EP2540986A2 - Aube de turbine - Google Patents

Aube de turbine Download PDF

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Publication number
EP2540986A2
EP2540986A2 EP12174450A EP12174450A EP2540986A2 EP 2540986 A2 EP2540986 A2 EP 2540986A2 EP 12174450 A EP12174450 A EP 12174450A EP 12174450 A EP12174450 A EP 12174450A EP 2540986 A2 EP2540986 A2 EP 2540986A2
Authority
EP
European Patent Office
Prior art keywords
section
blade
sealing
sealing plate
front wall
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP12174450A
Other languages
German (de)
English (en)
Other versions
EP2540986A3 (fr
Inventor
Alexander Anatolievich Khanin
Ilya Mikhailovich Fedorov
Andrey Anatolievich Sedlov
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 EP2540986A2 publication Critical patent/EP2540986A2/fr
Publication of EP2540986A3 publication Critical patent/EP2540986A3/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades

Definitions

  • the present invention relates to a blade, in particular to a cooled blade, for a turbine as well as to a rotor for a turbine with at least one such blade.
  • a turbine in particular a gas turbine, usually comprises a rotor and a stator with the rotor comprising rotating blades arranged radially around a shaft.
  • the blade itself comprises a platform, wherein a top plate of the platform supports an airfoil of the blade at the inner end of the airfoil. At its opposite end, i.e. at a bottom plate, the platform is adapted for the connection to the shaft.
  • the rotation of the blades leads to a rotation of the shaft, wherein this rotation is used for further purposes such as the generation of electricity.
  • the expansion energy of a fluid is used.
  • the expanding fluid thereby flows past the blades along a flow direction, wherein stationary vanes of the stator provide a beneficial flow path for the driving fluid.
  • adjacent blades are arranged in the circumferential direction with respect to the rotation of the rotor, wherein the blades are arranged adjacent to vanes in the flow direction. That is, in particular, the blades face a neighbouring vane in the upstream direction, with respect to the flow direction, of the driving fluid.
  • the platform of a said blade comprises a curved front wall facing an upstream neighbouring vane.
  • the front wall further supports a sealing section for providing sealing between said blade and the upstream neighbouring vane, said sealing section being at least partially arranged below the neighbouring vane, wherein below is defined with respect to a radial direction of the shaft.
  • the sealing section is thus at least partially arranged below the vane in particular at an inner end of the vane.
  • a flow path width reduction is known as a reasonable method to increase the efficiency of a turbine of the said kind, in particular during a retrofit. That is, the path of the driving fluid is restricted in a direction crossing the flow path direction, in particular in the radial direction, which increases the speed of the driving fluid along the flow path and thus the efficiency of the turbine.
  • the blades and vanes accordingly and preserve other parts of the turbine such as the shaft.
  • Such an adaptation of a blade comprises in particular an increase of the platform size. That is the size of the platform is increased along the radial direction with respect to the shaft. This increase leads to a corresponding increase in the size of a platform of the corresponding vane. Keeping the remaining main parts of the turbine, in particular the shaft, as they are leads to a demand for an aligned and improved sealing between the blade and the neighbouring vane.
  • the present invention addresses the problem of delivering an improved or at least alternative embodiment for a blade of the said kind, which in particular is characterised by an improved sealing property.
  • the present invention is based on the general idea of ensuring a proper sealing between a blade and an upstream neighbouring vane of a turbine by providing a front wall of a platform of the blade with a flat section which runs perpendicular to a top plate of the platform carrying an airfoil of the blade at the inner end of the blade, said front wall facing the upstream neighbouring vane and comprising a curved section supporting a sealing section.
  • the sealing section provides sealing between the blade and the upstream neighbouring vane and is at least partially arranged below said vane.
  • the given directions, such as top or below are thereby defined with respect to a radial direction of an associated shaft to which the blade is connected.
  • the top plate of the platform is that plate of the platform being further away from the shaft and in particular running parallel to the shaft. Accordingly, a sealing section arranged below the vane is provided by an arrangement whereby the sealing section is closer to the shaft than the vane. Similarly, the inner end of the airfoil is the end of the airfoil closer to the shaft and/or facing the shaft.
  • the invention is thus based on the idea that the minimum distance between the blade and the upstream neighbouring vane required to accommodate the sealing section below said vane is reduced by providing the front wall with the flat section.
  • This is in particular beneficial if the height of the platform is increased and the distance between the blade and the upstream neighbouring vane is kept, wherein the height is given with respect to the radial direction and thus as seen in a longitudinal section view of the blade.
  • Such a height increase of the platform is in particular used during a retrofit process of the turbine, wherein the vane is adapted accordingly to decrease a flow path width and thus the available radial volume leading to an efficiency increase of the turbine by a rise of the speed of a driving fluid of the turbine.
  • the front wall of the platform of the blade comprises a flat section wherein the flat section is arranged between the top plate of the platform and the curved section of the front wall.
  • the curved section is arranged below the flat section and the flat section is arranged below the top plate, wherein below is given with respect to the radial direction.
  • a transition between the perpendicularly arranged top plate and the flat section is provided by means of an upper transition section arranged between the top plate and the flat section.
  • the upper transition section thereby preferably comprises a curved shape to avoid a sharp transition or edge between the top plate and the front wall. That is, the upper transition section is in particular curved with a radius of curvature R3, wherein the direction of curvature is preferably oriented away from the platform.
  • a curvature of the upper transition section and the corresponding choice of the radius of curvature R3 moreover lead to desired aerodynamic properties of the blade.
  • a respective transition between the flat section and the curved section supporting the sealing section can be realised by means of a lower transition section arranged between the flat section and the curved section, according to a further embodiment.
  • the lower transition thereby comprises in particular a radius of curvature R4, which is different from a radius of curvature R5 of the curved section.
  • the lower curved section moreover comprises a direction of curvature oriented opposite to the direction of curvature of the upper transition section. That is, in a preferred embodiment, the upper transition section is curved away from the platform while the lower transition section comprises a curvature oriented towards the platform.
  • Such an embodiment in particular leads to a sealing section being arranged essentially parallel to the top plate.
  • the airfoil of the blade contacts the upper transition section by means of an airfoil transition section.
  • the airfoil transition section is thus arranged on the upstream side and at the inner end of the airfoil.
  • the airfoil transition section further preferably comprises a complimentary shape, which allows for a smooth transition between the airfoil and the airfoil transition section on its upper side facing the airfoil.
  • the airfoil transition section On its lower side opposing the airfoil, the airfoil transition section comprises preferably two different radii of curvature, wherein one of these radii R1 is arranged at one edge of the said side contacting the upper transition section and the other radius R2 is arranged at the opposing edge crossing the upper transition section.
  • Said lower side of the airfoil transition section thereby preferably comprises a smooth transition between the two radii of curvature along a path between both said edges.
  • the airfoil transition section and the upper transition section are shaped complementarily on their contacting sides, which in particular allows for a smooth transition between the airfoil transition section and the upper transition section and thus for a smooth transition between the airfoil, the front wall and the top plate, in particular for aerodynamic reasons.
  • the sealing section supported by the curved section of the front wall comprises at least one fin.
  • the fin is thereby arranged on the side of the sealing section facing the airfoil and is arranged below the associated upstream neighbouring vane of the blade.
  • the fin therefore projects in the radial direction and is adapted to cooperate with a neighbouring fin to establish a fluidic sealing between the blade and said vane, in particular to prevent the driving fluid of the turbine from accessing the area under the platforms.
  • the fin usually cooperates with a facing part of the vane, wherein the cooperating facing part is in particular formed and/or constructed to form a labyrinth seal with the fin.
  • Preferred embodiments thereby comprise several fins, adapted to cooperate with a complementary vane part to form the sealing.
  • the sealing section comprises at least one fin, which is inclined away from the flat section of the blade. That is, said fin is inclined away from the platform and inclined towards the upstream neighbouring vane and thus against the flow direction.
  • said fin is inclined away from the platform and inclined towards the upstream neighbouring vane and thus against the flow direction.
  • Such an incline in particular leads to an improved sealing effect of the sealing section when interacting with the according part of the vane.
  • at least one fin is inclined towards the flat section of the front wall and thus towards the platform and away from said vane.
  • Embodiments comprising a combination of inclined and non inclined as well as different degrees of inclination are also possible and thus form part of the present invention.
  • the blade comprises several fins arranged on the sealing section, wherein different fins comprise different sizes and/or shapes. That is one or several fins comprise a different size and/or shape compared to one or more other fins.
  • the sealing section comprises four fins facing the airfoil. All four fins further comprise the same inclination away from the platform of the vane and thus against the flow direction. The first three neighbouring fins of the platform moreover have the same size and shape and the fourth fin, i.e. the fin furthest from the platform, comprises a different shape than the other three and is in particular larger than the others.
  • the first three fins show the same size and shape while the fourth and thus last fin has a different shape and a larger size.
  • the fourth and thus last and bigger fin thereby preferably forms the edge of the sealing section and thus the edge of the front wall. Therefore, in particular in a longitudinal section view of the blade, the first three fins comprise a height H2 and the forth fin comprises another height H3, wherein H3 is bigger than H2.
  • the blade can be equipped with sealing plates. Therefore the blade comprises at least one sealing plate guide for the assembly of at least one sealing plate.
  • the sealing plate guide therefore forms a recess in which the corresponding sealing plate is arranged in order to establish a seal.
  • the sealing plate guide does thereby not necessarily comprise a continuing shape. That is, the sealing plate guide can be constructed in sections along a path, in particular by means of segments.
  • a fixing of the sealing plate is further preferably realised by means of fixing portions of the sealing plate guide, wherein said fixing portion is adapted to cooperate with a complementarily shaped fixing part of the corresponding sealing plate. That is, the sealing plate guide in particular comprises at least one fixing portion adapted to interact or receive or engage with the according fixing part of the sealing plate.
  • At least one of the sealing plate guides is constructed curvilinear for the assembly of a complementarily shaped sealing plate.
  • a sealing plate guide is in particular arranged below the front wall of the blade.
  • said sealing plate guide is further running below the whole front wall extending into the sealing section. That is in particular, said sealing plate guide runs below the sealing section and continues below the flat section and the upper transition section. Said sealing plate guide is thereby preferably arranged below one of the circumferential edges of the front wall. Such an arrangement in particular simplifies the assembly of the corresponding sealing plate.
  • At least one of the sealing plate guides is arranged below the top plate of the platform.
  • Said sealing plate guide is thus in particular arranged parallel to the top plate and can optionally extend over the whole extent of the top plate.
  • Said sealing plate guide is thereby preferably arranged below one of the circumferential edges of the top plate.
  • the sealing plate guide arranged below the front wall contacts the sealing plate guide arranged below the top plate.
  • the contact is thereby in particular realised by a contact of an edge of the sealing plate guide below the front wall with the lower side of the sealing plate guide below the top plate, i.e. with the side of the sealing plate guide opposing the top plate.
  • the contact can further be arranged at a position spaced from an edge of the sealing plate guide below the top plate, said edge in particular facing the front wall.
  • the blade comprises at least one sealing plate guide arranged at a back wall of the platform for the assembly of a sealing plate, wherein said back wall is opposed to the front wall, i.e. in particular the back wall is arranged on a downstream side of the blade.
  • Said sealing plate guide can further be adapted to be aligned with the sealing plate guide at the back wall of a circumferential neighbouring blade. That is the sealing plate guide arranged at the back wall in particular runs across the back wall and in particular over the whole back wall, and can be aligned with a similar sealing plate guide of a neighbouring blade, wherein the same sealing plate is preferably arranged within both said sealing plate guides.
  • the said sealing plate guides thereby do not necessarily contact each other.
  • the back wall of the blade comprises a projection, wherein the projection is adapted to be arranged in a complementarily shaped recess of the back wall of a circumferential neighbouring blade.
  • the blade comprises a recess, wherein the recess is adapted to receive a complementarily shaped projection of the back wall of a circumferential neighbouring blade. The according projections and recesses are thereby conveniently arranged at facing edge of the corresponding back walls.
  • the blade can further comprise an arbitrary combination of said recesses and projections cooperating with according recesses and projection of the back wall of the circumferential neighbouring blades.
  • a preferred embodiment is however given by a back wall comprising a projection at one of its edges facing the back wall of a circumferential neighbouring blade and a recess at its other edge facing the back wall of the other circumferential neighbouring blade.
  • the blade In a longitudinal section view of the blade, i.e. in a section view running along the radial direction, the blade comprises a height of the front wall H, which is defined as the height difference between the top plate and the sealing section of the blade.
  • Another characteristic value of the front wall is given by the flat section height H1 in the said longitudinal section view, wherein the flat section height H1 is defined as the height difference between the top plate and the junction between the flat section and the lower transition section.
  • a rotor in particular a rotor for a turbine, is equipped with at least one blade according to the invention.
  • a rotor preferably comprises several blades according to the invention, said blades arranged adjacently in the circumferential direction.
  • the rotor can additionally comprise at least one sealing plate being arranged in the respective sealing plate guide of at least one blade, wherein said sealing plate can comprise a bilayer construction and is additionally or alternatively resilient.
  • said rotor is conveniently arranged within a turbine, wherein the front walls of the blades face an upstream neighbouring vane of a stator of the turbine.
  • the turbine is also part of the invention.
  • a blade 1 comprises a platform 2, wherein the platform 2 comprises a top plate 3 carrying an airfoil 4 at the inner end of the airfoil 4.
  • the inner end is in relation to a direction depicted by an arrow 5, wherein the arrow 5 denotes the radial direction of a shaft the blade is connected with, when assembled in a rotor 6 and in a turbine 7 respectively.
  • the arrow 5 therefore denotes the radial direction with respect to the rotation of the blade 1.
  • the platform 2 of the blade 1 further comprises side walls 8 with respect to a circumferential direction depicted by the arrow 9, wherein said side walls 8 form a platform cavity being enclosed by a front wall 10 and a back wall 11 of the platform 2 with respect to a flow direction depicted by the arrow 12.
  • the circumferential direction thereby refers to a direction of rotation of the blade 1, when assembled in the rotor 6 or the turbine 7 respectively.
  • a driving fluid flow passes the blade 1 of the turbine 7, said driving fluid flow direction defining the flow direction depicted by the arrow 12.
  • the front wall 10 is arranged on an upstream side of the blade 1 with respect to the flow direction given by the arrow 12, which is on the right side of the view shown in Fig. 1 .
  • the back wall is respectively arranged on a downstream side, which is the left side of the view shown Fig. 1 .
  • the blade 1 moreover comprises a fir tree form 13 arranged on a bottom plate 14 of the platform 2, wherein the term 'bottom' is given with respect to the radial direction given by the arrow 5.
  • the fir tree form 13 in particular is shaped to form a connection between the blade 1 and the shaft of the rotor 6 and the turbine 7.
  • the airfoil 4 comprises channels 15 of a channel system for cooling purposes.
  • the front wall 10 comprises a curved section 16 supporting a sealing section 17 of the front wall 10.
  • the curved section 16 is constructed with a radius of curvature R5 and connected to the sealing section 17 on its upstream side, wherein the radius of curvature of the curved section 16 extends generally towards the platform 2.
  • the sealing section 17 comprises a planar top side 18, wherein the top side 18 is facing the airfoil 4.
  • the top side 18 of the sealing section 17 thus faces in the direction of the arrow 5 and thus in the radial direction and runs parallel to the top plate 3 of the platform 2.
  • the sealing section 17 further comprises four fins 19, 20 arranged on its top side 18.
  • the first three fins 19 have the same size and shape, wherein the numbering of the fins 19, 20 is done following a direction opposing the flow direction 12 and thus from left to right in the shown view.
  • the fourth fin 20 of the sealing section 17 is arranged at the furthermost upstream edge of the sealing section 17 and thus on the furthest right side of the sealing section 17 in the shown view.
  • the fin 20 therefore forms the tail of the sealing section 17 on the upstream side and is formed larger than the other fins 19. All four fins 19, 20 are inclined away from the platform 2 and thus towards a direction opposing the flow direction depicted by the arrow 12.
  • the first three fins 19 comprise inclined and planar walls 21 which extend from the top side 18 of the sealing section 17 and each fin 19 comprises a planar surface 22 at its distal, wherein the planar surfaces 22 run parallel to the top side 18 of the sealing section 17.
  • the fourth fin 20 comprises two walls 23, 24, wherein one of the said walls 23 facing the platform 2 has a curved shape whereas the other wall 24 facing away from the platform 2 has a planar surface.
  • the transition between the top side 18 of the sealing section 17 and the fin 20 on the side facing the platform 2 thus comprises a curved shape while all other transitional regions between the top side 18 and the fins 19, 20 are angular.
  • the walls 23, 24 of the fin 20 extend to a planar surface 22 at a distal end of said fin 20, wherein said planar surface 22 runs parallel to the top side 18 of the sealing section 17 and thus the top plate 3 of the platform 2.
  • the curved section 16 is adjacent a lower transition section 25 on the side of the curved section 16 opposite to the sealing section 17.
  • the lower transition section 25 comprises a curved shape having the same direction of curvature as the curved section, i.e. towards the platform, but having a different radius of curvature R4.
  • the curved section 16 is thus arranged between the sealing section 17 and the lower transition section 25.
  • the lower transition section 25 thereby serves as a transition between the curved section 16 and a flat section 26 of the front wall 10.
  • the flat section 26 is thus arranged on the side of the lower transition section 25 opposite to the curved section 16.
  • the flat section 26 thereby runs perpendicular to the top plate 3 of the platform 2 and thus also perpendicular to the top side 18 of the sealing section 17.
  • An upper transition section 27 is arranged on the side of the flat section 26 opposing the lower transition section 25.
  • the upper transition section 27 comprises a curved shape, wherein the curvature is projected away from the platform 2 and thus in the opposite direction to the curvatures of the curved section 16 and the lower transition section 25.
  • the upper transition section 27 moreover comprises a radius of curvature R3 and serves as a transition between the perpendicularly arranged top plate 3 and flat section 26.
  • a height H of the front wall 10 is defined by a distance along the radial direction 5 between the top plate 3 and the top side 18 of the of the sealing section 17, these being arranged in a parallel manner.
  • the curved section 16, the lower transition section 25, the flat section 26 and the upper transition section 27 all have a rectangular shape and the long sides of the respective sections 16, 25, 26, 27 form the boarders between adjacent sections.
  • the rectangular shape of the upper transition section 27 is however overlapped by a curved tip 28 of an airfoil transition section 29, as shown in Fig. 2 , wherein the airfoil transition section 29 serves as a transition between the upstream side of the airfoil 4 and the platform 2.
  • the curved tip 28 of the airfoil transition section 29 is thereby delimited by two different radii of curvature R1, R2 at the circumferential edges of the airfoil transition section 29 and thus at its edges along the direction given by the arrow 9, wherein one of said radii of curvature R1 contacts the top long edge of the upper transition section 27 and is bigger that the other said radius of curvature R2, with the latter one running across the upper transition section 27.
  • a flat section height H1 can be defined as the height difference between the top plate 3 and the junction between the flat section 26 and the lower transition section 25.
  • the respective heights H2, H3 of the fins 19, 20 can further be defined as shown in the enlarged view in Fig. 3 .
  • the height H2 of the fins 19 is given by their radial length and hence their dimension along the radial direction given by the arrow 5.
  • the height H3 of the larger fin 20 is similarly given by the corresponding dimension in the radial direction.
  • the blade 1 further comprises three sealing plate guides 30, 31, 32, as shown in Fig. 1 , Fig. 4 and Fig. 6 , wherein the single sealing plate guides 30, 31, 32 comprise different sizes and shapes, but all have similar fixing portions 33. Said fixing portions 33, thereby, are adapted to interact with or engage or receive a complementary fixing part 34 of a corresponding sealing plate 35, 36, 37 arranged within the corresponding sealing plate guide 30, 31, 32.
  • One of the sealing blade guides 30 has a curvilinear shape and is arranged below the edge of the front wall 10 and opposing the circumferential direction.
  • the guide of the sealing plate guide 30 is provided by three segments 38 cooperating with the bottom side 39 of the front wall 10, said bottom side being curvilinear shaped.
  • the walls 40 of the segments 38 thus cooperate with the bottom facing side 39 of the front wall 10 to form the curvilinear shaped sealing plate guide 30, wherein the walls 40 comprise a complementary shape to the corresponding region of the bottom side 39 of the front wall 10.
  • the two segments 38 arranged below the curved section 16 and/or the sealing section 17 of the front wall 10 moreover form the fixing portions 33 interacting with the corresponding fixing part 34 of the corresponding sealing plate 35 in order to connect the sealing plate 35 with the sealing plate guide 30.
  • the third segment 38 is arranged adjacent to the flat section 26 of the front wall 10 and below the flat plate 3 of the platform 2.
  • This segment 38 thereby comprises two walls 40, one of which is shaped curvilinear and complementary to the bottom side 39 of the front wall and meets the other wall 40, which is planar shaped and faces the bottom side 39 of the top plate 3 of the platform.
  • the latter wall 40 therefore forms a part of the sealing plate guide 31 arranged below the top plate 3.
  • Another segment 38 is arranged below the top plate 3 in a region situated closer to the back wall 11 of the platform 2.
  • Said segment 38 forms the fixing portion 33 of the sealing plate guide 31 arranged below the top plate 3 together with another segment 38 contacting and forming part of the back wall 11 and arranged perpendicular to the back wall 11.
  • the sealing plate guide 31 thus penetrates into the back wall 11 to some extent.
  • Said sealing plate guide 31 also penetrates into the front wall 10 to some extent by means of a slot 41, said slot 41 running parallel to the top plate 3. Therefore, a corresponding sealing plate 36 arranged within the sealing plate guide 31 below the top plate 3, is contacted by the sealing plate 35 arranged within the sealing plate guide 30 below the front wall 10 at a side of the sealing plate 36 facing away from the top plate 3, as shown in Fig. 3, Fig. 4 and Fig. 6 . Said contact is moreover provided in a region of the sealing plate 36 below the top plate 3 which is spaced from the edge of said sealing plate 36, said edge facing the front wall 10. This leads to a closed sealing in the transition region between the front wall 10 and the top plate 3.
  • the other sealing plate guide 32 is arranged at a centre region of the back wall 11 of the platform 2 and is provided by means of a groove 42 within the back wall 11. Said sealing plate guide 32 moreover runs across the whole width of the back wall 11 to allow the assembly of the same sealing plate 37 within said sealing plate guide 32, and within a similar sealing plate guide 32 arranged at the back wall of the circumferentially adjacent blade 1, as shown in Fig. 4 , wherein Fig. 4 shows two circumferential neighbouring blades 1 of the rotor 6.
  • the blades shown here additionally comprise circle shaped openings 43 arranged below the sealing plate guides 32 of the corresponding blades 1. These openings are provided in particular for cooling purposes. There is a gap between the two blades 1 shown in Fig.
  • sealing plates 35, 36, 37 shown in Fig. 4 comprise a bilayer construction, wherein the single layers run along the corresponding sealing plates 35, 36, 37.
  • Said sealing plates 35, 36, 37 moreover comprise a springy/resilient property, which in particular leads to a better sealing result.
  • FIG. 5 A top perspective view of the rotor is shown in Fig. 5 to reveal that the back wall 11 of the front blade 1 comprises a step-like recess 44 at the edge of said back wall 11 facing the back wall 11 of the neighbouring blade 1.
  • the latter back wall 11 comprises a complementarily shaped step-like projection 45 facing the back wall 11 of the front blade 1, wherein the recess 44 of the back wall 11 of the front blade 1 receives the projection 45 of the back wall 11 of the other blade 1.
  • Said plane contact 46 thereby leads in particular to an improved sealing of the driving fluid flowing along the flow direction depicted by the arrow 12.
  • a blade 1 arranged within the turbine 7 is shown in Fig. 6 .
  • the blade thereby faces an upstream neighbouring vane 47 with respect to the flow direction of the driving fluid given by the arrow 12, wherein the sealing section 17 is arranged below the vane 47 with respect to the radial direction given by the arrow 5 and thus as illustrated in the shown view of Fig. 6 .
  • the cooperating part 49 comprises a stepped shape in the shown longitudinal view section, wherein the step projecting further towards the facing sealing section 17 cooperates with the smaller fins 19, while the other step of the cooperating part 49 interacts with the bigger fin 20.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12174450.2A 2011-07-01 2012-06-29 Aube de turbine Withdrawn EP2540986A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2011127159/06A RU2564741C2 (ru) 2011-07-01 2011-07-01 Лопатка турбины и ротор турбины

Publications (2)

Publication Number Publication Date
EP2540986A2 true EP2540986A2 (fr) 2013-01-02
EP2540986A3 EP2540986A3 (fr) 2017-05-31

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EP12174450.2A Withdrawn EP2540986A3 (fr) 2011-07-01 2012-06-29 Aube de turbine

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EP (1) EP2540986A3 (fr)
RU (1) RU2564741C2 (fr)

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WO2014209464A3 (fr) * 2013-04-18 2015-03-12 United Technologies Corporation Géométrie de bord de plateforme de profil aérodynamique de moteur à turbine à gaz
DE102013220467A1 (de) * 2013-10-10 2015-05-07 MTU Aero Engines AG Rotor mit einem Rotorgrundkörper und einer Mehrzahl daran angebrachter Laufschaufeln
US20160061048A1 (en) * 2013-03-25 2016-03-03 United Technologies Corporation Rotor blade with l-shaped feather seal
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same

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RU2564741C2 (ru) 2015-10-10
RU2011127159A (ru) 2013-01-10

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