EP2828484B1 - Aube de turbine - Google Patents

Aube de turbine Download PDF

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Publication number
EP2828484B1
EP2828484B1 EP13714573.6A EP13714573A EP2828484B1 EP 2828484 B1 EP2828484 B1 EP 2828484B1 EP 13714573 A EP13714573 A EP 13714573A EP 2828484 B1 EP2828484 B1 EP 2828484B1
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EP
European Patent Office
Prior art keywords
side wall
wall
suction
pressure
leading edge
Prior art date
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Active
Application number
EP13714573.6A
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German (de)
English (en)
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EP2828484A1 (fr
Inventor
Martin Schnieder
Sergey Shchukin
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Ansaldo Energia IP UK Ltd
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Ansaldo Energia IP UK Ltd
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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
    • F05C2251/00—Material properties
    • F05C2251/02—Elasticity
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • 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
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity

Definitions

  • the disclosure relates to a turbine blade for a flow rotating machine with an airfoil bounded by a concave pressure and a convex suction sidewall enclosing a cavity extending from the pressure and suction sidewall as well as a longitudinally extending suction tube. and the pressure side wall inwandig connecting partition is limited.
  • Turbine blades of the abovementioned type represent heat-resistant components which are used in particular within turbine stages of gas turbine assemblies and are exposed in the form of guide vanes or blades to the hot gases emerging directly from the combustion chamber.
  • the heat resistance of such turbine blades is due, on the one hand, to the use of heat-resistant materials and, on the other hand, to highly efficient cooling of the turbine blades exposed directly to the hot gases, which have corresponding cavities for continuous flow and admission of coolant, preferably cooling air
  • coolant preferably cooling air
  • Coolant supply system of the gas turbine assembly which is used to cool all heat-exposed Gas turbine components cooling air during gas turbine operation, in particular the turbine blades, provides.
  • Conventional turbine blades have a blade root to which radially or indirectly adjoins the airfoil, which has a concave shaped pressure side wall and a convex suction side wall, which integrally connect in the region of the blade leading edge and between which a space is limited, which is for cooling purposes supplied by the blade root with cooling air.
  • the term "radially” here refers to the turbine blade extension in the assembled state within the gas turbine arrangement, which is oriented radially to the axis of rotation of the rotor unit.
  • the intermediate space is provided with radially extending partitions, each delimiting radially inside the airfoil oriented cavities, some of which via fluidic connections feature.
  • passage openings are provided in the suction or pressure side wall, in the region of the turbine blade front and / or trailing edge or on the turbine blade tip, so that the cooling air can escape outward into the hot gas channel of the turbine stage.
  • An optimized for cooling purposes gas turbine blade is the EP 1 319 803 A2 can be seen, which provides a plurality of radially oriented cooling channel cavities within the turbine blade, each of which is fluidly connected in a meandering manner and are traversed in accordance with different levels of heat-contaminated airfoil regions with more or less cooling air.
  • it is the area of the blade leading edge that undergoes the greatest flow and heat exposure of the hot gases to cool in a particularly efficient manner.
  • a cavity extending inwardly along the blade leading edge of the suction and pressure side wall, which unite at the blade leading edge and of an intermediate wall, which connects the suction and pressure side, is limited and is fed from the side of the blade root with cooling air.
  • the cooling air flowing through the cavity reaches the outside in the area of the blade tip.
  • the cooling air flow vortexing structures are provided.
  • a further preferred cooling of the blade leading edge region of a turbine blade is in the US 5,688,104 described.
  • a cavity which is bounded on the one hand by the suction and pressure side wall, which unite at the blade leading edge, and by an intermediate wall which rigidly connects the suction and pressure side wall within the airfoil.
  • the cavity extending along the blade leading edge is fed with cooling air which enters the cavity exclusively through cooling channel openings provided inside the intermediate wall.
  • the rectilinearly formed intermediate wall is provided in the radial longitudinal extent with a plurality of individual passageways through which cooling air from an adjacent radially extending cooling channel along the airfoil occurs in the form of an impingement cooling in the direction of the blade leading edge within the cavity referred to above.
  • film cooling openings directed toward the suction and pressure side outer wall are respectively provided along the blade leading edge, by means of which the cooling air introduced inside the cavity is discharged to form a film cooling at the pressure and suction side outer wall.
  • Turbine blades which for purposes of optimized heat resistance in particular in the region of the blade leading edge on the above Cooling measures have, however, often show in the blade leading edge region along the pressure and suction side wall fatigue phenomena that appear in the final stage by cracking.
  • the reason for such cracking is the occurrence of thermo-mechanical stresses within the suction and pressure sidewall in the blade leading edge region resulting from high temperature differences between the hot gas-loaded blade leading edge and the cooling air-loaded inner wall portions of the airfoil.
  • US 3191908 and the JP 2002 242607 A are blades with a suction and pressure side wall inwandig interconnecting intermediate wall having holes for impingement cooling of the side wall.
  • the EP 0 806 546 A1 discloses a turbine blade having a ceramic leading edge insert which is mounted on the leading edge of the airfoil and is impingement air cooled.
  • a turbine blade according to claim 1 for a flow rotating machine with an airfoil which is bounded by a concave pressure and a convex suction side wall, which are connected in the region of a blade leading edge assignable to the blade and a longitudinal extent of the blade leading edge extending cavity
  • the innwandig of the pressure and suction side wall in the region of the blade leading edge and a longitudinally extending to the blade leading edge the suction and the pressure side wall innwandig connecting intermediate wall is limited, further, that reduces the temperature differences caused by fatigue in the blade leading edge until completely avoided in order to improve the life of the highly heat-exposed turbine blades in this way.
  • the measures required for this purpose should as far as possible not impair the cooling measures known per se, but also improve and support them. Also, the measures required for this purpose should require neither cost-intensive nor manufacturing relevant complex expenses.
  • a turbine blade according to the invention for a flow rotary machine has an airfoil which is delimited by a concave pressure and a convex suction sidewall. These walls are connected in the region of a blade leading edge that can be assigned to the blade and include a cavity extending in the longitudinal extent of the blade leading edge, which extends inwardly from the pressure and suction side wall in the area of the blade leading edge and from the longitudinal direction to the blade leading edge, the suction and the Pressure side wall inwandig connecting partition wall is limited.
  • This intermediate wall and the suction and / or pressure side wall are a coherent part. This is typically made as a casting.
  • the disclosed turbine blade is characterized in that the intermediate wall in the connection region to the suction and / or pressure side wall at least partially has a perforation in order to increase the elasticity.
  • a perforation is to understand a variety of holes. These are typically arranged along a line. Typically, this line is at least partially straight. For example, three or more holes may be arranged along a straight line.
  • the elasticity of the intermediate wall is increased. Due to the elastic connection area, the intermediate wall has less stiffening effect on the entire blade, so that the tension between the pressure and suction side wall is also reduced.
  • a connection region of the intermediate wall to the suction and / or pressure side wall of the adjacent to the suction and / or pressure side wall region of the intermediate wall is here designated.
  • connection area can extend up to a quarter of the distance between the suction and pressure side wall.
  • the terminal region extends to a distance that is less than the thickness of the intermediate wall or less than one to two times the thickness of the intermediate wall.
  • the connection area is a rounding or a fillet limited in the transition from intermediate wall to the suction and / or pressure side wall.
  • the connection area is limited to an area from the side wall, which corresponds to twice the radius of the rounding or groove in the transition from intermediate wall to the suction and / or pressure side wall.
  • the disclosure is based on the finding that the fatigue cracks in the blade leading edge region of turbine blades exposed to hot gases are primarily due to the thermally induced expansion and contraction tendency of the pressure and suction side wall regions in the blade leading edge region, the intransigence of the rigidly formed, always with cooling air flow around the intermediate wall the vane leading edge immediately downstream of the airfoil and the suction side wall and pressure side wall firmly connects, mechanically counteracts, whereby the highly heated heat exposed suction and pressure side wall areas experience an increased internal mechanical stress, which in turn entails a high material stress, ultimately to the Life reducing fatigue leads.
  • the blade leading edge immediately downstream intermediate wall, which defines together with the inner walls of the pressure and suction side wall extending along the blade leading edge cavity, according to the solution modified , so that the intermediate wall or the connection region of the intermediate wall experiences an elasticity, whereby the thermally induced expansion and shrinkage tendency of the suction side and pressure side wall regions along the blade leading edge can be at least partially yielded.
  • the intermediate wall has a perforation at least at a connecting region to the side wall, by means of which the elasticity described above can be realized.
  • the perforation comprises a series of cylindrical holes.
  • the perforation comprises a number of oblong holes or slots, whose longer side extends parallel to the respective adjacent suction or pressure side wall.
  • the port By connecting the intermediate wall and the side wall, relatively thick accumulations of material form their ratio of surface to volume is much smaller than in a free wall section.
  • the port On the inside, the port also obstructs the flow of the walls, so that the temperature of the blade material in the connection area changes more slowly than the material temperatures in a free wall section in the event of transient changes in the hot gas or cooling air temperatures. This leads to additional thermal stresses, which are reduced by the perforation.
  • connection region of the intermediate wall to the suction and / or pressure side wall is even formed with a rounded or chamfered groove.
  • This groove is due to production of cast blades.
  • they reduce the concentration of stress on the wall connection, and on the other hand, the accumulation of material in the connection area between the intermediate wall and the suction and / or pressure side wall is increased by the groove.
  • the perforation in the connection area improves the heat transfer on the inside of the walls, so that transient temperature changes can be better followed.
  • the perforation extends at least partially through the groove.
  • the intermediate wall in extension from the suction to the pressure side wall or vice versa on at least one of a rectilinear wall course deviating, curved trained wall portion. This curvature increases the elasticity, so that, in particular in combination with the perforated connection region of the intermediate wall, a flexible intermediate wall results.
  • the intermediate wall immediately facing the blade leading edge, which connects the suction and pressure side inner wall has a "V" or "U” -shaped wall cross-section which preferably extends over the entire radial length of the intermediate wall.
  • a solution designed according to the curvature of the intermediate wall the course extends from the suction to the pressure side wall or vice versa and allows just this spatial direction a curvature caused by bending elasticity, allows in the case of a thermally induced expansion of suction and pressure side wall in the blade leading edge region by elastic stretching of the curved Partial wall the effort of the suction and pressure side wall to give relative to each other to space.
  • the curved partition wall formed by increasing the wall curvature can follow the decreasing wall distance.
  • the turbine blade at the bottom of the "v" or "U” shaped cross section of the intermediate wall has, at least in sections, a perforation which runs parallel to the perforation of the connection region in order to increase the elasticity.
  • the mutual distance between the pressure side and the suction side wall in the blade leading edge region can be adjusted depending on the temperature level without being affected harmful mechanical stresses within the pressure and suction side wall, in particular in the connection area to the inner intermediate wall occur.
  • the intermediate wall at least partially form with an equal or preferably smaller partition wall thickness, compared to the wall thickness of the suction and pressure side wall in the blade leading edge region.
  • the intermediate wall along its entire wall cross-section must have a constant wall thickness.
  • the intermediate wall thickness, elasticity of the perforated connection region and the curvature behavior of the intermediate wall can be matched to one another in such an optimized manner that a particularly suitable transitional elasticity can be achieved. If it is necessary to realize particularly high transient elasticities, particularly highly curved and / or suitably thinly selected wall sections along the intermediate wall are suitable.
  • the measure according to the solution of an intermediate wall with a perforated connection region is not necessarily limited to the intermediate wall which directly faces the blade leading edge.
  • the "V" - or "U” -shaped wall curvature of the blade leading edge immediately facing intermediate wall is designed and arranged such that the convex wall side of the "V" - or "U” -shaped formed wall portion facing the region of the blade leading edge.
  • a row of holes is regarded as a perforation in which the proportion of the hole lengths in the perforation direction is at least 30% of the total length of the perforated area.
  • the proportion of the hole lengths is at least 50% of the total length of the perforated area. This is e.g. realized by a series of cylindrical bores, each spaced at twice the diameter. In particular, in versions with slots or slots, a proportion of the hole lengths may exceed 70% of the total length of the perforated area.
  • connection region of the intermediate wall to the pressure or suction side wall comprises, for example, up to 20% of the wall distance between the two Sidewalls.
  • connection region extends one or two wall thicknesses of the intermediate wall in the direction of connection of the intermediate wall.
  • Fig. 1 are shown schematically a vane 2 and a blade 3, as they are arranged in a not further illustrated turbine stage 1 along a guide and blade row. It is assumed that the vane 2 and the blade 3 come into contact with a hot gas flow H, which flows in the illustration from left to right, the respective airfoils 4 of the vane 2 and the blade 3.
  • the blades 4 of the guide and rotor blades 2, 3 protrude into the hot gas duct of the turbine stage 1 of a gas turbine arrangement, which is defined by radially in each case inner shrouds 2i, 3i and by the radially outer shrouds 2a of the guide vanes 2 and radially outer heat accumulation segments 3a is limited.
  • the moving blade 3 is mounted on a rotor unit R (not shown), which is rotatably mounted about a rotation axis A.
  • Fig. 2 is a cross-sectional view through a guide or blade shown, which extends along one of Fig. 1 removable sectional plane AA results.
  • the typical blade profile of a turbine guide or turbine blade is characterized by an aerodynamically profiled blade 4, which is bounded on both sides by a convex suction side wall 7 and by a concave pressure side wall 6.
  • the convex suction side wall 7 and the concave pressure side wall 6 unite in the area of the blade leading edge 5, which, as already explained, is directly exposed to the hot gas flow passing through the turbine stage of a gas turbine arrangement. It is obvious that the turbine blade area along the blade leading edge 5 experiences a particularly strong thermal load.
  • radially oriented cavities 9, 10, 11, etc. are provided within the airfoil 4, which are flushed with cooling air.
  • the individual cavities 9, 10, 11, etc. are separated by partitions 8, 12, 13, etc. mutually.
  • partitions 8, 12, 13, etc. mutually.
  • the individual cooling channels 9, 10, 11, etc. communicate with each other.
  • the foremost intermediate wall 8 is at least partially provided with a perforation 16 in the connection region to the suction 7 and / or pressure side wall 6.
  • Embodiments of perforations 16 are in the Fig. 3a, b and c shown.
  • a first embodiment is in the Fig. 3a shown.
  • a perforation 16 is provided in the connection region of the intermediate wall 8 to the suction and pressure side wall 6, 7.
  • the perforations of the example shown are a series of cylindrical holes 18, which are arranged parallel to the suction and pressure side wall 6, 7.
  • the perforation 16 on the pressure side wall 6 extends in the example only over a portion of the intermediate wall eighth
  • a second embodiment is in the Fig. 3b shown.
  • a perforation 16 is provided in the connection region of the intermediate wall 8 to the suction and pressure side wall 6, 7.
  • the perforations of this example are a series of oblong holes 19, which are arranged parallel to the suction and pressure side wall 6, 7 and whose longer side extends in each case parallel to the adjacent suction 7 or pressure side wall 6.
  • a central perforation 20 is provided, which runs parallel to the suction and pressure side walls 6, 7 in the middle of the intermediate wall 8. Together with the perforations 16 in the connection region to the suction and pressure side wall 6, 7 so a two-part partition wall 8 is formed, which can be flexibly folded.
  • FIG. 4a illustrated embodiment illustrated in detail, showing the blade profile in the blade leading edge region.
  • the Fig. 4a shows a perforation 16 in the connection region of the suction side wall 7 and in the connection region of the pressure side wall 6.
  • the main direction of the material expansion or shrinkage 21 of the side walls 6, 7 extends in the example substantially parallel to the extension of the intermediate wall. 8
  • the intermediate wall 8 has a U-shaped wall cross-section, which is connected in one piece on both sides to the suction side wall 6 as well as to the pressure side wall 7 in one piece.
  • the U-shaped wall formation of the intermediate wall 8 gives the blade profile area an additional elastic deformability such that the thermally induced material expansion or shrinkage tendency of the suction and pressure side wall can be yielded by the wall distance w not fixed, as before, but within certain limits, which is determined by the shape and curvature elasticity of the intermediate wall 8 and the elasticity of the perforation 16 is variable.
  • FIG. 4c an embodiment with an additional central perforation 20 is shown in detail.
  • This divides the intermediate wall 8 into two legs, which run starting from the connection region to the side walls 6, 7 at an angle to each other, wherein the angle can be changed flexibly by the central perforation 20 and thus expansion-related changes in the distance between the pressure and suction side wall can be easily compensated.
  • Fig. 4c an example of a possible film cooling arrangement shown.
  • the U-shaped intermediate wall 8 which is integrally connected on both sides with the inner wall of the suction 7 and 6 pressure side wall, preferably has a convex-side wall course, which faces the blade leading edge 5 and substantially parallel to the cavity 9 limiting, on the blade leading edge 5 integrally connected suction 7 and pressure side wall 6 is formed.
  • the cooling air passes in this example, at least partially through the perforations 16 and 20 Mittelperfor réelle in the front cavity.
  • FIG. 4d Another embodiment with details for cooling is in Fig. 4d shown.
  • it still has cooling air passage channels 15a, b, c, which serve for the impact air cooling of the inner wall side of the blade wall leading edge.
  • the passageways 15a, b, c can be subdivided into at least three groups with respect to their passageway longitudinal extent and the throughflow direction predetermined therewith.
  • a first group of passage channels 15a is characterized by a direction of flow directed towards the suction side wall 7
  • a second group of passage channels 15b is characterized by a flow direction directed towards the blade leading edge
  • a third group of passage channels 15c is characterized by a pressure side wall 6 Flow direction out.
  • the passageways 15a, 15b and 15c are distributed along the entire radial extent in the intermediate wall 8 and thus ensure effective and individual cooling of the blade leading edge region of the turbine blade. Of course, further passageways can be attached to the intermediate wall 8 for the purpose of optimized impingement cooling.
  • impingement air cooling can be combined with a central perforation.
  • baffled air holes have a larger diameter, eg twice the diameter, than perforation holes.

Claims (13)

  1. Aube de turbine pour une turbomachine rotative, la pale de turbine comprenant une pale (4), qui est délimitée par une paroi concave côté pression (6) et une paroi convexe côté aspiration (7), qui sont reliées au niveau d'une arête avant de pale (5) pouvant correspondre à la pale (4) et qui forment une cavité (9), s'étendant dans l'extension longitudinale de l'arête avant de la pale (5), qui est délimitée, à l'intérieur des parois, par les parois côté pression (6) et côté aspiration (7) au niveau de l'arête avant de la pale (5) ainsi que par une paroi intermédiaire (8) s'étendant dans la direction longitudinale vers l'arête avant de la pale (5), reliant à l'intérieur des parois les parois côté aspiration (7) et côté pression (6), l'aube de turbine comprenant, dans la transition entre la paroi intermédiaire (8) et les parois côté aspiration (7) et/ou côté pression (6), un arrondi ou une gorge (17),
    caractérisée en ce que la paroi intermédiaire (8) comprend, dans une partie de raccordement aux parois côté aspiration (7) et/ou côté pression (6) au moins à certains endroits une perforation (16) afin d'augmenter l'élasticité de la paroi intermédiaire dans la partie de raccordement, la partie de raccordement étant limitée à une partie à partir de la paroi côté aspiration (7) et/ou côté pression (6), qui correspond au double du rayon de l'arrondi ou de la gorge (17).
  2. Aube de turbine selon la revendication 1, caractérisée en ce que la perforation (16) comprend une rangée de trous cylindriques (18).
  3. Aube de turbine selon la revendication 1, caractérisée en ce que la perforation comprend une rangée de trous allongés (19) ou de fentes dont le côté le plus long est parallèle à la paroi côté aspiration (7) et/ou côté pression (6) adjacente.
  4. Aube de turbine selon l'une des revendications 1 à 3,
    caractérisée en ce que la partie de raccordement de la paroi intermédiaire (8) aux parois côté aspiration (7) et/ou côté pression (6) comprend une gorge (17) et en ce que la perforation (16) s'étend au moins partiellement à travers la gorge (17).
  5. Aube de turbine selon l'une des revendications 1 à 4,
    caractérisée en ce que la paroi intermédiaire (8) comprend un côté de paroi opposé à la cavité (9), qui délimite au moins une autre cavité (10) avec les parois côté aspiration (7) et côté pression (6),
    et en ce que les cavités (9, 10) sont des canaux de refroidissement dans lequel un produit de refroidissement peut être introduit.
  6. Aube de turbine selon la revendication 5,
    caractérisée en ce que les ouvertures de la perforation (16) sont réalisées parallèlement à la surface de la paroi côté aspiration (7) respectivement paroi côté pression (6) dans la partie de raccordement de la paroi intermédiaire (8) et, pendant le fonctionnement, l'air de refroidissement s'écoule à travers ces ouvertures d'une cavité (10) à l'autre cavité (9) et un jet de sortie de l'ouverture correspondante s'étendant de manière tangentielle par rapport à la paroi interne de la paroi côté aspiration (7) respectivement paroi côté pression (6) correspondante.
  7. Aube de turbine selon l'une des revendications 1 à 6,
    caractérisée en ce que la paroi intermédiaire (8) comprend, dans l'extension de la paroi côté aspiration (7) à la paroi côté pression (6) ou inversement, au moins une portion de paroi réalisée de manière courbe, s'écartant d'un tracé de paroi linéaire et en ce que l'au moins une portion de paroi courbe est réalisée de façon à ce que la portion de paroi présente une élasticité due à sa courbure en direction de l'extension de la paroi intermédiaire (8) de la paroi côté aspiration (7) vers la paroi côté pression (6) ou inversement.
  8. Aube de turbine selon la revendication 7,
    caractérisée en ce que l'au moins une portion de paroi réalisée de manière courbe est réalisée en forme de v ou en forme de u dans une section transversale coupant l'arête avant de l'aube (5).
  9. Aube de turbine selon la revendication 8,
    caractérisée en ce que l'aube de turbine comprend, à la base de la section transversale réalisée en forme de v ou en forme de u, de la paroi intermédiaire (8), au moins à certains endroits, une perforation (16) qui s'étend parallèlement à la perforation de la partie de raccordement, afin d'augmenter l'élasticité.
  10. Aube de turbine selon l'une des revendications 7 à 9,
    caractérisée en ce que le côté de paroi convexe de la portion de paroi réalisée en forme de v ou en forme de u est réalisé et disposé de manière largement parallèle à la paroi côté aspiration (7) et la paroi côté pression (6) limitant la cavité (9) et reliée à l'arête avant de l'aube (5).
  11. Aube de turbine selon l'une des revendications 7 à 10,
    caractérisée en ce que, dans la paroi intermédiaire (8), sont prévus des canaux de passage (15) pour un refroidissement par impact de la paroi côté aspiration (7) et de la paroi côté pression (6) reliées à l'arête avant de l'aube (5).
  12. Aube de turbine selon l'une des revendications 7 à 11,
    caractérisée en ce que les canaux de passage disposés à l'intérieur de la paroi intermédiaire (8) peuvent être divisés, en ce qui concerne leur direction d'écoulement prédéterminée par une extension longitudinale de canaux de passage pouvant être attribués aux canaux de passage, en au moins trois groupes : un premier groupe de canaux de passage (15a) avec une direction d'écoulement orientée vers la paroi côté aspiration (7), un deuxième groupe de canaux de passage (15b) avec une direction d'écoulement orientée vers l'arête avant de l'aube (5) ainsi qu'un troisième groupe de canaux de passage (15c) avec une direction d'écoulement orientée vers la paroi côté pression (6).
  13. Aube de turbine selon l'une des revendications 1 à 12,
    caractérisée en ce que l'aube de turbine est une aube directrice ou une aube mobile d'un étage de turbine d'une disposition de turbine à gaz.
EP13714573.6A 2012-03-22 2013-03-21 Aube de turbine Active EP2828484B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP13714573.6A EP2828484B1 (fr) 2012-03-22 2013-03-21 Aube de turbine

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP12160893 2012-03-22
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EP3199760A1 (fr) * 2016-01-29 2017-08-02 Siemens Aktiengesellschaft Aube de turbine dotée d'un élément d'étranglement
US20170234141A1 (en) * 2016-02-16 2017-08-17 General Electric Company Airfoil having crossover holes
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EP0899425A2 (fr) 1997-09-01 1999-03-03 Asea Brown Boveri AG Aube pour une turbine à gaz
WO2000012868A1 (fr) 1998-08-31 2000-03-09 Siemens Aktiengesellschaft Pale de turbine
EP1197635A2 (fr) 2000-10-12 2002-04-17 Solar Turbines Incorporated Refroidissement des aubes de turbine
US20020106275A1 (en) 2000-10-12 2002-08-08 Harvey Neil W. Cooling of gas turbine engine aerofoils
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JP6169161B2 (ja) 2017-07-26
CN104204412A (zh) 2014-12-10
JP2015511678A (ja) 2015-04-20
EP2828484A1 (fr) 2015-01-28
WO2013139926A1 (fr) 2013-09-26
CN104204412B (zh) 2016-09-28
US9932836B2 (en) 2018-04-03
CA2867960A1 (fr) 2013-09-26
US20150004001A1 (en) 2015-01-01

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