WO2013013975A1 - Agencement de plan aérodynamique comprenant un élément d'étanchéité fait d'une mousse de métal - Google Patents

Agencement de plan aérodynamique comprenant un élément d'étanchéité fait d'une mousse de métal Download PDF

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Publication number
WO2013013975A1
WO2013013975A1 PCT/EP2012/063544 EP2012063544W WO2013013975A1 WO 2013013975 A1 WO2013013975 A1 WO 2013013975A1 EP 2012063544 W EP2012063544 W EP 2012063544W WO 2013013975 A1 WO2013013975 A1 WO 2013013975A1
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WO
WIPO (PCT)
Prior art keywords
airfoil
sealing element
edge side
root section
cavity
Prior art date
Application number
PCT/EP2012/063544
Other languages
English (en)
Inventor
Ulf Nilsson
Original Assignee
Siemens Aktiengesellschaft
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 Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2013013975A1 publication Critical patent/WO2013013975A1/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • 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
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/612—Foam

Definitions

  • Airfoil arrangement comprising a sealing element made of metal foam
  • the present invention relates to an airfoil arrangement for a gas turbine and to an airfoil system for a gas turbine.
  • the present invention relates to a method for sealing a gap between a first root section of a first airfoil device of a gas turbine and a second root section of a second airfoil device of a gas turbine.
  • airfoil devices are mounted in order to guide a working fluid through a gas turbine.
  • the airfoil devices may comprise blades which are mounted to a rotating turbine shaft or vanes which are mounted for example to a housing of the gas turbine.
  • the airfoil devices are mounted in a circumferential direction around the turbine shaft one after another. A gap may exist between adjoining airfoil devices such that leakage occurs. For this reason, a sealing arrangement is required between adjacent airfoil devices.
  • FIG. 6 illustrates a conventional sealing arrangement between two airfoil devices.
  • the conventional airfoil device 600 comprises a conventional airfoil 601 that is mounted to a conventional platform 606. At the opposed face of the
  • a conventional cavity 602 is formed. Through the conventional airfoil disk 610 cooling air may flow into the conventional airfoil 601, for example. Between the inner face of the conventional platform 606 and the conventional cavity 602, a conventional seal wire 603 is attached into an adapted groove inside the conventional platform 606. The conventional seal wire 603 is further attached to an adjacent further conventional platform of a further conventional airfoil device (not shown in Fig. 6) . A gap between the conventional platform 606 and the further adjacent conventional platform is sealed by the conventional seal wire 603.
  • the conventional airfoil device is mounted to a conventional airfoil disc 610.
  • a conventional lock strip 605 is used preventing the airfoil device from moving forward i.e. against the flow direction of the hot working gas.
  • a conventional seal strip 604 is mounted, wherein the conventional seal strip 604 is adapted for sealing a gap between a front face of the conventional airfoil device 600 and a further front face of a further adjoining conventional airfoil device.
  • the upstream face of the root of the airfoil device may have a tang that prevents the airfoil device from being pushed backwards i.e. in the flow direction of the hot working gas.
  • FIG. 7 shows a turbine rotor comprising two conventional airfoil discs 610 wherein each comprises a plurality of grooves that extend along a generally axial direction 102 of the gas turbine. The grooves are distributed one after another along a circumferential direction 103 of the
  • WO 2009/053169 Al shows a turbine blade assembly for a gas turbine, wherein a seal strip is mounted between a platform and a root cavity. The seal strip is further in contact with a locking plate for locking the airfoil to an airfoil disc.
  • WO 2008/046684 Al discloses a turbine blade assembly for a gas turbine. A seal strip is attached to a respective platform of adjacent turbine blades in order to minimize the leakage of hot working gas into the space under the
  • EP 1 600 606 Al discloses a turbine stage, wherein between platforms a seal strip is attached for providing a damping and a sealing of the adjacent blades.
  • EP 1 467 066 Bl discloses a corrugated seal.
  • An annular member comprises an S-shape profile wherein to a radially inwards extending portion of the annular member a lining is arranged which consists of metal foam, a porous sintered metal or a non-metallic material.
  • This objective is solved by an airfoil arrangement for a gas turbine, an airfoil system for a gas turbine and by a method for sealing a gap between a first root section of a first airfoil device and a second root section of a second airfoil device according to the independent claims.
  • an airfoil arrangement for a gas turbine comprises a first airfoil device, a second airfoil device and a sealing element.
  • the first airfoil device comprises a first root section with which the first airfoil device is mountable to an airfoil disc.
  • the first root section comprises a first platform, a first leading edge side and a first trailing edge side.
  • the first root section has a first cavity which is partially surrounded by the first platform, the first leading edge side and the first trailing edge side.
  • the second airfoil device comprises a second root section with which the second airfoil device is mountable to the airfoil disc.
  • the second root section comprises a second platform, a second leading edge side and a second trailing edge side.
  • the second root section has a second cavity which is partially surrounded by the second platform, the second leading edge side and the second trailing edge side.
  • the first airfoil device and the second airfoil device are mountable to the airfoil disc such that the first root section adjoins to the second root section and the first cavity and the second cavity form a common cavity.
  • the sealing element for partially sealing the common cavity is located inside the first cavity and the second cavity such that the sealing element covers a gap between the adjoining first root section and the second root section.
  • the sealing element comprises metal foam.
  • an airfoil system for a gas turbine is presented, wherein the airfoil system comprises an airfoil disc and the above- described airfoil arrangement.
  • the first airfoil device and the second airfoil device are mounted to the airfoil disc such that the first root section adjoins the second root section and the first cavity and the second cavity form the common cavity.
  • a method for sealing a gap between a first root section of a first airfoil device of a gas turbine and a second root section of a second airfoil device of the gas turbine comprises a first root section with which the first airfoil device is mountable to an airfoil disc.
  • the first root section comprises a first platform, a first leading edge side and a first trailing edge side.
  • the first root section has a first cavity which is partially surrounded by the first platform, the first leading edge side and the first trailing edge side.
  • the second airfoil device comprises the second root section with which the second airfoil device is mountable to the airfoil disc.
  • the second root section comprises a second platform, a second leading edge side and a second trailing edge side.
  • the second root section has a second cavity which is
  • the first airfoil device and the second airfoil device are mountable to the airfoil disc such that the first root section adjoins to the second root section and the first cavity and the second cavity form a common cavity.
  • the gap between the first root section and the second root section is covered by a sealing element for partially sealing the common cavity, wherein the sealing element is located inside the first cavity and the second cavity and wherein the sealing element comprises a metal foam.
  • the airfoil device comprises an airfoil which is e.g. a rotating blade for a gas turbine.
  • the airfoil extends from the platform of the airfoil device into the mainstream flow of the hot working gas.
  • the airfoil device comprises the root section which extends from the platform in opposite direction in comparison to the airfoil.
  • the root section of the airfoil device is mountable to the airfoil disc.
  • the airfoil disc is e.g. a blade carrier device.
  • the root section comprises the platform, the first leading edge side, the first trailing edge side and a mounting (bottom) section (which comprises e.g. a mounting plug which may be formed in a fir tree shape or a rail) .
  • the platform has a first surface which faces to a mainstream flow channel of the gas turbine and a second surface which faces to an opposite region of the platform in comparison to the first surface.
  • the airfoil such as a blade, is attachable to the first surface.
  • the platform extends generally along a circumferential direction and an axial direction of the gas turbine and/or a radial direction.
  • the thickness of the platform i.e. its extension along the normal of the surface, e.g. along the radial direction, is generally smaller in comparison to the other extensions, e.g. to the extensions along the axial and circumferential direction.
  • axial direction, circumferential direction and radial direction refer to directions with respect to a turbine shaft of the gas turbine.
  • the radial direction describes a run through a point of the rotating axis of the turbine shaft and the axial direction describes a run parallel to the rotating axis of the turbine shaft.
  • the axial direction and the radial direction are orientated in particular perpendicular with respect to each other .
  • the leading edge side and the trailing edge side are attached to the platform.
  • the leading edge side and the trailing edge side run from the second surface of the platform along a substantially radial direction.
  • the leading edge side is located more upstream with respect to the trailing edge side, wherein "upstream” and “downstream” describe a location of a part along a flow direction of the main stream of the working fluid of the gas turbine.
  • the platform, the trailing edge side and the leading edge side may form a U-shape inside of which the cavity is formed.
  • the above-described structure of the airfoil device is valid for the described first airfoil device, second airfoil device and any further airfoil device described in the present application.
  • the cavity may be flushed with cooling air, wherein the cooling air may be fed from the hollow airfoil or the blade root for cooling purposes.
  • the cavity may also be surrounded additionally by a bottom side which is connected to the trailing edge side and the leading edge side and which bottom side is located on the opposite side of the cavity in comparison to the second surface of the platform.
  • the radially outward facing part of the airfoil disc may be generally parallel to and may have an equal shape as the second side of the platform.
  • the outward facing part of the airfoil disc may form at least part of the bottom side which surrounds partially the cavity.
  • a plurality of airfoil devices are mounted adjacent to each other to the airfoil disc along the circumferential
  • the sealing element which may have a rectangular or oval cross section, is during operation in contact with the walls (leading edge sides, trailing edge sides, platform sides) of the first cavity and the second cavity.
  • the sealing element covers the gap and at least partially the first platform and the second platform.
  • protrusions e.g. casted on the side of the first and second platform in the cavity on the otherwise substantially flat surface that centres the sealing element and preventing it from circumferentially moving to one of the first airfoil device or the second airfoil device. This allows the width of the sealing element to be reduced generally or locally and thereby reducing the load from centrifugal force that the airfoil device has to carry during operation.
  • the sealing element comprises a metal foam.
  • a metal foam is a porous metallic structure which has a significantly reduced density compared to a solid metal piece of the same material.
  • a metal foam is a cellular structure consisting of a metal material containing a large volume fraction of gas-filled pores. The pores can be sealed (close-cell foam) or they can form an interconnection network (open-cell foam) .
  • the porosity or void fraction is a measure of the void spaces in a material, and is a fraction of the volume of voids over the total volume, i.e. between 0 - 1 or between 0 % - 100 % (percent) .
  • the porosity of the metal foam of the sealing element is approximately 75 % - 95%, i.e. 75 % - 95% of the volume consists of void spaces.
  • the strength of foamed metal possesses a power law relationship to its density, i.e. a 20% denser material is more than twice as strong as a 10% denser material.
  • Metal foam may be based on many different metals, such as aluminium or nickel.
  • a sealing element between two airfoil devices is used which is at least partially or completely made of a metal foam.
  • the sealing element is lighter than a sealing element made of a solid material.
  • a foam metal the stability of the seal element is not reduced dramatically in comparison to the solid metal.
  • the sealing element may be larger in
  • the sealing element may be self-supporting.
  • the sealing element is located inside the first cavity and the second cavity such that the sealing element abuts partially on the first platform, partially on the first leading edge side, partially on the first trailing edge side, partially on the second platform, partially on the second leading edge side and partially on the second trailing edge side.
  • the sealing element may comprise for example a U- shaped cross-section comprising two sides which are combined by a base section.
  • the sealing element may comprise for example a polygonal or an oval cross-section.
  • the U-shaped cross-section lies within a cross-section plane, wherein the normal of the cross-section plane runs along or is parallel to the circumferential direction.
  • the base section is alignable onto the respective platforms and the two sides are abuttable onto the respective leading edge sides and the respective trailing edge sides.
  • the angle of the sides of the sealing element with respect to the base section of the sealing element may be larger than the angle of the respective trailing edge sides and leading edge side sides to the platform.
  • the U-shaped sealing element may be clamped inside the cavity such that the sealing element forms a clamping fixation and a press-fit connection within the cavity of the respective airfoil device. Further fixation means are not necessary, i.e. there is no support underneath the seal in the direction of the thickness of the seal extending from the bottom surface (i.e. the airfoil disc surface) of the airfoil disc.
  • the sealing element By allowing the sealing element to cover for example the complete area of the leading edge side and trailing edge side of the root section and having support points between the respective adjacent leading edge sides and trailing edge sides of the adjacent airfoil device, a proper seal function and a good support/stability during assembly is achieved. Moreover, if the airfoil devices are rotating blade devices, centrifugal forces will press the sealing element against the respective (second surfaces of the) platforms such that a tight seal is achieved. During standstill of the gas turbine, the sealing element is kept in position by the clamping connection or a press-fit connection of the sealing element with the respective trailing edge sides and leading edge sides.
  • ends of the sealing element may rest on the airfoil disc face at the same time as the sealing element is partially in contact with, or close to, leading edge sides, trailing edge sides and platform sides, which in combination with the width of the sealing element prevents it from moving away from the gap.
  • each of the first platform, the first leading edge side, the first trailing edge side, the second platform, the second leading edge side and the second trailing edge side to which the sealing element abuts comprises a planar surface shape.
  • the sides may be formed planar, i.e. may be free of fixing means such as machined recesses, grooves or projections for fixing the sealing element.
  • the sealing element comprises a first section with a first porosity and a second section with a second porosity.
  • the second porosity is higher (i.e. comprises a higher fraction of the volume of voids over the total volume of a respective section) than the first porosity.
  • the sealing element is located inside the first cavity and the second cavity such that the first section of the sealing element covers the gap between the adjoining first root section and the second root section.
  • the sealing element may be provided with a reduced weight without losing its sealing characteristic and its stability. If the porosity is lower, the sealing element is denser, wherein if the porosity is higher, the sealing element has a lesser density and more air may possibly migrate through the foam metal material of the sealing element in case an open-cell foam is used. In
  • the section of the sealing element with the first porosity is located with the sealing element in a region where the gap occurs in order to provide a good sealing characteristic .
  • the sealing element comprises at least a cut-out section.
  • the sealing element does not have a continuous section with material but have also cut-outs (through-holes) , where material is taken away in order to reduce the weight of the sealing element.
  • the cut-out sections are located at regions of the sealing element where no high stresses and gaps exist.
  • the sealing element is coated with a corrosion protection coating, in particular with MCrAlY. Hence, corrosion of the sealing element may be reduced.
  • the sealing element comprises an (radial) end, wherein the airfoil disc comprises a groove or recess which is formed such that the end of the sealing element abuts inside the groove or recess.
  • the recess of the airfoil disc runs substantially along the circumferential direction of the gas turbine.
  • the recess may have a U-formed, V-shaped, square-shaped or rectangular- shaped cross-section, so that the recess is fully formed and machined in the airfoil disc.
  • the recess may also be machined in the airfoil disc such that the recess is formed by a ledge and has an L-form, squared-shape or rectangular-shaped cross- section. Hence, the edge (end) of the sealing element is placed inside the recess and the respective leading edge side or the trailing edge side presses the edge of the sealing element to the airfoil disc.
  • the recess can be formed in such a way, that the end (edge) of the sealing element is clamped inside the recess between the airfoil device and the airfoil disc.
  • the width of the recess is slightly smaller than the width of the end of the sealing element in order to achieve a clamping, press- fit connection of the end inside the recess.
  • the sealing element comprises a further (radial) end, wherein the further end comprises a seal lip which abuts onto the airfoil disc.
  • the sealing ability against fluids e.g. cooling fluids
  • the seal lip may extend from the sealing or trailing edge side of the airfoil disc inside the cavity, such that the pressure of the fluid inside the cavity presses the seal lip against the surface of the airfoil disc.
  • the seal lip is detachably mounted to the further end of the sealing element.
  • the seal lip is for example a leaf-type seal which is
  • FIG. 1 shows a perspective view of an airfoil arrangement comprising three airfoil devices according to an exemplary embodiment of the present invention
  • Fig. 2 shows a schematic side view along a circumferential direction showing an airfoil arrangement comprising the sealing element according to an exemplary embodiment of the present invention
  • Fig. 3 shows a schematic side view along a circumferential direction of an airfoil arrangement according to an exemplary embodiment of the present invention, wherein the sealing element comprises a seal lip
  • Fig. 4 shows a schematic side view along a circumferential direction of an airfoil arrangement according to an exemplary embodiment of the present invention, wherein the seal lip is detachably mounted to the sealing element
  • Fig. 5 shows a schematic view of a sealing element comprising cut-outs according to an exemplary embodiment of the present invention ;
  • Fig. 6 shows a schematic view of a conventional airfoil device which is attached to a conventional airfoil disc
  • Fig. 7 shows a schematic view of a conventional airfoil disc.
  • Fig. 1 shows a perspective view of an airfoil arrangement 100 for a gas turbine according to an exemplary embodiment of the present invention.
  • the airfoil arrangement 100 comprises three airfoil devices, in particular a first airfoil device 110, a second airfoil device 120 and a further airfoil device 130.
  • the airfoil devices 110, 120, 130 are mounted in a row along a circumferential direction 103 around a turbine shaft of the gas turbine.
  • the first airfoil device 110 comprises a first root section 112 with which the first airfoil device 110 is mountable to an airfoil disc 200 (see Fig. 2) .
  • the root section 112 comprises for example a radial extending plug with a fir tree cross-sectional shape for being mounted to a respective groove of the airfoil disc 200.
  • Each plug extends along a radial direction 104 which is oriented substantially to a rotating axis of the turbine shaft of the turbine.
  • Each airfoil device 110, 120, 130 comprises a respective platform, wherein between the plug and the platform a cavity 111 is formed.
  • cooling air is feedable to the airfoils for cooling purposes. Some of the cooling air is injected into the cavity 111.
  • a gap 101 exists between two adjoining airfoil devices 110, 120; 120, 130 .
  • cooling air from the cavity 111 may stream into the volume through which the hot working gas of the gas turbine flows along an axial direction 102. Due to pressure differences for example between the leading and trailing edge of the airfoil device, the hot working fluid may be ingested into the volume inside the cavity 111.
  • a sealing element 210 (see Fig. 2) according to the present invention is attached into the airfoil arrangement 100 shown in Fig. 1.
  • Fig. 2 shows a side view along the circumferential direction 103 of the first airfoil device 110. Axial locking
  • the airfoil device 110 is mounted to the airfoil disc 200 by the first root section 112.
  • the plug of the root section 112 which is shown in Fig. 1, is not shown in Fig. 2.
  • the first root section 112 further comprises a first platform 214, a first leading edge side 215 and a first trailing edge side 213.
  • the axial direction 102 is shown which is parallel to a rotating axis of the turbine shaft, wherein the hot working gas of the gas turbine streams substantially at least with one component along the axial direction 102.
  • the side of the root section 112 which is located more upstream is denoted the leading edge side 215, whereas the side which is located more
  • an airfoil 212 is attached forming part of the airfoil device 110.
  • the airfoil 212 may be formed with a hollow shape, wherein cooling fluid which streams through the root section 112 may be injected inside the inner volume of the hollow airfoil 212 for cooling purposes .
  • the respective feature of the first airfoil device 110 are also valid for the second airfoil device 120 or any further airfoil device 130, as shown for example in Fig. 1.
  • the second airfoil device 120 and the further airfoil device 130 may comprise as well a respective root section with which the respective airfoil device 120, 130 is mounted to the airfoil disc 200.
  • the second root section and the further root section comprise a respective platform, a respective leading edge side and a respective trailing edge side.
  • the second root section has a second cavity which is partially surrounded by the second platform, the second leading edge side and the second trailing edge side.
  • the first airfoil device 110 and the second airfoil device 120 are mounted to the airfoil device 200 such that the first root section 112 adjoins to the second root section and the first cavity 111 and the second cavity form a common cavity.
  • the sealing element 210 for partially sealing the common cavity is located inside the first cavity 111 and the second cavity such that the sealing element 210 covers the gap 101 between the adjoining first root section 112 and the second root section.
  • the gap 101 occurs between two adjoining platforms 214 and in addition also between two adjoining trailing edge sides 213 and/or to adjoining leading edge sides 215.
  • the sealing element 210 comprises a metal foam such that the sealing element 210 comprises lesser weight and a good stability in comparison to a sealing element consisting of a conventional solid metal material. Because the sealing element 210 consists of a metal foam with less weight, a larger sealing element 210 may be applied without affecting the overall weight of the airfoil arrangement 100
  • the sealing element 210 may fully or partially surround the sides of the inner cavity 111 for example. As shown in Fig. 2, such a lighter sealing element 210 may cover (at least partially) the trailing edge side 213, the leading edge side 215 and the platform 214, for example.
  • the sealing element 210 comprises a U-shaped cross-section as shown in Fig. 2.
  • the lightweight sealing element 210 may extend along the
  • the stability of the sealing element 210 is improved such that further fixing means for the sealing element 210 may be obsolete.
  • the sealing element 210 may be formed self-supporting.
  • the sealing element 210 may comprise edges (i.e. radial ends) which abut on a surface of the airfoil disc 200, such that the sealing element 210 may rest onto the airfoil disc 200 and is thus stable and self-supporting.
  • the sides of the sealing element 210 which extend along the radial direction 104 may form a press-fit (clamping) connection with the trailing edge side 213 and the leading edge side 215 of the first and second root sections 112.
  • sealing element 210 self supporting the need to cast or machine conventional recesses at any parts of the platform or respective trailing/leading edge sides is no longer needed, which significantly reduces the cost of the component and the machining time. In other words there is no need to have supports inside the cavity 111 that prevents the sealing element from moving away from gap 101, e.g. moving radially inwardly away from the platform 214.
  • the airfoil device 110 is a blade device which rotates together with the turbine shaft, the sealing element 210 is pressed due to centrifugal forces with its base section, which combines the two sides of the sealing element 210, onto the inner surface of the respective
  • the airfoil disc 200 comprises a recess 201 which runs substantially along the circumferential direction 103 and in which the recess 201 corresponds substantially to a shape of the edge 211 of the sealing element 210.
  • the edge 211 of the sealing element 210 abuts inside the recess 201 of the airfoil disc 200.
  • the recess 201 may be formed by a ledge or step which is machined into the airfoil disc 200.
  • One side of the recess 201 may be covered by e.g. the leading edge side 215 (as shown in Fig. 2) or the trailing edge side 213 after
  • Fig. 3 shows a further exemplary embodiment of the airfoil system 100.
  • Axial locking arrangements which fix the airfoil device 110, 120, 130 to an airfoil disc 200 are not shown for sake of clarity.
  • the airfoil device 110 in Fig. 3 has the same structural features as the airfoil device 110 shown in Fig. 2.
  • the sealing element 210 comprises at a further end a seal lip 311 which is adapted for being abutted onto a surface of the airfoil disc 200.
  • the seal lip 311 may be formed integrally with the sealing element 210.
  • the seal lip 311 is formed in such a way, that a high pressure of the gas (cooling fluid) inside the cavity 111 presses the seal lip 311 onto the surface of the airfoil disc 200.
  • the sealing element 210 may have during installation larger tolerances in order to provide an easy implementation of the sealing element 210, wherein during operation, the sealing function is achieved by an operating pressure of the cooling fluid inside the cavity 111 and the common cavity, respectively.
  • the seal lip 311 as shown in Fig. 3 comprises beneficial properties during installation and during operation at the same time.
  • Fig. 4 shows an exemplary embodiment of the first airfoil device 110.
  • the airfoil device 110 comprises the same
  • the sealing element 210 comprises the seal lip 311, wherein the seal lip 311 is a separate structural part in comparison to the seal element 210.
  • the seal element 210 may be formed of metal foam, whereas the separate seal lip 311 is formed of another sealing material, such as metal formed like a e.g. a leaf seal.
  • the seal lip 311 may be detachably mounted to the sealing element 210 such that the seal lip 311 may be exchanged for maintenance purposes, for example.
  • the seal lip 311 may be present to allow a pre-loaded force to be applied to the seal element 210. For this the seal lip 311 touching an opposing surface such that the seal element 210 may be clamped into position. This allows that the seal element 210 will be in close contact with the underside of the first platform 214 of the blade.
  • Fig. 5 illustrates an exemplary embodiment of the sealing element 210.
  • the sealing element 210 comprises a U-shaped profile.
  • a projection line of the gap 101 is shown for clarity purposes.
  • the gap 101 would run along the projected line 502. In regions of the sealing element 210 that do not cover the gap 101 when being
  • the overall weight of the sealing element 210 may be further reduced without reducing the sealing or
  • the sealing element 210 may comprise a section with a foam metal that comprises a lower porosity than the adjacent sections of the sealing element 210.
  • the porosity of the metal foam in the region of the projection line 502 is lower, a higher density and thus better sealing characteristics of the sealing element 210 in the region of the gap 101 (projection line 502) are achieved.
  • the sealing element 210 comprises an open-cell foam section in the region of the gap 101 (projection line 502) . Where there is no need to release cooling air the sealing element 210 comprises a close-cell foam section in the region of the gap 101 (projection line 502) .
  • the term "comprising” does not exclude other elements or steps and "a" or “an” does not exclude a plurality. Also elements described in association with different embodiments may be combined. It should also be noted that reference signs in the claims should not be construed as limiting the scope of the claims.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention porte sur un agencement de plan aérodynamique qui comprend un élément d'étanchéité fait d'une mousse de métal. Un agencement de plan aérodynamique (100) pour une turbine à gaz comprend un premier dispositif de plan aérodynamique (110), un second dispositif de plan aérodynamique (120) et un élément d'étanchéité (210). Le premier dispositif de plan aérodynamique (110) comprend une première section de pied (112) au moyen de laquelle le premier dispositif de plan aérodynamique (110) peut être monté sur un disque de plan aérodynamique (200). La première section de pied (112) comprend une première plateforme (214), un premier côté de bord d'attaque (215) et un second côté de bord d'attaque (213). La première section de pied (112) présente une première cavité (111) qui est partiellement entourée par la première plateforme (214), le premier côté de bord d'attaque (215) et le premier côté de bord de fuite (213). Le second dispositif de plan aérodynamique (120), qui possède de façon générale les mêmes éléments structuraux que le premier dispositif de plan aérodynamique (110), comprend une seconde cavité, les premiers dispositifs de plan aérodynamique (110, 220) pouvant être montés sur le disque de plan aérodynamique (200) de telle sorte que la première section de pied (112) soit adjacente à la seconde section de pied et que la première cavité (111) et la seconde cavité forment une cavité commune. L'élément d'étanchéité (210) comprenant une mousse de métal est placé à l'intérieur de la cavité commune de telle sorte que l'élément d'étanchéité (210) recouvre une fente (101) entre la première section de pied (112) et la seconde section de pied.
PCT/EP2012/063544 2011-07-25 2012-07-11 Agencement de plan aérodynamique comprenant un élément d'étanchéité fait d'une mousse de métal WO2013013975A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP11175189.7 2011-07-25
EP11175189A EP2551464A1 (fr) 2011-07-25 2011-07-25 Agencement d'aube comprenant un élément d'étanchéité en mousse métallique

Publications (1)

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WO2013013975A1 true WO2013013975A1 (fr) 2013-01-31

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170050352A1 (en) * 2014-08-06 2017-02-23 The Boeing Company Composite structure and method of forming thereof
US9995160B2 (en) 2014-12-22 2018-06-12 General Electric Company Airfoil profile-shaped seals and turbine components employing same
US10472911B2 (en) 2017-03-20 2019-11-12 Weatherford Technology Holdings, LLC. Gripping apparatus and associated methods of manufacturing
US10519740B2 (en) 2017-03-20 2019-12-31 Weatherford Technology Holdings, Llc Sealing apparatus and associated methods of manufacturing
US10626740B2 (en) 2016-12-08 2020-04-21 General Electric Company Airfoil trailing edge segment

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Publication number Priority date Publication date Assignee Title
EP2881544A1 (fr) * 2013-12-09 2015-06-10 Siemens Aktiengesellschaft Profilé d'aube de turbine à gaz et agencement associé
FR3027950B1 (fr) * 2014-11-04 2019-10-18 Safran Aircraft Engines Roue de turbine pour une turbomachine
EP3438410B1 (fr) 2017-08-01 2021-09-29 General Electric Company Système d'étanchéité pour machine rotative

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB712112A (en) 1951-07-13 1954-07-21 Bristol Aeroplane Co Ltd Improvements in or relating to blade-locking means for turbine and the like rotor assemblies
EP0816638A2 (fr) * 1996-06-27 1998-01-07 United Technologies Corporation Elément amortisseur et d'étanchéité pour aubes de turbine
US6561764B1 (en) * 1999-03-19 2003-05-13 Siemens Aktiengesellschaft Gas turbine rotor with an internally cooled gas turbine blade and connecting configuration including an insert strip bridging adjacent blade platforms
WO2003102380A1 (fr) * 2002-05-30 2003-12-11 Snecma Moteurs Maitrise de la zone de fuite sous plate-forme d'aube
US20040179937A1 (en) * 2001-09-25 2004-09-16 Erhard Kreis Seal arrangement for reducing the seal gaps within a rotary flow machine
EP1600606A1 (fr) 2004-05-03 2005-11-30 Rolls-Royce Deutschland Ltd & Co KG Système d'étanchéité et d'amortissement pour les aubes des turbines à gaz
US20070122269A1 (en) * 2003-12-20 2007-05-31 Reinhold Meier Gas turbine component
EP1467066B1 (fr) 2003-04-09 2007-12-12 Rolls-Royce Plc Joint ridé
WO2008046684A1 (fr) 2006-10-17 2008-04-24 Siemens Aktiengesellschaft Ensemble pale de turbine
WO2009053169A1 (fr) 2007-10-25 2009-04-30 Siemens Aktiengesellschaft Ensemble d'aubes de turbine et bande d'étanchéité
EP2295722A1 (fr) * 2009-09-09 2011-03-16 Alstom Technology Ltd Pale de turbine

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB712112A (en) 1951-07-13 1954-07-21 Bristol Aeroplane Co Ltd Improvements in or relating to blade-locking means for turbine and the like rotor assemblies
EP0816638A2 (fr) * 1996-06-27 1998-01-07 United Technologies Corporation Elément amortisseur et d'étanchéité pour aubes de turbine
US6561764B1 (en) * 1999-03-19 2003-05-13 Siemens Aktiengesellschaft Gas turbine rotor with an internally cooled gas turbine blade and connecting configuration including an insert strip bridging adjacent blade platforms
US20040179937A1 (en) * 2001-09-25 2004-09-16 Erhard Kreis Seal arrangement for reducing the seal gaps within a rotary flow machine
WO2003102380A1 (fr) * 2002-05-30 2003-12-11 Snecma Moteurs Maitrise de la zone de fuite sous plate-forme d'aube
EP1467066B1 (fr) 2003-04-09 2007-12-12 Rolls-Royce Plc Joint ridé
US20070122269A1 (en) * 2003-12-20 2007-05-31 Reinhold Meier Gas turbine component
EP1600606A1 (fr) 2004-05-03 2005-11-30 Rolls-Royce Deutschland Ltd & Co KG Système d'étanchéité et d'amortissement pour les aubes des turbines à gaz
WO2008046684A1 (fr) 2006-10-17 2008-04-24 Siemens Aktiengesellschaft Ensemble pale de turbine
WO2009053169A1 (fr) 2007-10-25 2009-04-30 Siemens Aktiengesellschaft Ensemble d'aubes de turbine et bande d'étanchéité
EP2295722A1 (fr) * 2009-09-09 2011-03-16 Alstom Technology Ltd Pale de turbine

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170050352A1 (en) * 2014-08-06 2017-02-23 The Boeing Company Composite structure and method of forming thereof
US10780616B2 (en) * 2014-08-06 2020-09-22 The Boeing Company Methods of forming composite structures
US9995160B2 (en) 2014-12-22 2018-06-12 General Electric Company Airfoil profile-shaped seals and turbine components employing same
US10626740B2 (en) 2016-12-08 2020-04-21 General Electric Company Airfoil trailing edge segment
US10472911B2 (en) 2017-03-20 2019-11-12 Weatherford Technology Holdings, LLC. Gripping apparatus and associated methods of manufacturing
US10519740B2 (en) 2017-03-20 2019-12-31 Weatherford Technology Holdings, Llc Sealing apparatus and associated methods of manufacturing

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