EP3369892B1 - Contournage d'une plate-forme de grille d'aube - Google Patents

Contournage d'une plate-forme de grille d'aube Download PDF

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Publication number
EP3369892B1
EP3369892B1 EP17159076.3A EP17159076A EP3369892B1 EP 3369892 B1 EP3369892 B1 EP 3369892B1 EP 17159076 A EP17159076 A EP 17159076A EP 3369892 B1 EP3369892 B1 EP 3369892B1
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EP
European Patent Office
Prior art keywords
platform
blade
edge
recess
blade cascade
Prior art date
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Active
Application number
EP17159076.3A
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German (de)
English (en)
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EP3369892A1 (fr
Inventor
Inga Mahle
Markus Brettschneider
Fadi Maatouk
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.)
MTU Aero Engines AG
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MTU Aero Engines 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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to ES17159076T priority Critical patent/ES2819128T3/es
Priority to EP17159076.3A priority patent/EP3369892B1/fr
Priority to US15/908,401 priority patent/US10648339B2/en
Publication of EP3369892A1 publication Critical patent/EP3369892A1/fr
Application granted granted Critical
Publication of EP3369892B1 publication Critical patent/EP3369892B1/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
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/129—Cascades, i.e. assemblies of similar profiles acting in parallel
    • 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 grid segment, a blade grid, a platform and a blade channel of a turbomachine and a turbomachine.
  • Fluid flow machines such as gas and steam turbines regularly have a flow channel for carrying a fluid through.
  • the flow channel which is also referred to as an annular space, is bounded radially inward by the shaft of a rotor and radially outward by a housing; the terms "radial” as well as “axial” and “circumferential direction” and terms derived therefrom are used in this Unless otherwise stated, font always refers to a (intended) axis of rotation of the rotor.
  • Blade grids are arranged in the annular space of a turbomachine (for which the term “blade ring” is also common). They each include guide vanes or rotor blades, which lie one behind the other in the circumferential direction at essentially regular intervals, as well as associated platforms, which are also referred to as “cover plates” and which each have an inflow-side and an outflow-side platform edge. These platform edges delimit the platform surface facing the blades (or blade blades) in the axial direction.
  • the "upstream” platform edge is the edge of the platform through which the (axial) main flow passing through the annular space of the turbomachine first passes
  • the “downstream” platform edge is the other edge.
  • the terms “downstream” and “upstream” relate accordingly to the main axial flow direction and only to the axial position, i.e. regardless of a possible shift in the circumferential direction:
  • a point in this document is to be understood as “downstream of the leading edges”, if it is arranged axially offset in the main flow direction for a direct connection of the leading edges on the platform surface.
  • the pressure side of one blade and the suction side of an adjacent blade each delimit a so-called blade channel in the circumferential direction.
  • this vane channel is delimited within the turbomachine by so-called side walls.
  • These are formed on the one hand by the platforms and on the other hand by radially opposite sections: in the case of rotor blades, such a side wall is a radially outer section (in particular of the housing), in the case of guide vanes a radially inner section (in particular a Rotor hub).
  • blade intermediate strip The section of the platform surface that is created in the axial direction by the direct connections of the leading edges or the trailing edges of adjacent blades on the platform surface (or by a projection of a straight connection of the named edges in the radial direction onto the platform surface) and in the circumferential direction by their suction or pressure side is limited, is referred to in this document as "blade intermediate strip".
  • the width of the blade intermediate strip in the circumferential direction is called the "pitch" of the blade grid. In particular, it can be measured as the distance between the leading edges of adjacent blades in the circumferential direction on the platform surface.
  • the depth of the space between the blades in the axial direction that is to say the distance, measured parallel to the intended axis of rotation of the turbomachine, between the leading edges of the blades and their trailing edges is referred to as the "grid width”.
  • a fluid flow guided through a flow channel is regularly influenced by the surfaces of the side walls. Flow layers that run close to these surfaces are deflected more strongly than flow layers further away from the side walls because of their lower speed. This creates a secondary flow which is superimposed on an axial main flow and which in particular leads to eddies and pressure losses.
  • contours in the form of elevations and / or depressions are often introduced into the side walls.
  • the EP 2 372 088 A2 discloses an integrally manufactured turbine blade disk which has a ring with upstream and downstream edges, between which rotor blades and - in the region of the leading edges of the rotor blades - depressions in the surface of the ring are arranged.
  • the DE 10 2010 007 985 A1 discloses a steam turbine with stator blade profiles, behind which a slot for moisture absorption is arranged. From the WO 98/44240 A1 a flow channel with a wall having a groove structure is known and from US Pat US 2008/232968 A1 a sidewall contouring for a row of blades of a turbomachine.
  • the EP 2 372 102 A2 discloses a platform section for a rotor of a gas turbine and the WO 2015/092204 A1 a turbine blade with a platform.
  • the object of the present invention is to provide an alternative technology for a turbo machine with which secondary flows can be reduced in an advantageous manner.
  • a blade grid segment according to the invention for a blade grid of a turbomachine comprises a platform and at least two (adjacent) blade blades which, according to the above, define an intermediate blade strip with an axial grid width through their inflow and outflow edges on the platform surface.
  • the platform has an upstream platform edge which has a contour with a depression. In the axial direction, this recess extends into the blade intermediate strip by at most 10% of the grid width.
  • the depression can be arranged completely upstream of the leading edges, that is to say not protrude into the intermediate blade strip.
  • the depression is to be understood as a local expression of a line that results from the cross-section of a two-dimensional line Platform surface (flat) recess along the platform edge results.
  • a “depression” is to be understood as a local formation in the platform surface in which the latter extends towards the side facing away from the blade blades.
  • the designation (as well as terms such as “lowered” or the like) is based on an orientation or a coordinate system in which the blades extend “up” from the platform surface and a depression accordingly in the opposite direction (down "down”) ) leads.
  • the depression is thus arranged completely in the interior of a surface strip of the platform surface, the outflow-side delimitation of which extends in the axial direction by at most 10% of the grid width downstream of the leading edges; in particular in relation to this limitation, the depression is lowered in all its points (whereby an edge of the depression can be regarded as not belonging to it).
  • the recess is preferably formed continuously. According to a special embodiment, the outflow-side delimitation does not even run further than (at most) 5% of the grid width downstream of the leading edges of the blades.
  • a blade grid segment according to the invention can be in one piece or assembled.
  • the platform can be in one piece or comprise two or more parts, from each of which one of the impeller blades protrudes, or the platform can be designed as at least one separate component that is or can be arranged between the impeller blades.
  • a platform according to the invention is set up to adjoin a blade in the circumferential direction on each side and, together with the blades (none, one or both of which can be permanently formed on the platform), together a blade grid segment according to the invention according to one of those disclosed in this document Form embodiments.
  • a blade grid according to the invention comprises at least one blade grid segment according to the invention in accordance with one of the embodiments disclosed in this document.
  • a turbomachine according to the invention comprises one or more blade grids according to the invention.
  • a blade channel according to the invention leads through a blade channel according to the invention
  • Blade grid segment according to one of the embodiments disclosed in this document is therefore limited by such a blade grid segment and a side wall opposite its platform (facing the platform surface).
  • the vane channel is delimited in the circumferential direction by the pressure side of one of the vane blades of the vane grid segment and by the suction side of the (adjacent) other of the vane blades opposite this.
  • a blade grid segment according to the invention, a blade grid according to the invention, a blade channel according to the invention, a platform according to the invention and a turbomachine according to the invention each enable an improvement in the secondary flows and thus a reduction in losses in the respective hub or housing area. In this way, a high degree of efficiency of the turbomachine can be achieved.
  • the blade grid segment or the blade grid or the flow channel or the platform can in particular be part of a low-pressure turbine.
  • the vane grid can be a guide vane grid or a rotor blade grid, so the blade blades can each be guide blades or rotor blade blades.
  • the platform can be designed to delimit a vane channel through the vane lattice segment to the radially inward or radially outward direction.
  • the platform edge on the inflow side is preferably designed to be used (at least essentially) adjacent to a further (separate) element (for example the hub or the housing or another vane grille) in the turbomachine. It can be set up to form a section of a wall of a gap through which cooling fluid is or can be introduced into the annular space of the turbomachine.
  • the platform edge on the inflow side (which can comprise sections of several parts of a multi-part platform) is preferably delimited by the (circumferential direction) positions of the leading edges of the two blades; these boundaries can have a physical expression (for example, in that the platform ends in them in perimeter viewing) or they can only be defined or defined abstractly to define the platform edge on the upstream side.
  • the platform edge on the inflow side preferably has an extent (or length) in the circumferential direction which is (essentially) equal to the pitch.
  • An embodiment of the present invention has proven to be particularly advantageous in which the depression extends along the platform edge on the inflow side (preferably continuously) over at least 50% of the pitch.
  • the depression preferably has a positive distance (> 0) from the pressure side of one of the blades and / or from the suction side of the other blade, so that it does not touch the respective side.
  • the recess can be spaced equally or differently from the two blades.
  • the distance from the depression to the leading edge of one vane e.g. the one on whose pressure side the vane interspace region is adjacent
  • the distance between the recess and the leading edge of the other vane can be greater or smaller than the distance between the recess and the leading edge of the other vane.
  • an embodiment of the present invention has proven to be advantageous in which the upstream platform edge (or its contour) is designed asymmetrically to its radial central axis, that is, a radial axis that runs through the center of the upstream platform edge.
  • the platform surface comprises a surface area which is arranged between the depression and a pressure side of one (the first) of the airfoils.
  • a surface area is preferably covered by the platform edge on the inflow side.
  • the contour of the platform edge on the inflow side then comprises an edge of the surface area, which is referred to below as the “pressure-side” surface area.
  • an edge section of the platform edge on the inflow side, in which it covers the surface area on the pressure side can extend in the circumferential direction preferably over at least 10% or at least 20% of the pitch.
  • Each point of the depression is preferably lowered compared to each point of the pressure-side surface area (in the radial direction).
  • the platform surface can comprise a surface area which is arranged between the depression and a suction side of the other (second) of the airfoils.
  • a surface area is preferably formed by the platform edge on the inflow side detected.
  • the contour of the platform edge on the inflow side then comprises an edge of the surface area, which is referred to below as the “suction-side” surface area.
  • an edge section of the platform edge on the inflow side, in which it covers the surface area on the suction side can extend in the circumferential direction preferably over at least 10% or at least 20% of the pitch.
  • Each point of the depression is preferably lowered compared to each point of the suction-side surface area (in the radial direction).
  • the platform surface thus includes both a pressure-side and a suction-side surface section (possibly with the further properties mentioned).
  • an edge section in which the inflow-side platform edge encompasses the suction-side surface area is larger than an edge section of the inflow-side platform edge in which it encompasses the suction-side surface area; in another variant it is the other way round, and in a further embodiment both sections are of the same size.
  • the platform surface can be designed to be uncontoured.
  • FIG. 1 is schematically an exemplary (developed) embodiment of a Vane grid segment 1 according to the invention shown in plan view; the viewing direction corresponds to the radial direction (outwards or inwards, depending on whether the platform 10 is part of an outer or an inner side wall).
  • the vane grid segment comprises adjacent vane blades 20, 30 and a platform 10 according to the invention, which has a platform surface 12, an inflow-side platform edge 10a (with reference to the intended axial main flow direction X) and an outflow-side platform edge 10b.
  • the upstream platform edge 10a can - although not shown - comprise sections of several parts of a multi-part platform. It is limited by the (circumferential) positions of the leading edges 23, 33 of the two blades 20, 30; In particular, the extent (or length) of the platform edge 10a on the inflow side in the circumferential direction is thus equal to the pitch t.
  • the result is an (axial) grid width g.
  • the platform surface has a recess 13 which is captured by the platform edge 10a on the inflow side.
  • the inflow-side platform edge 10a In cross-section (along a plane to which the intended axis of rotation is normal) it follows that the inflow-side platform edge 10a has a contour with the recess 13 (in the form of a depression) (not shown directly in the figure, but implied by it) .
  • the recess is arranged completely upstream of the blade intermediate strip 11. It extends continuously along the platform edge 10a on the inflow side (that is to say continuously) over an extent d which is greater than 50% of the division t.
  • an outflow-side delimitation 13b of the recess 13 has an axial distance, which changes with its course, from the inflow-side platform edge 10a;
  • an outflow-side delimitation of the recess 13 could extend essentially without axial deviations in the circumferential direction U, in a radial projection onto the The platform surface thus run parallel to the platform edge 10a on the inflow side (not shown).
  • the platform surface has a pressure-side surface section 14 arranged between the pressure side 21 of the airfoil 20 and the recess 13 and reaching the front platform edge 10a as well as a suction-side surface section 15 arranged between the suction side 32 of the airfoil 30 and the recess 13 and reaching the front platform edge .
  • the recess 13 is completely lowered in the radial direction compared to each point of the pressure-side section 14 and each point of the suction-side section 15 (which is again not visible in the figure due to the representation as a plan view).
  • the pressure-side surface section 14 reaching up to the front platform edge 10a extends in a continuous edge section 14a along the front platform edge 10a.
  • the suction-side section 15 reaching the front platform edge extends in a continuous edge section 15a along the front platform edge 10a.
  • the edge portion 15a is smaller than the edge portion 14a.
  • the upstream platform edge 10a is asymmetrical to its radial central axis (not shown in the figure), that is to say to a radial axis which runs through the center of the upstream platform edge 10a.
  • FIG 2 shows schematically a developed alternative embodiment of a blade grid segment 1 'according to the invention in a plan view. It has like that in Figure 1
  • the vane grid segment 1 shown has vane blades 20, 30 and a platform 10 according to the invention with an upstream platform edge 10a (based on the intended, axial main flow direction X) and a downstream platform edge 10b.
  • the platform surface of the platform 10 of the blade lattice segment 1 ′ comprises a recess 13 ′ which runs along the platform edge 10a on the inflow side and is covered by the platform edge 10a on the inflow side.
  • a contour encompassing the recess 13 'in the form of a contiguous depression in the inflow side platform edge 10a (again not shown directly in the figure, but implied by it) .
  • An outflow-side delimitation 13'b of the recess 13 ' also has in FIG Figure 2
  • the example shown shows a distance in the axial direction that changes with its course from the platform edge 10a on the inflow side;
  • an outflow-side delimitation of the recess extends essentially without axial deviations in the circumferential direction (ie runs parallel to the inflow-side platform edge 10a in the projection onto the platform surface).
  • the recess 13 ' is arranged in the interior of a surface strip of the platform surface 12', the downstream boundary of which runs in the circumferential direction and is located downstream of the leading edges 23, 33 of the blades 20, 30 by the axial distance a.
  • a 0.1g applies, where g is the axial grid width.
  • the recess 13 ′ thus protrudes at most 10% of the axial grid width g into the blade intermediate strip 11.
  • the platform surface has a pressure-side surface section 14 'arranged between the pressure side 21 of the airfoil 20 and the depression 13' and reaching the front platform edge 11, as well as a suction-side surface section 14 'arranged between the suction side 32 of the airfoil 30 and the recess 13' and reaching the front platform edge Surface section 15 '.
  • the recess 13 ' is completely lowered in the radial direction compared to each point of the pressure-side section 14' and each point of the suction-side section 15 '(which in turn is not visible in the figure due to the representation as a top view).
  • the surface section 14 'on the pressure side reaching the front platform edge extends in an edge section 14'a continuously along the front platform edge 10a.
  • the suction-side section 15 'reaching the front platform edge extends continuously in an edge section 15'a along the front platform edge 10a.
  • the edge section 15'a is larger than the edge section 14'a; In a special embodiment, the edge section 15'a can be at least 1.5 times or even at least twice as large as the edge section 14'a.
  • a blade grid segment 1, 1 'for a blade grid of a turbomachine which comprises a platform 10 and at least two blade blades 20, 30 which, through their inflow and outflow edges 23, 33, 24, 34, form an intermediate blade strip 11 with an axial grid width on the platform surface determine g.
  • An upstream Platform edge 10a has a contour with a recess 13, 13 '. In the axial direction, this recess 13, 13 ′ extends into the blade intermediate strip 11 by at most 10% of the grid width g.
  • a corresponding platform, a blade grid, a blade channel and a turbo-machine are also disclosed.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (14)

  1. Segment de grille d'aube (1, 1') destiné à une grille d'aube d'une turbomachine, le segment de grille d'aube comprenant une plate-forme (10) comportant une surface de plate-forme (12) et un bord de plate-forme côté attaque (10a), ainsi qu'au moins deux pales d'aube (20, 30) qui déterminent, par leurs bords d'attaque et leurs bords de fuite (23, 33, 24, 34), sur la surface de plate-forme (12), une bande d'aube intermédiaire (11) ayant une largeur de grille axiale (g),
    le bord de plate-forme côté attaque (10a) présentant un contour comportant une dépression (13, 13') sous la forme d'une cavité, la dépression (13, 13') s'étendant à l'intérieur de la bande d'aube intermédiaire (11) dans la direction axiale sur au plus 10 % de la largeur de grille (g),
    caractérisé en ce que
    la dépression (13, 13') s'étend en continu le long du bord de plate-forme côté attaque (10a) sur au moins 50 % de la distance de pas (t).
  2. Segment de grille d'aube selon la revendication 1, la surface de plate-forme (12) présentant une section de surface (14) côté pression, laquelle est disposée entre un côté de pression (21) d'une première pale d'aube (20) des au moins deux pales d'aube (20, 30) et la dépression (13), et se prolonge jusqu'au bord de plate-forme côté attaque (10a), et présentant une section de surface (15) côté aspiration, laquelle est disposée entre un côté d'aspiration (32) d'une seconde pale d'aube (30) des au moins deux pales d'aube (20, 30) et la dépression (13), et se prolonge jusqu'au bord de plate-forme côté attaque (10a), la dépression (13) étant complètement renfoncée dans la direction radiale par rapport à chaque point de la section côté pression (14) et à chaque point de la section côté aspiration (15).
  3. Segment de grille d'aube (1, 1') selon la revendication 1, la surface de plate-forme comprenant une zone de surface côté pression (14, 14') qui est disposée entre un côté de pression (21) de l'une des pales d'aube (20) et la dépression (13, 13').
  4. Segment de grille d'aube (1, 1') selon la revendication 2 ou 3, une section de bord (14a, 14'a) dans laquelle le bord de plate-forme côté attaque (10a) retient la zone de surface côté pression (14, 14') comprenant au moins 10 % ou au moins 20 % de la distance de pas (t).
  5. Segment de grille d'aube (1, 1') selon la revendication 1, la surface de plate-forme comprenant une zone de surface côté aspiration (15, 15') qui est disposée entre un côté d'aspiration (32) de l'une des pales d'aube (30) et la dépression (13, 13').
  6. Segment de grille d'aube (1, 1') selon la revendication 2 ou 5, une section de bord (15a, 15'a) dans laquelle le bord de plate-forme côté attaque (10a) retient la zone de surface côté aspiration (15, 15') comprenant au moins 10 % ou au moins 20 % de la distance de pas (t).
  7. Segment de grille d'aube selon l'une des revendications précédentes, la dépression (13) étant disposée complètement en amont des bords d'attaque (23, 33).
  8. Segment de grille d'aube selon l'une des revendications précédentes, la grille d'aube étant une grille d'aube directrice ou une grille d'aube mobile.
  9. Segment de grille d'aube selon l'une des revendications précédentes, une délimitation côté fuite (13'b) de la dépression s'étendant sensiblement parallèlement au bord de plate-forme côté attaque (10a).
  10. Segment de grille d'aube selon l'une des revendications précédentes, le bord de plate-forme côté attaque (10a) étant réalisé de manière asymétrique par rapport à son axe central radial.
  11. Grille d'aube comportant deux ou plus segments de grille d'aube (1, 1') selon l'une des revendications précédentes.
  12. Canal d'aube d'une turbomachine, lequel canal est délimité par un segment de grille d'aube (1, 1') selon l'une des revendications 1 à 10 ainsi que par une paroi latérale faisant face à la plate-forme (10) du segment de grille d'aube.
  13. Plate-forme (10) destinée à un segment de grille d'aube selon l'une des revendications 1 à 10, la plate-forme étant conçue de sorte à être contiguë aux au moins deux pales d'aube (20, 30) dans la direction circonférentielle (U).
  14. Turbomachine comportant au moins une grille d'aube selon la revendication 11.
EP17159076.3A 2017-03-03 2017-03-03 Contournage d'une plate-forme de grille d'aube Active EP3369892B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
ES17159076T ES2819128T3 (es) 2017-03-03 2017-03-03 Contorneo de una plataforma de una rejilla de paletas
EP17159076.3A EP3369892B1 (fr) 2017-03-03 2017-03-03 Contournage d'une plate-forme de grille d'aube
US15/908,401 US10648339B2 (en) 2017-03-03 2018-02-28 Contouring a blade/vane cascade stage

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Application Number Priority Date Filing Date Title
EP17159076.3A EP3369892B1 (fr) 2017-03-03 2017-03-03 Contournage d'une plate-forme de grille d'aube

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EP3369892A1 EP3369892A1 (fr) 2018-09-05
EP3369892B1 true EP3369892B1 (fr) 2020-08-19

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US10648339B2 (en) 2020-05-12
EP3369892A1 (fr) 2018-09-05
ES2819128T3 (es) 2021-04-15
US20180252107A1 (en) 2018-09-06

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