EP3324002A1 - Système d'étanchéité pour une turbomachine axiale et turbomachine axiale - Google Patents
Système d'étanchéité pour une turbomachine axiale et turbomachine axiale Download PDFInfo
- Publication number
- EP3324002A1 EP3324002A1 EP17198765.4A EP17198765A EP3324002A1 EP 3324002 A1 EP3324002 A1 EP 3324002A1 EP 17198765 A EP17198765 A EP 17198765A EP 3324002 A1 EP3324002 A1 EP 3324002A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- shroud
- sealing
- sealing system
- tip
- housing
- 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.)
- Granted
Links
- 238000007789 sealing Methods 0.000 title claims abstract description 163
- 230000003068 static effect Effects 0.000 claims abstract description 68
- 239000002347 wear-protection layer Substances 0.000 claims description 33
- 239000000463 material Substances 0.000 claims description 18
- 238000011144 upstream manufacturing Methods 0.000 claims description 9
- 239000011248 coating agent Substances 0.000 claims description 4
- 238000000576 coating method Methods 0.000 claims description 4
- 238000002156 mixing Methods 0.000 description 5
- 239000010410 layer Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 239000000203 mixture Substances 0.000 description 4
- 230000002093 peripheral effect Effects 0.000 description 4
- 230000015572 biosynthetic process Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 238000000227 grinding Methods 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 229910001347 Stellite Inorganic materials 0.000 description 1
- 208000004350 Strabismus Diseases 0.000 description 1
- WAIPAZQMEIHHTJ-UHFFFAOYSA-N [Cr].[Co] Chemical class [Cr].[Co] WAIPAZQMEIHHTJ-UHFFFAOYSA-N 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 238000000149 argon plasma sintering Methods 0.000 description 1
- AHICWQREWHDHHF-UHFFFAOYSA-N chromium;cobalt;iron;manganese;methane;molybdenum;nickel;silicon;tungsten Chemical compound C.[Si].[Cr].[Mn].[Fe].[Co].[Ni].[Mo].[W] AHICWQREWHDHHF-UHFFFAOYSA-N 0.000 description 1
- 229910017052 cobalt Inorganic materials 0.000 description 1
- 239000010941 cobalt Substances 0.000 description 1
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 1
- 230000008021 deposition Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 238000005476 soldering Methods 0.000 description 1
- 239000002344 surface layer Substances 0.000 description 1
Images
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
-
- 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
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
-
- 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
- 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
- F01D11/127—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 with a deformable or crushable structure, e.g. honeycomb
-
- 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
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for blades
-
- 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
- F05D2230/90—Coating; Surface treatment
-
- 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
-
- 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
- F05D2260/00—Function
- F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
- F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
Definitions
- the present invention relates to a sealing system for an axial flow machine according to the preamble of claim 1. Furthermore, the present invention relates to an axial flow machine according to claim 14.
- the pressure in the working fluid changes from stage to stage.
- the pressure in the compressor is usually downstream of a row of blades higher than the pressure upstream, in the turbine, however downstream of a row of blades less than the pressure upstream.
- a sealing system is provided in the region of an outer annular space boundary, which is designed for example as a labyrinth system.
- Such sealing systems have the task of keeping a leakage current through a sealing gap between the rotating blading and a housing minimal and thus to allow a stable operating behavior with high efficiency.
- the rotating components of a turbine on sealing fins or sealing tips, which can strip or shrink against honeycomb seals.
- the seals are designed as a squint and inlet coverings.
- An object of the present invention is to propose a further sealing system for an axial flow machine. It is another object of the present invention to provide an axial flow machine with a sealing system according to the invention.
- the object of the invention is achieved by a sealing system having the features of claim 1. It is further achieved by an axial flow machine having the features of claim 14.
- a sealing system for an axial flow machine which comprises at least one impeller with a shroud arranged radially on the outside and a housing surrounding the impeller. Between the shroud and the housing, a gap is arranged. The gap is bounded on the one hand by means of a seal connected to the housing and on the other hand by means of at least one sealing tip arranged on the cover band.
- This arranged on the shroud sealing tip can be referred to as a rotating sealing tip, as it rotates with the impeller.
- the seal is, viewed in the radial direction, arranged opposite the shroud. The limitation of the gap by the seal and the shroud can reduce the flow losses of the slit flow.
- static sealing tip At the downstream end portion of the housing-side seal another, connected to the housing, static sealing tip is arranged.
- this static sealing tip By means of this static sealing tip, the flow through the gap is influenced, in particular reduced.
- the flow downstream of the static sealing tip is influenced by means of the static sealing tip.
- An influence in particular a reduction of the flow through the gap by means of the static sealing tip, can be caused by flow losses of the static sealing tip.
- a possible vortex formation downstream of the static sealing tip can be influenced by the static sealing tip.
- the gap flow between the static sealing tip and the shroud may cause a vortex or vortex region downstream, the direction of rotation of which has primarily the same flow direction as the adjacent main flow.
- the flow losses and / or the disturbance of the main flow through these vortices can be reduced. This can advantageously increase the efficiency of the axial flow machine by the sealing system according to the invention.
- a reduced main flow disturbance due to the described direction of rotation of the vortices may be referred to as a low loss mixing with the main flow.
- a sealing system without static sealing tip lead to a vortex formation whose primary direction of rotation is opposite to the main flow. This would lead to a lossy mixture with the main flow and could contribute to a reduction in the efficiency of the turbomachine.
- the shroud arranged radially on the outside of the impeller can be referred to as an outer shroud or as a shovel outer shroud.
- the arranged between the shroud and the housing gap may be referred to as a running gap.
- the axial flow machine according to the invention comprises at least one low-pressure turbine stage with a sealing system according to the invention.
- the axial flow machine may further comprise at least one high-pressure turbine stage, a low-pressure compressor stage and a high-pressure compressor stage. Each of said stages may comprise a sealing system according to the invention.
- the axial flow machine may be a gas turbine, in particular an aircraft gas turbine or an aircraft engine.
- Inventive exemplary embodiments may have one or more of the following features.
- a static and / or a circumferential sealing tip can be referred to as Dichtfin.
- the seal associated with the housing may be an inlet seal.
- An inlet seal can be called an abradable seal.
- An inlet seal may have an insertable coating or an insertable layer into which, for example, a sealing tip can penetrate to form a sealing gap. This sealing gap can be made small by the penetration or shrinkage of a sealing tip, in particular during an intended operating state and thus contribute advantageously to optimize the efficiency of the turbomachine.
- the inlet seal may comprise a honeycomb structure for penetrating a sealing tip.
- the inlet seal may be connected to the housing cohesively and / or positively.
- the inlet seal may be glued, soldered, riveted or clamped, or otherwise attached to the housing.
- the inlet seal is attached only to the housing.
- the inlet seal is thus arranged only on one side of the gap.
- the shroud may include at least two sealing tips.
- Two sealing tips can engage in two opposite inlet seals on the housing and form a sealing gap.
- the at least two sealing tips can be arranged axially one behind the other on a radius or at a radial height.
- the two sealing tips can be arranged axially one behind the other at different radii or at radially different heights, that is, offset radially.
- the shroud has no seal, in particular no inlet seal.
- the shroud has three or more sealing tips.
- the sealing tips may be arranged radially at a height or at different heights. For example, two axially successively arranged sealing tips have the same radius, whereas a third sealing tip is arranged radially further outside.
- the at least one sealing tip of the shroud is arranged inclined upstream.
- the angle of inclination between the radial direction and the axial direction may be, for example, at least 15 degrees.
- a non-sloped sealing tip in the radial direction would be zero degrees.
- An inclined sealing tip can favor the flow losses due to a smaller flow through the gap influence.
- An inclined sealing tip can also be advantageous in terms of the shroud configuration, for example, in an arrangement of multiple sealing tips on the shroud.
- the structural strength of the shroud with an inclined sealing tip can be advantageously higher.
- the upstreammost sealing tip of the shroud can be inclined.
- the incline can be twenty degrees, twenty-five degrees, thirty degrees or more.
- the shroud has wear protection in the opposite region of the static sealing tip.
- the wear protection can advantageously prevent direct contact of the static sealing tip with the base material of the shroud. Direct contact could damage the shroud causing more damage.
- the wear protection of the shroud extends beyond the opposite region of the static sealing tip, in particular at least to the adjacent shroud end.
- the wear protection can extend over more area of the shroud.
- the wear protection is a, at least in sections, coating of the shroud.
- the wear-resistant layer can also be understood as a flake-like element fastened to the shroud in a material- and / or non-positive manner, for example of a material with the trade name "stellite".
- the wear protection is arranged in regions over the circumference of the shroud.
- the wear protection can be arranged only at individual points of the shroud.
- the material of the static sealing tip has a lower hardness than the hardness of the wear protection layer.
- the hardness of the material can be a measure of the resistance of the material to wear.
- the material of the wear protection layer preferably differs from the base material of the shroud and, in particular, also has a greater hardness relative to this base material.
- greater hardness in the sense of the present invention is meant in particular a “greater wear resistance”.
- the wear protection is superior to the rest of the shroud surface, or in other words, the height of the wear protection extends beyond the surface of the shroud.
- the wear protection thickness can have, for example, 5 ⁇ m, 10 ⁇ m, 20 ⁇ m or another thickness.
- a wear protection is produced by means of a local surface layer hardening, in particular by means of a laser-supported method.
- the static sealing tip is fastened to the housing with a positive-locking component, in particular a holding element.
- the static sealing tip can be materially connected to the holding element.
- the static sealing tip is secured to the housing with a positive fit component, particularly a retainer, on the downstream baffle, or the baffle connection.
- the static sealing tip can be materially connected to the holding element.
- the impeller is a turbine runner, particularly a low-pressure turbine runner.
- the shroud is segmented about the circumference of the impeller.
- the segments are designed as z-shroud segments.
- the impeller blades can advantageously be braced with one another.
- the contact regions of the shroud segments have wear protection in the circumferential direction.
- This wear protection can be designed as wear protection in the opposite region of the static sealing tip.
- this wear protection projects as a wear protection layer beyond the shroud surface, so that in the event of contact of the static sealing tip with the shroud, initially only the wear protection layer touches becomes.
- the hardness of the wear protection layer is greater than the hardness of the static sealing tip. This advantageously allows the shroud to be protected from contact with the static sealing tip. Such contact could damage the shroud.
- the wear protection can be integrally connected to the shroud, for example by means of welding (for example by laser deposition welding).
- the material of the wear protection can be a cobalt-based hard alloy, for example a cobalt-chromium alloy, or have such.
- the hardness of the wear-resistant coating can be greater than 600 Vickers hardness (HV for short) purely by way of example.
- the static sealing tip is connected in a form-fitting and / or material-locking manner to the housing by means of a holding element.
- the static sealing tip on the side opposite the shroud has a circumferentially variable, in particular wave-shaped structure.
- a circumferentially variable, in particular wave-shaped structure By means of the variable or wave-like structure, when the sealing tip contacts the shroud, or with a wear protection layer on the shroud, an axially larger area of a contact surface of the sealing tip can be used in comparison with a non-variable or wavy, ie straight, structure over the circumference.
- the heat input during a contact process or a rubbing process between the sealing tip and the shroud (or the wear protection layer) can advantageously be distributed over a larger area and a larger volume of material. As a result, the load, in particular the thermal material stress, of the wear protection layer can be locally reduced.
- Some or all embodiments according to the invention may have one, several or all of the advantages mentioned above and / or below.
- the leakages that is to say the bypass flow or the gap flow
- the leaks can be referred to as primary losses.
- the gap flow can be reduced.
- the main flow less disturbed and thus the efficiency of the turbomachine can be increased.
- the disturbances of the main flow can be called secondary losses.
- the vortex formation can be influenced downstream of the static sealing tip and thus the vortex rotation direction of the main flow direction can be adjusted. As a result, a low-loss mixture of the vortices resulting from the slit flow can be achieved with the main flow.
- FIG. 1 shows a known from the prior art sealing system 100 'of a turbine stage with an inlet seal 12 and two rotating (rotating) sealing tips 5 in longitudinal section.
- a sealing system 100 ' may be synonymously referred to as a sealing system.
- the inlet seal 12 may be referred to as inlet lining.
- a housing portion 10 is shown on the housing side, in which a seal carrier 11 is mounted.
- the housing portion 10 could also be referred to as a static sealing part.
- the inlet seal 12 is fixed, for example, materially by means of soldering or gluing.
- two sealing tips 5, which can be referred to as sealing fins In the inlet seal 12 engage two sealing tips 5, which can be referred to as sealing fins.
- a running gap 6 between the inlet seal 12 and the sealing tips 5 is generated or generated by means of shrinkage or cutting in of the sealing tips 5.
- the sealing tips 5 are arranged on a radially outer shroud 4, which in turn is connected to an impeller 3.
- the shroud 4 may be integrally connected to the impeller 3, for example by means of a laser sintering process.
- the flow direction of a leakage flow (the leakage flow may be referred to as a split flow or bypass flow) is shown by the arrow of the reference numeral 6 of the nip 6.
- the flow direction is in the arrow direction of the reference character of the nip 6.
- a stiffening structure 13 is optionally shown on the shroud 4.
- the moving blade 3 is unambiguously positioned with respect to the inlet seal 12, and thus with respect to the surrounding housing 30 and the guide wheels 1, 2, which may be referred to as stator.
- the rotor connected to the impeller 3 (in Fig. 1 not shown) move axially within certain limits relative to the stator, for example due to a play of the bearings, thermal expansions and other factors. Due to these axial movements of the rotor and the impeller 3, only a few sealing tips 5 can be arranged on the shroud 4.
- Fig. 1 are two sealing tips 5 are arranged as an example. Due to this limited number of sealing tips 5, the sealing effect, depending on the running gap 6, limited.
- Fig. 2 shows a sealing system according to the invention 100 a turbine stage with an inlet seal 12, two circumferential sealing tips 5 and connected to a housing 30 static sealing tip 20 in longitudinal section.
- the arrangement of the upstream stator 1, the downstream stator 2, the blade 3, the housing portion 10 and the seal carrier 11 (which is shown in FIG Fig. 2 designed differently than in Fig. 1 ) is analogous to the description of Fig. 1 ,
- the two rotating sealing tips 5 are axially offset on the shroud 5 relative to the arrangement of Fig. 1 arranged.
- a case-side static sealing tip 20 is installed opposite to the downstream end portion of the shroud 4.
- the static sealing tip 20 is in the exemplary embodiment of Fig. 2 fixed by means of a holding element 21 on the static housing section 10 and the housing-side holder of the downstream stator 2.
- the fixation can be designed as a clamp.
- An additional cohesive fixation of the static sealing tip 20 on the holding element 21 and / or of the holding element 21 on the housing section 10, for example by means of a soldered or welded connection, is optionally possible.
- Fig. 2 a so-called Griffinbegrenzer 22 introduced into the housing 30 inside.
- the room delimiter 22 can for example contribute to the reduction of flow losses.
- the additional static sealing tip 20 can advantageously reduce the leakage resulting from the running gap 6. Furthermore, the direction of rotation of the downstream of the static sealing tip 20 forming vortex W with respect to the direction of rotation of the sealing system 100 'from the Fig. 1 reverse, so that a low-loss mixture with the main flow H is advantageously possible.
- the low-loss mixture with the main flow H is through the same parallel flow direction of the main flow H with the flow direction of the immediately emerging vortex in Fig. 2 shown. Due to these two effects of the static sealing tip 20, reduction of the leakage and low-loss mixing of the vortex W with the main flow H, the total losses of the turbine stage can be advantageously reduced.
- the front upstream seal tip 5 is inclined, with respect to the radial direction r, against the main flow direction aligned in the axial direction.
- the inclination is about 30 degrees.
- the leakage flow can be influenced by the running gap 6.
- the two sealing tips 5 are arranged radially offset and thus approximately form the widening flow channel of the turbine stage.
- the shroud 4 is executed segmented over the circumference u.
- the segments are often executed as so-called z-shrouds (see Fig. 4 that look as View B Fig. 2 is shown), since their peripheral edges are not rectilinear in the axial direction of the turbomachine, but are formed substantially z-fömig. With this z-shape, it is possible to clamp in the mounted state, the circumferentially adjacent blades 3 a rotor stage with each other.
- a wear protection layer 8 which in the Figures 2 . 3 and 4 is shown dark.
- the wear protection view 8 is applied in the axial direction of the turbomachine not only in the central region of the z-fömigen peripheral edge of the shroud 4, in which by contact substantially the bracing forces between two circumferentially adjacent blades 3 are transmitted to the shroud 4, but the wear protection layer extends axially even further to the rear.
- the wear protection layer 8 extends in the axial direction of the turbomachine at least up to the axial position of the static sealing tip 20 to the rear. In the present embodiment, the wear protection layer 8 extends even to the downstream end of the shroud. 4
- the wear protection layer 8 projects beyond the surface of the shroud 4. This has the advantage that in case of an unwanted contact of the static sealing tip 20 with the shroud 4, for example in the case of a hard landing of an aircraft provided with the turbomachine as an engine, the static sealing tip 20 does not If the material of the wear protection layer 8 has a higher hardness than the material of the static sealing tip 20, the static sealing tip 20 is removed from the rotating impeller 3 or abraded.
- the static sealing tip 20 may be slightly shortened, for example, in the radial direction r. In this way, damage to the impeller 3 is prevented.
- a grinding of the static sealing tip 20 through the wear protection layer 8, however, is much less critical and the static sealing tip 20 can also be replaced relatively easily and inexpensively.
- Fig. 3 shows the sealing system 100 according to the invention in a cross-sectional plane (section A - A, see Fig. 2 ) with the static sealing tip 20, the seal carrier 11, the impeller 3 with shroud 4 and a wear protection layer 8 between the shroud segments.
- the shroud 4 is segmented.
- the so-called z-shroud has wear protection layers 7, 8 at the contact points of the abutting segments.
- the wear protection layer 8 which extends in the axial direction further downstream than the wear protection layer 7, projects slightly beyond the radial extent of the shroud surface. In Fig. 3 this is represented by the heel height 23.
- the static sealing tip 20 Due to this increase of the wear protection layer 8 over the surface of the shroud 4, the static sealing tip 20, for example, in the aforementioned case, first the increased wear protection layer 8 touched at a lower hardness of the material of the static sealing tip 20 against the hardness of the material of the wear protection layer 8 the static sealing tip 20 ground or deformed, but without touching the shroud 4 itself and damage.
- the wear-resistant layer 8 used for the contact of two circumferentially adjacent shrouds 4 can be synergistically used here in order to prevent possible damage to the base material of the shroud 4 by contact with the static sealing tip 20.
- the wear protection layer 8 in the axial and radial directions of the turbomachine is to be dimensioned only slightly larger than would otherwise be the case.
- Fig. 4 shows the shroud 4 in a view B from the radial outside (see Fig. 2 ) with the wear protection layers 7, 8.
- the profile shape of the blade shape of the impeller 3 is schematically indicated below the shroud.
- the sealing tips 5 of the shroud 4 project out of the plane of representation.
- the wear protection layers 7, 8 are located at the contact surfaces of the z-shroud to the circumferentially adjacent (not shown) segments of other bucket cover strips.
- the shaded anti-wear layer 8 was already in the cutting plane of Fig. 2 opposite the static sealing tip 20.
- Fig. 5a, b show two different courses of the radially inner edge, or inner edge of the static sealing tip 20 in the circumferential direction u in a view C (see Fig. 3 ).
- Fig. 5a is a straight waveform and shown in Fig. 5b a waveform.
- the waveform has the advantage that in the case of contact of the static sealing tip 20 with the wear protection layer 8 of the shroud 4, an axially larger area of the wear protection layer 8 for a grinding or deformation of the static sealing tip 20 is available.
- the heat input is distributed over a larger volume of material, as a result of which the wear protection layer 8 is loaded less locally.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102016222720.3A DE102016222720A1 (de) | 2016-11-18 | 2016-11-18 | Dichtungssystem für eine axiale Strömungsmaschine und axiale Strömungsmaschine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3324002A1 true EP3324002A1 (fr) | 2018-05-23 |
EP3324002B1 EP3324002B1 (fr) | 2021-06-16 |
Family
ID=60190693
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP17198765.4A Active EP3324002B1 (fr) | 2016-11-18 | 2017-10-27 | Système d'étanchéité pour une turbomachine et turbomachine axiale |
Country Status (4)
Country | Link |
---|---|
US (1) | US20180142567A1 (fr) |
EP (1) | EP3324002B1 (fr) |
DE (1) | DE102016222720A1 (fr) |
ES (1) | ES2881326T3 (fr) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3822461A1 (fr) * | 2019-11-15 | 2021-05-19 | MTU Aero Engines AG | Système d'étanchéité de turbomachine axiale |
FR3107720A1 (fr) * | 2020-02-27 | 2021-09-03 | Safran Aircraft Engines | Aube de turbine, procédé de fabrication ou de reconditionnement du talon de ladite aube |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11060407B2 (en) * | 2017-06-22 | 2021-07-13 | General Electric Company | Turbomachine rotor blade |
FR3100271B1 (fr) * | 2019-09-04 | 2022-08-26 | Safran Aircraft Engines | Aube de turbomachine comportant un talon pourvu d’un becquet à plateforme déportée |
DE102019216646A1 (de) * | 2019-10-29 | 2021-04-29 | MTU Aero Engines AG | Laufschaufelanordnung für eine strömungsmaschine |
WO2021199718A1 (fr) * | 2020-03-30 | 2021-10-07 | 株式会社Ihi | Structure de suppression d'écoulement secondaire |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2604797A1 (fr) * | 2011-12-13 | 2013-06-19 | MTU Aero Engines GmbH | Aube de rotor dotée d'un agencement de nervures ayant un revêtement abrasif |
EP2647796A1 (fr) * | 2012-04-04 | 2013-10-09 | MTU Aero Engines GmbH | Système d'étanchéité pour turbomachine |
US20150211372A1 (en) * | 2014-01-30 | 2015-07-30 | Solar Turbines Incorporated | Hot isostatic pressing to heal weld cracks |
EP2957718A1 (fr) * | 2014-06-18 | 2015-12-23 | Siemens Aktiengesellschaft | Turbine |
EP3061850A1 (fr) * | 2015-02-25 | 2016-08-31 | United Technologies Corporation | Revêtement métallique sans phases durs pour pointe d'aube de compresseur |
Family Cites Families (22)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3694882A (en) * | 1970-09-24 | 1972-10-03 | Westinghouse Electric Corp | Method for providing a corrugated seal in an elastic fluid machine |
GB1423833A (en) * | 1972-04-20 | 1976-02-04 | Rolls Royce | Rotor blades for fluid flow machines |
US3867060A (en) * | 1973-09-27 | 1975-02-18 | Gen Electric | Shroud assembly |
FR2635562B1 (fr) * | 1988-08-18 | 1993-12-24 | Snecma | Anneau de stator de turbine associe a un support de liaison au carter de turbine |
US6131910A (en) * | 1992-11-19 | 2000-10-17 | General Electric Co. | Brush seals and combined labyrinth and brush seals for rotary machines |
US5234318A (en) * | 1993-01-22 | 1993-08-10 | Brandon Ronald E | Clip-on radial tip seals for steam and gas turbines |
US6190124B1 (en) * | 1997-11-26 | 2001-02-20 | United Technologies Corporation | Columnar zirconium oxide abrasive coating for a gas turbine engine seal system |
US20040124231A1 (en) * | 1999-06-29 | 2004-07-01 | Hasz Wayne Charles | Method for coating a substrate |
US6547522B2 (en) * | 2001-06-18 | 2003-04-15 | General Electric Company | Spring-backed abradable seal for turbomachinery |
US6616410B2 (en) * | 2001-11-01 | 2003-09-09 | General Electric Company | Oxidation resistant and/or abrasion resistant squealer tip and method for casting same |
US7059821B2 (en) * | 2003-05-07 | 2006-06-13 | General Electric Company | Method and apparatus to facilitate sealing within turbines |
JP4285134B2 (ja) * | 2003-07-04 | 2009-06-24 | 株式会社Ihi | シュラウドセグメント |
GB2417053B (en) * | 2004-08-11 | 2006-07-12 | Rolls Royce Plc | Turbine |
EP1715224A1 (fr) * | 2005-04-18 | 2006-10-25 | Siemens Aktiengesellschaft | Joint d'étanchéité de turbomachine |
US7686568B2 (en) * | 2006-09-22 | 2010-03-30 | General Electric Company | Methods and apparatus for fabricating turbine engines |
DE102008023326A1 (de) * | 2008-05-13 | 2009-11-19 | Mtu Aero Engines Gmbh | Deckband für Laufschaufeln einer Strömungsmaschine und Strömungsmaschine |
GB2492546A (en) * | 2011-07-04 | 2013-01-09 | Alstom Technology Ltd | A labyrinth seal for an axial fluid flow turbomachine |
US8858167B2 (en) * | 2011-08-18 | 2014-10-14 | United Technologies Corporation | Airfoil seal |
US9151174B2 (en) * | 2012-03-09 | 2015-10-06 | General Electric Company | Sealing assembly for use in a rotary machine and methods for assembling a rotary machine |
EP2647795B1 (fr) * | 2012-04-04 | 2018-11-07 | MTU Aero Engines AG | Système d'étanchéité pour turbomachine |
US9291061B2 (en) * | 2012-04-13 | 2016-03-22 | General Electric Company | Turbomachine blade tip shroud with parallel casing configuration |
US8936431B2 (en) * | 2012-06-08 | 2015-01-20 | General Electric Company | Shroud for a rotary machine and methods of assembling same |
-
2016
- 2016-11-18 DE DE102016222720.3A patent/DE102016222720A1/de not_active Withdrawn
-
2017
- 2017-10-27 ES ES17198765T patent/ES2881326T3/es active Active
- 2017-10-27 EP EP17198765.4A patent/EP3324002B1/fr active Active
- 2017-11-16 US US15/815,494 patent/US20180142567A1/en not_active Abandoned
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2604797A1 (fr) * | 2011-12-13 | 2013-06-19 | MTU Aero Engines GmbH | Aube de rotor dotée d'un agencement de nervures ayant un revêtement abrasif |
EP2647796A1 (fr) * | 2012-04-04 | 2013-10-09 | MTU Aero Engines GmbH | Système d'étanchéité pour turbomachine |
US20150211372A1 (en) * | 2014-01-30 | 2015-07-30 | Solar Turbines Incorporated | Hot isostatic pressing to heal weld cracks |
EP2957718A1 (fr) * | 2014-06-18 | 2015-12-23 | Siemens Aktiengesellschaft | Turbine |
EP3061850A1 (fr) * | 2015-02-25 | 2016-08-31 | United Technologies Corporation | Revêtement métallique sans phases durs pour pointe d'aube de compresseur |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3822461A1 (fr) * | 2019-11-15 | 2021-05-19 | MTU Aero Engines AG | Système d'étanchéité de turbomachine axiale |
FR3107720A1 (fr) * | 2020-02-27 | 2021-09-03 | Safran Aircraft Engines | Aube de turbine, procédé de fabrication ou de reconditionnement du talon de ladite aube |
Also Published As
Publication number | Publication date |
---|---|
US20180142567A1 (en) | 2018-05-24 |
ES2881326T3 (es) | 2021-11-29 |
EP3324002B1 (fr) | 2021-06-16 |
DE102016222720A1 (de) | 2018-05-24 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP3324002B1 (fr) | Système d'étanchéité pour une turbomachine et turbomachine axiale | |
DE69506890T2 (de) | Dynamische kontrolle vom schaufelspitzenspiel | |
DE60029405T2 (de) | Abriebbeständige Verdichterstufe | |
DE102012013160B4 (de) | Labyrinthdichtungen | |
DE102012106175A1 (de) | Strukturierte schleifend abtragbare Beschichtungen für Oberflächen stationärer Dampfturbinenkomponenten | |
EP1898054B1 (fr) | Turbine a gaz | |
EP2647795B1 (fr) | Système d'étanchéité pour turbomachine | |
EP2132414B1 (fr) | Agencement en feuillure | |
DE102004024683A1 (de) | Dichtungssystem für horizontale Verbindungsstellen von Zwischenböden von Dampfturbinen | |
EP1320662A1 (fr) | Systeme de garniture d'etancheite | |
DE3148985C2 (de) | Rotorbaugruppe | |
DE102014117262A1 (de) | L-Bürstendichtung für Turbomaschinenanwendungen | |
DE3503423A1 (de) | Verdichter fuer eine axialstroemungsmaschine | |
EP1747349A1 (fr) | Aube de turbomachine munie d'un anneau de renforcement et d'une baguette d'etancheite a poids optimise | |
EP2647796A1 (fr) | Système d'étanchéité pour turbomachine | |
WO2008074633A1 (fr) | Turbo machine, en particulier turbine à gaz | |
EP2811117A2 (fr) | Anneau de renforcement pour une turbomachine | |
EP2860356B1 (fr) | Turbomachine | |
EP3056684B1 (fr) | Bague intérieure séparée axialement pour une turbomachine, un stator et groupe motopropulseur | |
EP3401503A1 (fr) | Dispositif rotor d'une turbomachine | |
EP3514333B1 (fr) | Carénage d'extrémité d'aube de rotor pour une turbomachine, aube de rotor, procédé de fabrication d'un carénage d'extrémité d'aube de rotor et aube de rotor | |
EP3521562B1 (fr) | Aube d'une turbomachine | |
EP2410215A1 (fr) | Joint à brosse pour turbomachine | |
EP0894945A2 (fr) | Turbine et aubage de turbine | |
DE10305899A1 (de) | Dichtungsanordnung zur Dichtspaltreduzierung bei einer Strömungsrotationsmaschine |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
AX | Request for extension of the european patent |
Extension state: BA ME |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE |
|
17P | Request for examination filed |
Effective date: 20181102 |
|
RBV | Designated contracting states (corrected) |
Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: EXAMINATION IS IN PROGRESS |
|
17Q | First examination report despatched |
Effective date: 20200131 |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: GRANT OF PATENT IS INTENDED |
|
INTG | Intention to grant announced |
Effective date: 20200828 |
|
GRAJ | Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted |
Free format text: ORIGINAL CODE: EPIDOSDIGR1 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: EXAMINATION IS IN PROGRESS |
|
INTC | Intention to grant announced (deleted) | ||
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: GRANT OF PATENT IS INTENDED |
|
INTG | Intention to grant announced |
Effective date: 20210115 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE PATENT HAS BEEN GRANTED |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: EP |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R096 Ref document number: 502017010656 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: REF Ref document number: 1402481 Country of ref document: AT Kind code of ref document: T Effective date: 20210715 |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: FG4D Free format text: LANGUAGE OF EP DOCUMENT: GERMAN |
|
REG | Reference to a national code |
Ref country code: LT Ref legal event code: MG9D |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: BG Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20210916 Ref country code: HR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20210616 Ref country code: FI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20210616 Ref country code: LT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20210616 |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: MP Effective date: 20210616 |
|
REG | Reference to a national code |
Ref country code: ES Ref legal event code: FG2A Ref document number: 2881326 Country of ref document: ES Kind code of ref document: T3 Effective date: 20211129 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: NO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20210916 Ref country code: SE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20210616 Ref country code: RS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20210616 Ref country code: LV Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20210616 Ref country code: GR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20210917 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: CZ Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20210616 Ref country code: EE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20210616 Ref country code: NL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20210616 Ref country code: PT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20211018 Ref country code: RO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20210616 Ref country code: SM Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20210616 Ref country code: SK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20210616 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: PL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20210616 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 502017010656 Country of ref document: DE |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20210616 |
|
26N | No opposition filed |
Effective date: 20220317 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: AL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20210616 |
|
REG | Reference to a national code |
Ref country code: BE Ref legal event code: MM Effective date: 20211031 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MC Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20210616 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LU Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20211027 Ref country code: IT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20210616 Ref country code: BE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20211031 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LI Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20211031 Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20211031 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20211027 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: HU Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO Effective date: 20171027 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: CY Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20210616 |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MM01 Ref document number: 1402481 Country of ref document: AT Kind code of ref document: T Effective date: 20221027 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20231025 Year of fee payment: 7 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: ES Payment date: 20231117 Year of fee payment: 7 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: AT Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20221027 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20231023 Year of fee payment: 7 Ref country code: DE Payment date: 20231018 Year of fee payment: 7 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20210616 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: TR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20210616 |