upper surface 41a (only in Fig.2 but not in Fig.3 referenced with a reference symbol) of the seal carrier 41.
  • the sealing webs 51, 52 are attached to the respective seal support wall 31, 32 as multi-piece parts and are attached to them via the connecting element 35.
  • the front sealing web 51 together with the inner platform 21b and an inner platform 55 (shown only schematically as a contour) of the upstream rotor blade arrangement, forms a labyrinth seal 61
  • the rear sealing web 52 also forms together with the inner platform 21b of the guide blade arrangement 21 and the inner platform 56 (only schematically as Contour shown) of the downstream blade arrangement a labyrinth seal 62.
  • the variant according to Figure 5 differs from that according to Figure 4 only in the realization of the rear sealing web 72, which in this case is formed monolithically with the second seal carrier wall 32.
  • This design can be realized, for example, by bending a sheet metal accordingly.
  • the variant according to Figure 6 corresponds to the front sealing bar 51 of the Figures 4 and 5 , but is designed as a simplified design without a rear sealing web.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP23196083.2A 2022-09-22 2023-09-07 Module pour une turbomachine Pending EP4345251A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102022124401.6A DE102022124401A1 (de) 2022-09-22 2022-09-22 Modul für eine strömungsmaschine

Publications (1)

Publication Number Publication Date
EP4345251A1 true EP4345251A1 (fr) 2024-04-03

Family

ID=87971863

Family Applications (1)

Application Number Title Priority Date Filing Date
EP23196083.2A Pending EP4345251A1 (fr) 2022-09-22 2023-09-07 Module pour une turbomachine

Country Status (3)

Country Link
US (1) US20240102398A1 (fr)
EP (1) EP4345251A1 (fr)
DE (1) DE102022124401A1 (fr)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3733146A (en) * 1971-04-07 1973-05-15 United Aircraft Corp Gas seal rotatable support structure
US4721434A (en) * 1986-12-03 1988-01-26 United Technologies Corporation Damping means for a stator
EP2722486A1 (fr) * 2012-10-17 2014-04-23 MTU Aero Engines GmbH Support d'étanchéité pour ensemble statorique
DE102016222608A1 (de) * 2016-11-17 2018-05-17 MTU Aero Engines AG Dichtungsanordnung für eine Leitschaufelanordnung einer Gasturbine
DE102017221660A1 (de) * 2017-12-01 2019-06-06 MTU Aero Engines AG Modul für eine Strömungsmaschine
DE102018201295A1 (de) * 2018-01-29 2019-08-01 MTU Aero Engines AG Modul für eine strömungsmaschine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3647311A (en) 1970-04-23 1972-03-07 Westinghouse Electric Corp Turbine interstage seal assembly
US5597167A (en) 1994-09-28 1997-01-28 United Technologies Corporation Brush seal with fool proofing and anti-rotation tab
DE102012201050B4 (de) 2012-01-25 2017-11-30 MTU Aero Engines AG Dichtungsanordnung, Verfahren sowie Strömungsmaschine
DE102014212174A1 (de) 2014-06-25 2015-12-31 MTU Aero Engines AG Bürstendichtungssystem zum Abdichten eines Spalts zwischen relativ zueinander bewegbaren Bauteilen einer Strömungsmaschine
PL3409897T3 (pl) 2017-05-29 2020-04-30 MTU Aero Engines AG Uszczelka maszyny przepływowej, sposób wytwarzania uszczelki oraz maszyna przepływowa
DE102021125304A1 (de) 2021-09-29 2023-03-30 MTU Aero Engines AG Dichtungseinrichtung für eine Strömungsmaschine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3733146A (en) * 1971-04-07 1973-05-15 United Aircraft Corp Gas seal rotatable support structure
US4721434A (en) * 1986-12-03 1988-01-26 United Technologies Corporation Damping means for a stator
EP2722486A1 (fr) * 2012-10-17 2014-04-23 MTU Aero Engines GmbH Support d'étanchéité pour ensemble statorique
DE102016222608A1 (de) * 2016-11-17 2018-05-17 MTU Aero Engines AG Dichtungsanordnung für eine Leitschaufelanordnung einer Gasturbine
DE102017221660A1 (de) * 2017-12-01 2019-06-06 MTU Aero Engines AG Modul für eine Strömungsmaschine
DE102018201295A1 (de) * 2018-01-29 2019-08-01 MTU Aero Engines AG Modul für eine strömungsmaschine

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Publication number Publication date
DE102022124401A1 (de) 2024-03-28
US20240102398A1 (en) 2024-03-28

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