EP2132414B1 - Agencement en feuillure - Google Patents

Agencement en feuillure Download PDF

Info

Publication number
EP2132414B1
EP2132414B1 EP08718171.5A EP08718171A EP2132414B1 EP 2132414 B1 EP2132414 B1 EP 2132414B1 EP 08718171 A EP08718171 A EP 08718171A EP 2132414 B1 EP2132414 B1 EP 2132414B1
Authority
EP
European Patent Office
Prior art keywords
mass flow
fuel
flow
fuel mass
gap
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP08718171.5A
Other languages
German (de)
English (en)
Other versions
EP2132414A1 (fr
Inventor
Thomas Heinz-Schwarzmaier
Ulrich Rathmann
Carlos Simon-Delgado
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP2132414A1 publication Critical patent/EP2132414A1/fr
Application granted granted Critical
Publication of EP2132414B1 publication Critical patent/EP2132414B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • 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
    • F05D2240/57—Leaf seals

Definitions

  • the present invention relates to an arrangement between blade elements in a blade row in a gas turbine according to the preamble of claim 1.
  • Turbine blades in particular low-pressure turbine blades, usually have radially inside and / or outside at least one shroud element which, when the blade row is mounted, adjoins the respectively adjacent shroud element of the respectively adjacent blade element, forming a substantially radial gap.
  • a turbine blade element may at at least one axial edge, in particular the trailing edge, projecting on a first circumferentially facing side into the shroud element of the adjacent blade element protruding in the circumferential direction projection and on a second circumferentially facing side Having this projection receiving recess.
  • Such a Shiplap comes about by covering a recess on a first circumferentially facing side of an adjacent blade element by a projection on the second circumferentially facing side of a blade element or by the engagement of the projection in the recess.
  • a projection as well as a recess and the stepped overlapping or engagement area resulting during assembly are shown.
  • the known regular Shiplap but can not completely seal the radial gap, which is why a significant amount of cooling air can escape through the stepped overlap region. This loss results in reduced turbine efficiency and performance.
  • each blade element has at least one shroud element, as well as an adjacent to this shroud element and connected thereto, extending substantially in the radial direction with respect to a main axis of the blade row airfoil.
  • the shroud element adjoins with mounted blade row with the two circumferentially facing sides to the respective adjacent shroud element of the respective adjacent blade element, forming a respective substantially radial gap.
  • At least one blade element on a first circumferentially facing side has a circumferentially extending projection projecting into the shroud element of the adjacent blade element and at least one blade element has a recess receiving such a projection on a second side pointing in the circumferential direction.
  • a stepped portion of the radial gap In the region of the projection or the recess there is a stepped portion of the radial gap, wherein the guide of the radial gap in the stepped portion is designed as a labyrinth seal.
  • Out EP 1 221 539 A2 shows a partitioned wall structure in a gas turbine having a plurality of partial wall sections which are connected in the circumferential direction of a rotor of the gas turbine so as to form the wall structure with a substantially circular cross-section.
  • the wall portions are fixed to an outer end or an inner end of a respective blade of the gas turbine or arranged with a predetermined gap between the outer end of the respective blade to form a passage wall for high-temperature gas together with a blade surface of the respective blade, wherein column or Gaps are provided between adjacent connected wall sections.
  • the gas turbine engine shroud features a plurality of shroud segments and sealing fins, wherein the shroud segments are coupled to form a cylindrical shape by inserting one end portion of a sealing fin into a connecting portion of two adjacent shroud segments.
  • the connecting portion has such a shape that the inside end portion of a shroud segment protrudes circumferentially as compared with the outside end portion.
  • a first cladding segment adjacent to a second cladding segment has a connecting portion whose shape is complementary to the shape of the connecting portion of this cladding segment and the adjacent cladding segments are coupled such that there is a specific gap therebetween, with a perforating hole (2) a cooling air amount is provided in the connecting portion of the shroud segment.
  • Out GB 2 166 805 A shows a gas turbine, which has an annular flow path for working gases, a flow path for cooling fluid, which is arranged radially opposite to the flow path of the working gases.
  • a plurality of arcuate seal segments extend circumferentially about the axis, wherein at least a pair of seal segments define a first seal portion and a second seal portion circumferentially spaced from the first seal segment, thereby creating a groove which is variable in light of the operating conditions is designed.
  • the invention is therefore based on the object, an improved Arrangement to provide, which has an improved sealing effect compared to the known from the prior art Shiplaps and thus reduces the leakage flow from the secondary air circuit.
  • the core of the invention thus consists in providing a labyrinth seal between two adjacent shrouds of a blade element.
  • a labyrinth seal is understood to mean either a substantially zig-zag overlay or engagement region of two adjacent shroud elements on turbine blades with more than two directional changes of the radial gap, or a superposition respectively engagement region, which is the synergistic one Effect of tapering and widening of the gap on the vortex formation of the air in the gap, or a superposition respectively engagement area of two adjacent shroud elements on turbine blades, having a design which incorporates a combination of the two principles.
  • Labyrinth seals have hitherto been used only between two relatively movable parts, such as a stator element and a rotor element.
  • the DE 39 40 607 and the US 5,222,742 disclose labyrinth sealing systems between rotating and stationary parts of a gas turbine.
  • a labyrinth system results from the engagement of staggered long teeth in a stator seal member and staggered recesses in the rotor seal member, as well as staggered short teeth of the rotor seal member with staggered recesses of the stator seal member.
  • the geometry and inclination of the teeth is varied, which leads to cracks that increase the kinetic energy of the teeth Throttle by varying flow of gas or steam.
  • the WO 2005/028812 A1 discloses an array of stacked labyrinth seals to reduce the leakage current between fixed and rotating components, namely a segmented inner ring for supporting vanes in a stationary gas turbine.
  • the present invention transfers in a non-obvious way the principle of the stepped labyrinth seal on the problem of sealing a gap between shrouds of adjacent blade elements against leakage current, in particular in connection with a Shiplap.
  • the radial gap in the stepped region has at least one section in which the gap flow direction (S) runs counter to the direction of flow (A), according to the characterizing part of claim 1.
  • a first embodiment of the labyrinth seal is characterized in that an arrangement is provided between blade elements in a row of blades in a gas turbine, wherein each blade element has at least one shroud element, as well as an adjacent to this shroud element and connected thereto, substantially in the radial direction with respect a main axis of the blade row extending airfoil.
  • the shroud element adjoins the respectively adjacent shroud element of the respectively adjacent blade element with the blade row mounted with the two sides pointing in the circumferential direction, forming in each case a substantially radial gap.
  • At least one blade element has, on a first side pointing in the circumferential direction, a circumferential direction projecting into the shroud element of the adjacent blade element extending projection and at least one blade element on a second side facing in the circumferential direction on a such a projection receiving recess.
  • the guide of the radial gap in the stepped portion ie the Shiplap area, designed as a labyrinth seal.
  • the radial gap in the stepped area more than two changes in direction, in particular four, six, or eight changes in direction.
  • a change in direction is essentially a change in the gap current direction by 40 to 130 degrees, preferably by 60 to 110 degrees, particularly preferably substantially 80 to 100 degrees, but essentially understood in particular in the case of angular edge surfaces of the radial gap of about 90 degrees.
  • the gap flow direction is defined as essentially always parallel to the shroud surface extending direction of the air flow in the radial gap, the air coming from the leading edge ago initially flows in the axial direction to the trailing edge, after a change in direction but quite well chamfered or can flow transversely to the direction of flow. In the case of rounded edge surfaces, it may well be preferable to provide direction changes of 40-80 degrees, or of 110-130 degrees.
  • a change in direction has the purpose of diverting the gap flow of the air, which has unintentionally passed from the cooling air area into the radial gap, such that a pressure reduction takes place within the step, an additional flow resistance occurring within the step.
  • eddies form in the cooling air, in particular during the Passage through tapered gap sections. These vortices are deflected at a next change of direction and migrate, since they can not enter the next gap section. Whirls that do not migrate in a direction opposite to the split flow dissolve at least partially when they enter an extended region of the gap.
  • the cooling air itself prevents itself from moving in a uniform flow with high mass flow.
  • less cooling air exits the radial gap at the axial edge.
  • the radial gap in the shiplap region has angular and / or rounded edge surfaces. This means that when the direction changes, the individual sections can become angular or round at a certain angle.
  • the edge surfaces may be concave and / or convex, and / or straight.
  • the radial gap undergoes two equidirectional direction changes successively during its course in the stepped area.
  • the radial gap has a zigzag shape in the stepped overlapping or engagement region.
  • An arrangement with such a zigzag geometry of the radial gap can have at least one section in the stepped area, in which the gap flow direction runs counter to the direction of flow.
  • the radial gap in the stepped area has at least one taper and / or at least one extension.
  • a portion of the radial gap with such an extension may be at least 30% more, preferably at least 50% more than the width of the radial gap, or as the flow area at entering the stepped portion and may even be twice as large as the Flow cross section when entering the stepped area.
  • the width of the radial gap or the flow cross section is 75% -50%, preferably 50% -25% of the gap width when entering the stepped area.
  • an extension and / or a taper may be arranged before and / or after a change of direction.
  • an extension in the gap current direction of the air is arranged in the radial gap after a taper.
  • the range of directional change i. the region where the edge surfaces of the radial gap adjoin one another at a certain angle round or angularly or merge into one another, can be configured as an extension or taper compared to the inlet region of the air in the stepped region.
  • such areas of change of direction have rounded triangular areas (seen from above with respect to the plane of the shroud surface).
  • Another preferred embodiment of the present invention is a blade row of a gas turbine with an arrangement according to one of the previously described embodiments.
  • the radial gap between two adjacent shroud elements on the shroud underside is covered by a sealing sheet.
  • This sealing sheet impedes the entry of air from the cooling air area into the radial gap and thus initially minimizes the amount of air that is to be prevented by the inventive Shiplap arrangement at the exit from the gap, as they prevented by the sealing plate as possible at the entrance to the gap should be.
  • Other gasket variants as an alternative to the gasket sheet are not excluded here.
  • FIG. 1a shows an array of turbine blades as a rolled portion of a blade row in a plan view of the shroud surface 23, wherein three juxtaposed blade elements are shown.
  • a blade element 1 has a shroud element 13, as well as a shroud blade 9 adjacent to and connected to this shroud element 13 and extending essentially in the radial direction with respect to a main axis of the blade row.
  • the main axis of the blade row is that axis about which the shovel row is mounted defined circular cylinder is formed.
  • the main axis of the blade row represents the axis about which the circularly cylindrical blades rotate.
  • the airfoil 9 has an axially front blade leading edge 14 and an axially rear blade trailing edge 15.
  • the blade leading edge 14 is in the direction of flow A of the first axial edge and the leading edge 11 ago flows around first by the air flow of working medium flowing in the working medium range R working fluid.
  • the working medium then flows around the blade 9 and leaves it at the blade trailing edge 15 in the direction of the second axial edge or outflow edge 12.
  • the shroud element 13 adjoins the respective adjacent shroud element 13 of the respectively adjacent blade element 1 with the blade rows mounted with the two sides 4, 5 pointing in the circumferential direction U, forming a substantially radial gap 3 FIG. 1a the vane elements 1 are each shown with only one shroud element 13. However, it is conceivable that the blade elements 1 have both a radially inner and a radially outer shroud element 13.
  • Each blade element 1 has in the circumferential direction U a first, in the mounting direction M facing side 4 and a second, opposite to the mounting direction M facing page 5.
  • the first, pointing in mounting direction M peripheral side 4 of a mounted blade element 1 comes to rest by mounting a next blade element 1 to the second, opposite to the mounting direction M facing peripheral side 5 of the next mounted blade element 1.
  • the first mounted blade element 1, labeled with '1', as well as all the following blade elements 1, have a projection 6 pointing forwardly in the mounting direction M on an axial edge 12 on a first side 4 pointing in the circumferential direction U.
  • the projection 6 extends in the circumferential direction U and into the circumferential direction U Shroud element 13 of the adjacent blade element 1 protrudes.
  • the width B of the projection 6, Measured in the radial direction, a maximum of 40%, preferably not more than 20%, particularly preferably 5-15%, the overall depth T of a blade element 1.
  • the depth T is defined by the axial distance between the leading edge 11 and the trailing edge 12 of the blade element. 1
  • the projection 6 is to be understood as an offset in the circumferential direction U over a part of the axial course of a peripheral side 4 of a blade element 1.
  • the projection 6 defines, with respect to the longitudinal axis L of an airfoil 9 between two adjacent mounted airfoil elements 1, a radial gap 3 stepped in a plane defined by the shroud surface 23 extending in a radial plane E between the adjacent sides 4, 5 of the individual airfoils Blade elements of the axial leading edge 11 of a blade element 1 to the axial trailing edge 12 extends.
  • the juxtaposition of the blade elements 1 results in a stepped overlap or engagement region 2 between the shrouds of adjacent blade elements, whereby the radial gap 3 is sealed against the escape of cooling air. Without such a stepped arrangement 2, the air which has fallen into the radial gap 3 would escape unhindered from the opening 8 at the axial outflow edge 12 and thus be lost to the system.
  • FIG. 1b shows a schematic detail view of a stepped overlap region according to the prior art.
  • the resulting by the superposition of the shrouds of the two adjacent blade elements zigzag shape of the radial gap 3 can be seen.
  • Such an arrangement with two changes in direction deflects the cooling air from the cooling air area into the radial gap 3 and contributes to the reduction of the leakage flow at the trailing edge of the blade elements.
  • the conventional Shiplap according to the illustration therefore has two changes of direction in the region of an angle ⁇ of substantially 90 Degree on, with respect to the course of the radial gap 3.
  • Such a stepped overlap region according to the prior art has a substantially constant gap width in the entire course of the radial gap in the stepped portion.
  • FIG. 2 is the in FIG. 1a designated area 10 between two adjacent blade elements 1 at a first axial edge or leading edge 11 in a section perpendicular to the main axis of the blade row along in FIG. 1a designated line CC shown schematically. Shown is a section of two adjacent shroud elements 13 with their associated blades 9. In the figure, below the shroud elements 13, the cooling air area K is shown, and between the two blades 9, the area R of the working medium, characterized by the flow direction of the working medium A. The entrance of cooling air in the extending between the two cover sheets 13 radial gap 3 and the axial distribution of air in the radial gap 3 is made difficult in this embodiment by a sealing plate 17.
  • the sealing plate 17 for sealing the radial gap 3 is in each gap 24 or step of two adjacent shrouds in the circumferential direction U of the shroud underside, or engages in these steps or recesses 24 and extends in its length along the radial gap 3 parallel to a plane defined by the shroud surface level to the stepped portion 2 at the trailing edge 12 of the shroud element 13.
  • this sealing plate 17 has the function to intercept the radial component of the leakage flow, ie the radial Entry of cooling air from the cooling air area K in the radial gap 3 and thereby to prevent the first step to propagate the gap flow in the axial direction.
  • this sealing sheet 17 does not completely cover the radial gap in the radial direction in the stepped region of the shiplap, which is why relatively much cooling air can still enter the radial gap 3 from the cooling air region K in the shiplap region 20. In the present invention, it is therefore, inter alia, to minimize the escape of the despite the sealing means, such as here the sealing plate 17, in the radial gap 3 advised air from the radial gap 3 addition.
  • FIG. 3 shows various preferred embodiments of designed as labyrinth seals Shiplap arrangements, as a schematic representation of the in FIG. 1a designated section 20.
  • Shiplaps with only a single gradation each Shiplaps with a multi-level labyrinth seal according to the invention shown, for example, with 4 changes in direction, but this does not exclude the presence of other labyrinth stages, ie 2 and more additional direction changes.
  • the labyrinth seal sections of the radial gap 3 which run parallel or bevelled to the flow direction A alternate with those sections which are arranged transversely to the direction of flow A.
  • FIG. 3a shows a zigzag shape of the radial gap 3 in the stepped portion 2.
  • the zigzag shape of the gap 3 is achieved by two clockwise direction changes following two counterclockwise direction changes. This could alternatively be the other way around be the case.
  • the present embodiment has four changes in direction of the radial gap 3, of which the first two direction changes seen from the leading edge 11 to the trailing edge 12 in the counterclockwise direction, and the next two are arranged in a clockwise direction.
  • the air flows in the radial gap first parallel to the flow direction A, whereupon it flows for a portion transverse to the flow direction A, then opposite to the flow direction A, and then again flows transversely thereto, before it allows the geometry of the radial gap 3 again to flow in flow direction A.
  • the gap flow S of the cooling air coming from the leading edge 11 and directed towards the outflow edge 12 occurs essentially parallel to the direction of flow A into the stepped area 2.
  • the cooling air is deflected by about 90 degrees counterclockwise twice to then undergo a clockwise direction change of about 90 degrees twice before that cooling air which, despite the stepped arrangement as a labyrinth seal, does not prevent it from flowing to the trailing edge 12 was exiting at the trailing edge 12 from the radial gap 3.
  • the FIG. 3a illustrated preferred embodiment has straight edge surfaces 21 which are adjacent to each other at certain angles ⁇ .
  • the edge surfaces 21 could also border on each other by concave or convex edge surface shapes, so to speak under "round corners". It is also conceivable that the radial gap 3 in this arrangement could have changes in direction of other angular sizes ⁇ .
  • FIG. 3b illustrated embodiment of a labyrinth seal also shows a in the stepped area 2 exclusively of straight edge surfaces 21 existing radial gap 3.
  • the areas of change in direction are formed in this embodiment, all square.
  • the split flow S of the cooling air occurs after entering the stepped portion 2 parallel to the direction of flow A at the first change in direction, which is approximately 90 degrees counterclockwise, in a tapered gap 18, whereupon the gap current by about 90 degrees in a clockwise direction in a extended area 19 is deflected and then in turn counterclockwise about 90 degrees in a constriction area 18 is deflected to then still a deflection by about 90 degrees in the counterclockwise direction, before the air after two more, substantially 90- directional changes in direction clockwise to the outlet opening 8 at the trailing edge 12 of the blade element 1 passes.
  • Figure 3c is, as already in FIG. 3b , a labyrinth seal shown, in which the radial gap 3 in the transverse to the flow direction A arranged straight edge surfaces 21 is narrower than in the parallel to the flow direction A arranged -Rand vom 21.
  • the stepped portion eight changes in direction, wherein in the Spaltstromcardi S first Two direction changes are arranged in the counterclockwise direction, followed by two clockwise direction changes, then two counterclockwise direction changes and finally two clockwise direction changes.
  • the first turn of the counterclockwise direction is essentially 60-70 degrees.
  • the second direction change in the counterclockwise direction is about 100-110 degrees, as well as the next, arranged in a clockwise direction change of the radial gap 3.
  • the subsequent change in direction clockwise is again about 60-70 degrees, as well as the subsequent change in direction counterclockwise.
  • This is followed by one Direction change counterclockwise by about 100-110 degrees and then two clockwise direction changes, of which the first is also about 100-110 degrees, and the second is about 60-70 degrees.
  • the radial gap 3 has here, as shown, two successive upward (in the direction of flow) and two open at the bottom angular U-shaped sections.
  • the zigzag shape of the labyrinth seals with more than two direction changes, as in FIGS. 3a-c are characterized, inter alia, by the fact that the gap flow S of the cooling air is forced according to the geometry of the labyrinth seal within the radial gap 3 in sections in a direction opposite to the total flow direction A and that the gap current S undergoes strong turbulence in the course of the stepped portion 2 wherein the quotient between the flow area or width of the radial gap in a taper and the flow area in the area following the taper affect the degree of turbulence.
  • edge surfaces 21 can run parallel to the direction of flow A, transversely thereto or obliquely thereto, ie angled relative to the direction of flow.
  • These edge surfaces 21 may be flat respectively straight, or rounded, either convex, ie formed as bulges in the radial gap or concave, ie as spacers from the radial gap 3 in the shroud element 13 into it.
  • the edge surfaces 21 may adjoin one another angularly and / or along rounded edge surfaces 21 at specific angles.
  • 3d figure shows an embodiment of a labyrinth seal, which has only two changes in direction, but in comparison to a simple Shiplap in addition to the two changes in direction of the radial gap 3 each having a region with an extension 19 and a taper 18 in the radial gap 3.
  • Such a sequence of extension 19 in the direction of change of direction, followed by a tapered gap section 18 or vice versa also acts on the gap flow in a rate-throttling manner, which is desirable for the purpose of minimizing the leakage current.
  • the two changes in direction one of which is counterclockwise and the second is clockwise, are both substantially approximately 90 degrees.
  • the region of the first change of direction in the stepped region 2 is represented as a "rounded corner” or rounded expanded triangular region, while the second direction change region is designed as a conventional corner.
  • An extension 19 is defined as a section of the radial gap 3 in the stepped region 2, in which the width of the radial gap 3, ie the flow cross-section, at least 30% more, preferably at least 50% more than the gap width D, or even twice as large is.
  • a taper 18 is defined as a section of the radial gap 3 in the stepped region 2, in which the width of the radial gap 3, or the flow cross-section, is 50%, preferably 25-50% of the gap width D.
  • the ratio between the gap width D and the width of the gap ie the quotient between the width of the gap in the taper 18 and the gap width D at the entrance of the radial gap 3 in the stepped portion 2 substantially between 1: 2 and 1: 4, but possibly up to 1: 8.
  • the labyrinth seal after the in FIG. 3e illustrated embodiment has a majority of rounded edge surfaces 21.
  • air in the gap flow S from the leading edge 11 in the direction of the trailing edge 12th Seen through a conical taper 26 shown in this embodiment flows into the stepped portion 2, it passes into an extended triangular region 25 with rounded edge surfaces 21, at the radial gap 3 bounding edge surfaces 21 of the air flow is significantly deflected and swirled, here by ca 130 degrees in the counterclockwise direction, before being urged by a direction change clockwise by about 50-60 degrees in a direction transverse to the direction of flow A of the blade elements 1 arranged tapered portion 18 of the radial gap 3.
  • the cooling air flow flowing in the radial gap 3 undergoes a deflection of approximately 40-50 degrees in a clockwise direction into a second extension 19, in order then again to undergo a counterclockwise deflection of approximately 50-60 degrees into a rejuvenated gap region 18 before it can escape from the radial gap 3 at about 70-85 degrees clockwise at the trailing edge 12 after another deflection.
  • the edge surfaces 21 bounding the radial gap 3 are angularly adjacent to each other via two changes of direction, while the radial gap 3 in the adjoining area of the stepped area 2 also has rounded adjacencies when the direction changes the edge surfaces 21 has.
  • the radial gap 3 in the in FIG. 3f The labyrinth seal shown has a substantially uniform width D in a first half in relation to the direction of the gap flow S, while the second half has first along a flat surface a narrowed area 18 compared to the first labyrinth step and then an extension 19.
  • gap current S is initially only slightly deflected at an angle ⁇ of about 30 degrees counterclockwise before he for the purpose of vortex formation and speed throttling a significant deflection of substantially 90 degrees in Counterclockwise, then steered clockwise a significant 130-140 degrees in a next section of the radial gap 3, and then again turn about 130-140 degrees, but this time counterclockwise, in a tapered gap region 18, which is substantially transversely to the direction of flow A, is forced to then expand in a conical enlargement 27 by an angle ⁇ of about 50-70 degrees again in a rounded triangular region 25, at the rounded edge surfaces 21 of the air flow to about 50-70 degrees to Outlet at the second axial edge or the trailing edge 12, is guided.
  • FIG. 4 two contour representations of the absolute values of the flow velocities of the cooling air in the radial gap 3 in the stepped area 2 are shown.
  • the figure shows in a 2D CFD representation calculation results of examinations of a first labyrinth seal ( Fig. 4a ) as defined in 3d figure illustrated embodiment, in comparison to a still further improved labyrinth seal ( Fig. 4b ).
  • the marked areas 22, 28 are defined by their flow velocity.
  • the region 22 is defined as a high flow velocity region because the flow velocity is higher than that of the air flow during entry into the stepped region 2.
  • the entrance region into the stepped region 2 belongs to the region as well as the region of exit from the stepped region 2 28, which thus has a lower flow velocity than the region 22 Fig.
  • the regions 28 have a flow velocity that is substantially twice as high as the flow velocity in said regions 28 of FIG Fig. 4b illustrated embodiment.
  • Fig. 4a has only one region 22 with high flow velocity.
  • the arrangement shown has three such regions 22 with high flow velocity, in which the cooling air has a higher flow velocity than the inlet velocity in the radial gap having.
  • the flow velocity achieved in these areas however, in comparison to that in FIG. 4a designated area 22 about half as large flow velocities.
  • Both the lower limit and the upper limit of the flow velocity in the designated area 22 of FIG Fig. 4a is substantially about twice the corresponding lower limit or upper limit of said areas 22 of Fig.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)

Claims (15)

  1. Procédé de fonctionnement d'un ensemble turbine à gaz (1) comprenant le fait de comprimer un débit massique d'air dans un compresseur (11), d'introduire le débit massique d'air comprimé dans une première chambre de combustion (12), de brûler un premier débit massique de carburant dans la première chambre de combustion dans le débit massique d'air comprimé, de détendre le gaz chaud se formant dans une première turbine (13), d'introduire le gaz chaud partiellement détendu dans une deuxième chambre de combustion (14), et de brûler un deuxième débit massique de carburant dans la deuxième chambre de combustion dans le gaz chaud partiellement détendu, lequel procédé comprend en plus le fait d'amener à l'ensemble turbine à gaz le premier débit massique de carburant et le deuxième débit massique de carburant avec une pression d'alimentation de carburant et de spécifier à l'avance la répartition d'un débit massique total dans le premier et le deuxième débit massique de carburant conformément à un concept de fonctionnement normal, caractérisé par le fait de s'écarter de la répartition conformément au concept de fonctionnement normal lors du dépassement inférieur d'une valeur limite d'au moins une des pressions d'alimentation de carburant et de réduire le premier débit massique de carburant d'un débit massique différentiel par rapport au concept de fonctionnement normal et d'augmenter le deuxième débit massique de carburant d'au moins le débit massique différentiel.
  2. Procédé selon la revendication 1, caractérisé en ce que le procédé comprend en plus le fait d'amener à l'ensemble turbine à gaz le premier débit massique de carburant et le deuxième débit massique de carburant dans un conduit d'alimentation commun (50) avec une pression d'alimentation de carburant, de s'écarter de la répartition conformément au concept de fonctionnement normal lors du dépassement inférieur d'une valeur limite de la pression d'alimentation de carburant dans le conduit d'alimentation commun et de réduire le premier débit massique de carburant d'un débit massique différentiel par rapport au concept de fonctionnement normal, et d'augmenter le deuxième débit massique de carburant d'au moins le débit massique différentiel.
  3. Procédé selon la revendication 1 ou 2, pour lequel le concept de fonctionnement normal comprend le fait de spécifier à l'avance la répartition du débit massique total en fonction du rendement de puissance utile (Pact) de l'ensemble turbine à gaz.
  4. Procédé selon l'une quelconque des revendications 1, 2 ou 3, comprenant la détermination de la température d'entrée du gaz chaud lors de l'entrée dans la première turbine (13) pour la répartition du débit massique total, l'attribution à la première chambre de combustion (12) du premier débit massique de carburant de telle sorte que la température d'entrée atteigne une valeur limite supérieure admissible et l'attribution de la part en excès du débit massique total à la deuxième chambre de combustion (14) en tant que deuxième débit massique de carburant.
  5. Procédé selon l'une quelconque des revendications précédentes, caractérisé par le fait de régler le débit massique total de telle sorte que le rendement de puissance utile de l'ensemble turbine à gaz corresponde à une valeur théorique.
  6. Procédé selon l'une quelconque des revendications précédentes, comprenant le fait de définir la valeur limite de la pression d'alimentation de carburant en fonction du rendement de puissance utile de l'ensemble turbine à gaz.
  7. Procédé selon l'une quelconque des revendications précédentes, caractérisé par le fait de mesurer directement la pression d'alimentation de carburant.
  8. Procédé selon l'une quelconque des revendications précédentes, caractérisé par le fait de définir le débit massique différentiel en fonction de la différence entre la valeur limite de pression et la pression d'alimentation effective, pour lequel plus la pression d'alimentation effective est faible, plus le débit massique différentiel est grand.
  9. Procédé selon l'une quelconque des revendications précédentes, caractérisé par le fait d'adapter la répartition de carburant interne de la première chambre de combustion en fonction de la variation du premier débit massique de carburant.
  10. Procédé selon l'une quelconque des revendications précédentes, caractérisé par le fait de maintenir constant le débit massique total, de réduire le premier débit massique de carburant du débit massique différentiel et d'augmenter le deuxième débit massique de carburant du débit massique différentiel.
  11. Procédé selon l'une quelconque des revendications 1 à 9, caractérisé par le fait de diminuer le premier débit massique de carburant du débit massique différentiel, d'augmenter le deuxième débit massique de carburant du débit massique différentiel et d'augmenter en outre le deuxième débit massique de carburant d'un autre débit massique de telle sorte que le rendement de puissance utile de l'ensemble turbine à gaz soit maintenu constant.
  12. Procédé selon l'une quelconque des revendications 1 à 9, comprenant le fait d'augmenter le rendement de puissance utile de l'ensemble turbine à gaz, d'augmenter le débit massique total, de répartir le débit massique total conformément à un concept de fonctionnement normal entre le premier débit massique de carburant et le deuxième débit massique de carburant et de ne pas augmenter encore le premier débit massique de carburant lors du dépassement inférieur de la valeur limite de la pression d'alimentation de carburant et d'attribuer l'augmentation du débit massique total nécessaire à la hausse du rendement de puissance utile dans sa totalité au deuxième débit massique de carburant.
  13. Module de commande (60) d'une installation de centrale électrique qui est configuré pour exécuter un procédé selon l'une quelconque des revendications précédentes.
  14. Code numérique qui est adapté pour être exécuté dans un module de commande (60) d'une installation de centrale électrique et, s'il est exécuté dans le module de commande d'une installation de centrale électrique, pour amener à cet effet le module de commande à faire fonctionner l'installation de centrale électrique conformément à un procédé selon l'une quelconque des revendications précédentes.
  15. Support de données (63) sur lequel est mémorisé un code numérique selon la revendication 14 et/ou le code source de celui-ci.
EP08718171.5A 2007-04-05 2008-03-25 Agencement en feuillure Active EP2132414B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH5722007 2007-04-05
PCT/EP2008/053482 WO2008122507A1 (fr) 2007-04-05 2008-03-25 Agencement en feuillure

Publications (2)

Publication Number Publication Date
EP2132414A1 EP2132414A1 (fr) 2009-12-16
EP2132414B1 true EP2132414B1 (fr) 2015-07-01

Family

ID=38474112

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08718171.5A Active EP2132414B1 (fr) 2007-04-05 2008-03-25 Agencement en feuillure

Country Status (4)

Country Link
US (1) US8303257B2 (fr)
EP (1) EP2132414B1 (fr)
ES (1) ES2548441T3 (fr)
WO (1) WO2008122507A1 (fr)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010063594A1 (de) * 2010-12-20 2012-06-21 Mtu Aero Engines Gmbh Dichtanordnung und Turbomaschine mit einer derartigen Dichtanordnung
US8600707B1 (en) * 2011-03-24 2013-12-03 Florida Turbine Technologies, Inc. Process for analyzing a labyrinth seal for flutter
US20130256996A1 (en) * 2012-03-28 2013-10-03 General Electric Company Shiplap plate seal
US20130315708A1 (en) * 2012-05-25 2013-11-28 Jacob Romeo Rendon Nozzle with Extended Tab
DE102013220467A1 (de) * 2013-10-10 2015-05-07 MTU Aero Engines AG Rotor mit einem Rotorgrundkörper und einer Mehrzahl daran angebrachter Laufschaufeln
US10107127B2 (en) * 2014-07-31 2018-10-23 United Technologies Corporation Gas turbine engine with axial compressor having improved air sealing
US9937575B2 (en) * 2015-02-05 2018-04-10 United Technologies Corporation Brazed joints and methods of forming brazed joints
DE102015203872A1 (de) * 2015-03-04 2016-09-22 Rolls-Royce Deutschland Ltd & Co Kg Stator einer Turbine einer Gasturbine mit verbesserter Kühlluftführung
US10443736B2 (en) * 2015-10-01 2019-10-15 United Technologies Corporation Expansion seal
US20180230839A1 (en) * 2017-02-14 2018-08-16 General Electric Company Turbine engine shroud assembly
EP3498980B1 (fr) * 2017-12-15 2021-02-17 Ansaldo Energia Switzerland AG Agencement de joint à feuillure
CN114320488A (zh) * 2021-10-20 2022-04-12 中国航发四川燃气涡轮研究院 航空发动机涡轮导向器叶片缘板的封严结构
CN117027966B (zh) * 2023-08-09 2024-04-05 秦皇岛华宇通电力科技有限公司 用于减少轴端汽封漏气量的u型齿扰流汽封装置

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3279802A (en) * 1964-03-10 1966-10-18 Douglas Aircraft Co Inc Control surface shaft seal
FR2552159B1 (fr) * 1983-09-21 1987-07-10 Snecma Dispositif de liaison et d'etancheite de secteurs d'aubes de stator de turbine
US4650394A (en) * 1984-11-13 1987-03-17 United Technologies Corporation Coolable seal assembly for a gas turbine engine
US5639095A (en) * 1988-01-04 1997-06-17 Twentieth Technology Low-leakage and low-instability labyrinth seal
US5029876A (en) * 1988-12-14 1991-07-09 General Electric Company Labyrinth seal system
GB2251040B (en) * 1990-12-22 1994-06-22 Rolls Royce Plc Seal arrangement
GB2259328B (en) * 1991-09-03 1995-07-19 Gen Electric Gas turbine engine variable bleed pivotal flow splitter
US5257908A (en) * 1991-11-15 1993-11-02 Ortolano Ralph J Turbine lashing structure
SE507745C2 (sv) * 1996-11-05 1998-07-06 Alfa Laval Ab Tätningsanordning
US5797723A (en) * 1996-11-13 1998-08-25 General Electric Company Turbine flowpath seal
JP3999395B2 (ja) * 1999-03-03 2007-10-31 三菱重工業株式会社 ガスタービン分割環
US6425738B1 (en) * 2000-05-11 2002-07-30 General Electric Company Accordion nozzle
JP2002201913A (ja) * 2001-01-09 2002-07-19 Mitsubishi Heavy Ind Ltd ガスタービンの分割壁およびシュラウド
JP4508482B2 (ja) * 2001-07-11 2010-07-21 三菱重工業株式会社 ガスタービン静翼
SE524351C2 (sv) * 2002-07-02 2004-07-27 Skf Ab Tätningsarrangemang
US6910854B2 (en) * 2002-10-08 2005-06-28 United Technologies Corporation Leak resistant vane cluster

Also Published As

Publication number Publication date
US20100119371A1 (en) 2010-05-13
US8303257B2 (en) 2012-11-06
WO2008122507A1 (fr) 2008-10-16
ES2548441T3 (es) 2015-10-16
EP2132414A1 (fr) 2009-12-16

Similar Documents

Publication Publication Date Title
EP2132414B1 (fr) Agencement en feuillure
EP2025945B1 (fr) Machine de traitement des écoulements dotée d'un creux de paroi de canal de ceinture
EP0916812B1 (fr) Etage final pour turbine axial
EP1632662B1 (fr) Turbomachine avec soutirage
EP1595058B1 (fr) Systeme de joint notamment destine a des segments d'ailettes de turbines a gaz
EP0528138B1 (fr) Anneau d'aube de turbine axiale
EP1766192B1 (fr) Roue a aubes d'une turbine presentant une aube et au moins un canal refrigerant
EP2179143B1 (fr) Refroidissement de fente entre une paroi de chambre de combustion et une paroi de turbine d'une installation de turbine à gaz
DE3940607A1 (de) Labyrinth-dichtungssystem
EP2300686B1 (fr) Turbine à gaz pourvue d'une aube directrice
CH704935B1 (de) Stator-Rotor-Anordnung, Strömungsmaschine und Verfahren zum Herstellen einer Struktur aus umgekehrten Turbulatoren
EP2299124A1 (fr) Aube de rotor pour un compresseur axial
DE102007027427A1 (de) Schaufeldeckband mit Überstand
DE102009044585A1 (de) Verfahren, Vorrichtung und Systeme bezüglich der Umfangsausrichtung von Turbinenschaufelblättern in Bezug auf Brennkammerrohre und den Kühlluftstrom durch den Turbinenheissgasströmungsweg
DE102004024683A1 (de) Dichtungssystem für horizontale Verbindungsstellen von Zwischenböden von Dampfturbinen
DE102014100087A1 (de) Innenaufbau einer Turbinenlaufschaufel
DE3148985C2 (de) Rotorbaugruppe
DE3503421C2 (de) Axialverdichter für eine Turbomaschine
EP2921714A1 (fr) Groupe de série d'aubes
EP3064706A1 (fr) Rangée d'aubes directrices pour une turbomachine traversée axialement
EP2538024A1 (fr) Aube dans une turbomachine
CH708768A2 (de) Verriegelnde Abstandshalteranordnung zur Einführung in einen umlaufenden Befestigungsschlitz zwischen Plattformen benachbarter Laufschaufeln.
EP0992656B1 (fr) Turbomachine pour comprimer ou détendre un fluide comprimable
EP2846000B1 (fr) Roue statorique d'une turbine à gaz
EP3078804A1 (fr) Agencement virole pour une rangée d'aubes de rotor ou stator et turbine associée

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

17P Request for examination filed

Effective date: 20090930

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR

DAX Request for extension of the european patent (deleted)
17Q First examination report despatched

Effective date: 20140926

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20150402

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK 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: AT

Ref legal event code: REF

Ref document number: 734083

Country of ref document: AT

Kind code of ref document: T

Effective date: 20150715

Ref country code: CH

Ref legal event code: EP

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: DE

Ref legal event code: R096

Ref document number: 502008013105

Country of ref document: DE

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2548441

Country of ref document: ES

Kind code of ref document: T3

Effective date: 20151016

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20150701

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

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: 20150701

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: 20150701

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: 20151002

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: 20150701

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: 20151001

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

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: 20151102

Ref country code: IS

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: 20151101

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: 20150701

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: 20150701

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: 20150701

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502008013105

Country of ref document: DE

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: 20150701

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: 20150701

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: 20150701

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: 20150701

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: 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: 20150701

26N No opposition filed

Effective date: 20160404

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502008013105

Country of ref document: DE

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH

Ref country code: DE

Ref legal event code: R081

Ref document number: 502008013105

Country of ref document: DE

Owner name: ANSALDO ENERGIA SWITZERLAND AG, CH

Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

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: 20150701

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160331

REG Reference to a national code

Ref country code: ES

Ref legal event code: PC2A

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH

Effective date: 20161021

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: 20150701

Ref country code: LU

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: 20160325

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20161130

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160331

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160331

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160331

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160325

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 734083

Country of ref document: AT

Kind code of ref document: T

Effective date: 20160325

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

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: 20150701

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: ES

Payment date: 20170315

Year of fee payment: 10

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20170727 AND 20170802

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

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: 20150701

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160325

REG Reference to a national code

Ref country code: ES

Ref legal event code: PC2A

Owner name: ANSALDO ENERGIA SWITZERLAND AG

Effective date: 20170925

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502008013105

Country of ref document: DE

Owner name: ANSALDO ENERGIA SWITZERLAND AG, CH

Free format text: FORMER OWNER: GENERAL ELECTRIC TECHNOLOGY GMBH, BADEN, CH

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: 20080325

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: 20150701

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: 20150701

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: 20150701

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20190911

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180326

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20230825

Year of fee payment: 16

Ref country code: GB

Payment date: 20230822

Year of fee payment: 16

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20230821

Year of fee payment: 16