EP3358135B1 - 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
EP3358135B1
EP3358135B1 EP17154853.0A EP17154853A EP3358135B1 EP 3358135 B1 EP3358135 B1 EP 3358135B1 EP 17154853 A EP17154853 A EP 17154853A EP 3358135 B1 EP3358135 B1 EP 3358135B1
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EP
European Patent Office
Prior art keywords
elevation
blade row
blade
platform
axial
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.)
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Application number
EP17154853.0A
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German (de)
English (en)
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EP3358135A1 (fr
Inventor
Markus Brettschneider
Inga Mahle
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MTU Aero Engines AG
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MTU Aero Engines AG
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Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP17154853.0A priority Critical patent/EP3358135B1/fr
Priority to ES17154853T priority patent/ES2857568T3/es
Priority to US15/886,977 priority patent/US10590773B2/en
Publication of EP3358135A1 publication Critical patent/EP3358135A1/fr
Application granted granted Critical
Publication of EP3358135B1 publication Critical patent/EP3358135B1/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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
    • 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
    • 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
    • F05D2240/123—Fluid guiding means, e.g. vanes related to the pressure side of a stator vane
    • 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
    • F05D2240/124—Fluid guiding means, e.g. vanes related to the suction side of a stator vane
    • 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 “annular space”, is delimited radially inward by the shaft of a rotor and radially outward by a housing; the terms “radial” as well as “axial” and “circumferential direction” as well as terms derived therefrom are to be understood in this document - unless otherwise stated - always in relation to an 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” or “upstream” relate accordingly to the axial main 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 referred to as "downstream of the leading edges" (or downstream one other point) is to be understood lying when compared to a direct connection of the leading edges on the platform surface (or compared to the other point) it is arranged axially offset in / with the main flow direction (i.e. following it);
  • upstream with the opposite direction.
  • the distance between the leading edges of the airfoils and their trailing edges, measured in the direction of the intended axial main flow, is called the (axial) "grid width”.
  • 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 opposing sections of these platforms:
  • 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).
  • 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 pamphlet US 2012/051 900 A1 discloses a guide vane grid with a sidewall contouring in which a platform surface between the pressure side of one of the airfoils and the suction side of another of the airfoils each has an elevation and a depression, which together form an axially extending, curved channel.
  • a blade grille with a platform is known, the surface of which grows from the leading and trailing edges of the blades Has elevations. Furthermore, reference is also made to the pamphlets US20080232968A1 and NO20130204A1 referenced, which also give examples of sidewall contouring.
  • the object of the present invention is to provide a technique with which secondary flows in the annular space of a turbomachine can advantageously be further reduced. The object is achieved by a blade grid segment according to claim 1, a blade grid according to claim 9, a blade channel according to claim 10, and a turbomachine according to claim 11. Advantageous embodiments are specified in the subclaims.
  • a blade grid segment according to the invention for a blade grid (e.g. a rotor blade grid or a guide vane grid) of a turbomachine comprises at least two (preferably adjacent in the blade grid) blade blades and a platform.
  • the airfoils each have a leading edge and a trailing edge, which define an axial grid width.
  • the platform (which can form part of a radially inner or a radially outer side wall of a blade channel) has an inflow-side platform edge and a platform surface. This has at least one elevation extending to the pressure side of a first of the blade blades and at least one depression extending to the suction side of the other (that is to say the second) of the blade blades.
  • At least one highest point of the at least one elevation and at least one lowest point of the at least one depression are each at least 30% and at most 60% of the axial grid width downstream of the leading edges of the airfoils.
  • the at least one elevation and the at least one depression each extend as far as the platform edge on the inflow side.
  • the at least one highest point of the elevation is arranged downstream of the at least one lowest point of the depression.
  • a blade grid segment according to the invention can have one or more elevations or one or more depressions, each with the properties mentioned above and / or below.
  • the indication "at least one" is sometimes omitted for the survey and the deepening in the following for reasons of better readability.
  • an “elevation” is to be understood as a local formation (such as, for example, a hump or projection) in the platform surface, in which it extends towards the side facing the blade blades.
  • a “depression” is analogously a local formation in the platform surface in the other direction (that is to say to the opposite direction from the blade blades Side) to understand (such as a sink or niche).
  • the highest or lowest points are understood to be the points of the elevation or depression in which it extends the furthest in the respective direction.
  • the highest or lowest points can each form a surface section or a curve or be singular.
  • the elevation has precisely one highest point and / or the depression has precisely one lowest point.
  • the platform surface can comprise a (e.g., non-contoured) surface section which preferably extends as far as (or comprises) the downstream platform edge and which defines a zero surface in the sense that an elevation lies radially above and a depression lies radially below the zero surface.
  • said surface section preferably has essentially the same curvature as the platform edge on the downstream side; in particular, it can be flat if the platform edge on the downstream side is straight.
  • the platform edge on the inflow side is preferably designed to be used (at least essentially) adjacent to another (separate) element (e.g. the hub or the housing or another blade 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 limitations can be of a physical nature (e.g. in that the platform ends in them in perimeter view) or they can only be defined or defined abstractly for the definition of the upstream platform edge.
  • the at least one elevation and the at least one depression can be in the circumferential direction merge into one another at least in one area of the platform surface, i.e. only be separated there by a curve (lying on the platform surface) (which then describes a zero height line); an area around the curve can be described mathematically as a graph of a totally differentiable function, so its directional derivatives in the circumferential direction are different from zero at all points on the curve.
  • the curve can extend from the platform edge on the inflow side, so it can reach it.
  • the curve preferably has an extension of at least 20%, at least 30% or even at least 50% of the axial grid width.
  • the at least one elevation and the at least one depression can be separated at least in a section of the platform surface by an uncontoured partial area of the platform surface, which separates the elevation and the depression in the section in the circumferential direction from one another (and then thus describes a zero surface).
  • 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 blades protrudes, or the platform can be designed as a separate component that is or can be arranged between the blades.
  • a platform according to the invention is set up to adjoin a blade in the circumferential direction on each side and to form a blade grid segment according to the invention in accordance with one of the embodiments disclosed in this document together with the blades (none, one or both of which can be permanently molded to the platform) .
  • 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 grid segment according to the invention according to one of the embodiments disclosed in this document, that is to say is limited by such a blade grid segment and a side wall opposite its platform (facing the platform surface).
  • the blade channel is in the circumferential direction through the pressure side of one of the blades of the blade grid segment and through the latter opposite suction side of the (adjacent) other of the blades limited.
  • a blade grid segment according to the invention, a blade grid according to the invention, a blade channel according to the invention, and a turbomachine according to the invention influence the static pressure field on the platform surface and on the blades in the edge area through the geometry of the platform surface according to the invention. This enables a reduction in the secondary flow, in particular of eddies in the blade channel. In this way, losses can be reduced and the inflow into a further blade grille, possibly located downstream, can be improved.
  • the blade lattice segment or the blade lattice or the flow channel can in particular be part of a low-pressure turbine or be set up to be installed or used in a low-pressure turbine.
  • the blades can each be guide blades or rotor blades.
  • the first blade can, in particular, be based at least partially on the elevation and / or the second blade can be at least partially based in the depression.
  • An embodiment variant is advantageous in which the at least one highest point of the elevation lies on a boundary line between the first blade (or its pressure side) and the platform surface. In the vicinity of such a highest point, the platform surface can be convex or concave.
  • the deepest point of the depression can (if necessary additionally) lie on a boundary line between the second blade (or its suction side) and the platform surface. In the vicinity of such a deepest point, the platform surface can be convex or concave.
  • An embodiment of the present invention has proven to be advantageous in which the respective axial positions of the at least one highest point of the elevation and of the at least one lowest point of the depression differ from one another by at most 10% of the axial grid width.
  • the highest and lowest points are in one Surface strip of the platform between the blades, the upstream and downstream boundaries of which run in the circumferential direction and which has a width of 10% of the grid width in the axial direction.
  • such a surface strip is crossed in the axial direction by a curve in which the at least one elevation and the at least one depression merge into one another as described above.
  • the platform edge on the inflow side can cover the at least one elevation and / or the at least one depression.
  • the elevation or depression can therefore run into the platform edge on the inflow side, so that this itself (viewed as a one-dimensional curve) has a contour, preferably runs in a curved manner.
  • the upstream platform edge can have a maximum (a rise) in the area of the elevation (or an extension of the elevation) and / or a minimum (a depression) in the area of the depression (or an extension of the depression); the terms "maximum” and “minimum” are to be understood analogously to the terms “elevation” and "deepening”.
  • the platform surface has at least one further elevation which extends towards the suction side of the other (second) of the blades.
  • a further elevation is preferably arranged upstream of the at least one depression.
  • a highest point of the at least one further elevation is preferably at most 15% or even at most 10% of the axial lattice width downstream of the leading edges of the blades.
  • the further elevation in the circumferential direction can merge into the at least one depression in at least one area of the platform surface, i.e. there only be separated by a line (lying on the platform surface) (which then describes a zero height line) ; an area around the curve can be described mathematically as a graph of a totally differentiable function, so its directional derivatives in the circumferential direction are different from zero at all points of the line.
  • the further elevation is completely separated from the at least one depression in the circumferential direction by such a line.
  • the line can extend from the platform edge on the inflow side, and / or at least one of the ends or both ends of the line can reach up to the suction side of the second airfoil.
  • the second blade can be partially based on the further elevation.
  • An embodiment has proven to be advantageous in which the further elevation has its highest point (s) on a boundary line between the second blade (or its suction side) and the platform surface. In the vicinity of this point or these points, the platform surface can be convex or concave.
  • FIG. 1 an exemplary developed embodiment of a blade grid segment 1 according to the invention is shown schematically in a plan view (with a radial viewing direction). It comprises blade blades 20, 30, each having a pressure side and a suction side, as well as a platform 10 according to the invention with an inflow-side platform edge 10a (based on the intended main flow direction X) and an outflow-side platform edge 10b.
  • the platform can be constructed in one piece or, for example, in two parts (not shown), in particular it can comprise two parts, from which one of the blades 20, 30 protrudes.
  • the blade blades 20, 30 define an axial grid width g by the distance of their leading edges 23, 33 from their trailing edges 24, 34 on the platform surface, measured in the axial main flow direction X.
  • the platform surface has one that extends as far as the pressure side 21 of the one (first) airfoil 20, in which Figure 1 Elevation 11 with a highest point 12, illustrated by contour lines. As can be seen from the contour lines, the blade 20 is based partially (namely in its front region) on the elevation 11.
  • the platform surface has a surface extending to the suction side 31 of the other (second) airfoil 30, in which Figure 1 Depression 13, again illustrated by contour lines, with a deepest point 14.
  • Figure 1 Depression 13 again illustrated by contour lines, with a deepest point 14.
  • the blade 30 is partially based (namely in its front area) in the depression 13.
  • the highest point 12 and the lowest point 14 lie in an intermediate strip Z of the platform surface.
  • the inflow-side and outflow-side boundaries of the intermediate strip Z each run parallel to the inflow-side platform edge 10a.
  • both the elevation 11 and the depression 13 extend up to the platform edge 10a on the inflow side.
  • the highest point 12 of the elevation 11 has an axial position 12a, and the lowest point 14 of the recess analogously has an axial position 14a.
  • these positions 12a, 14a are at a distance d from one another;
  • d 0.1g applies, so that the named axial positions differ from one another in the axial direction by at most 10% of the axial grid width g.
  • FIG. 2 shows another embodiment of a developed blade lattice segment 1 'in plan view (with a radial viewing direction). Like that in Figure 1 Vane grid segment 1 shown, blade blades 20, 30 and a platform 10 with a platform surface and an upstream platform edge 10a (based on the intended, axial main flow direction X) and a downstream platform edge 10b.
  • the airfoil segment 1 shown also has the platform surface of the in Figure 2
  • the vane lattice segment 1 'shown has an elevation 11' extending to the pressure side 21 of one (first) airfoil 20 with a highest point 12 'and a depression 13' extending to the suction side 31 of the other (second) airfoil 30 with a lowest point 14 '.
  • the highest point 12 'of the elevation and the lowest point 14' of the depression are both in the intermediate strip Z, which is defined as described above by the distances a, b, are therefore at least 30% and at most 60% of the axial grid width g downstream of the Leading edges 23, 33 of the blades 20, 30 are arranged.
  • the upstream platform edge 10a detects the elevation 11 'in a section 11'a.
  • the upstream platform edge 10a therefore also has a (in the Figure 2 not shown) by having a local maximum (as a graph of a one-dimensional function) in area 11'a.
  • the blade grid segment 1 ′ also has a further elevation 15 ′, which extends as far as the suction side 32 of the second blade 30.
  • the further elevation 15 ' is arranged upstream of the recess 13'.
  • a blade grid segment 1, 1 ′ of a blade grid of a turbomachine which comprises at least two blade blades 20, 30, which determine an axial grid width g, and a platform 10 with a platform surface and an upstream platform edge 10a.
  • the platform surface has an elevation 11, 11 'extending to the pressure side 21 of a first of the impeller blades 20 and a recess 13, 13' extending to the suction side 32 of the other of the impeller blades 30.
  • At least one highest point 12, 12 'of the elevation 11, 11' and at least one lowest point 14, 14 'of the recess 13, 13' are each at least 30% and at most 60% of the axial grid width g downstream of the leading edges 23, 33 of the blades 20, 30.
  • the elevation 11, 11 'and the recess 13, 13' each extend as far as the platform edge 10a on the inflow side.
  • a vane grille, a vane channel and a fluid flow machine are also disclosed.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (11)

  1. Segment de grille d'aubes (1, 1') d'une grille d'aubes d'une turbomachine, le segment de grille d'aubes comprenantau moins deux pales d'aubes (20, 30) comportant respectivement un bord d'attaque et de fuite (23, 33, 24, 34) ainsi qu'une plate-forme (10) comportant une surface de plate-forme ainsi qu'un bord de plate-forme côté attaque (10a), une largeur axiale de grille (g) étant déterminée parla distance, mesurée dans la direction du flux axial principal prévu, des bords d'attaque (23, 33) des pales d'au bes (20, 30) à partir de leurs bords de fuite (24, 34),
    la surface de plate-forme présentant une élévation (11, 11') s'étendant jusqu'au côté pression (21) d'une première pale d'aubes (20) et une cavité (13, 13') s'étendant jusqu'au côté aspiration (32) de l'autre pale d'aubes (30),
    au moins un point (12, 12') le plus élevé de l'élévation (11, 11') et au moins un point (14, 14') le plus bas de la cavité (13, 13') étant respectivement situés à au moins 30 % et à au plus 60 % de la largeur axiale de grille (g) en aval des bords d'attaque (23, 33) des pales d'aubes (20, 30) et
    l'élévation (11, 11') et la cavité (13, 13') s'étendant respectivement jusqu'au bord de plate-forme (10a) côté attaque, le segment de grille d'aubes (1, 1') étant caractérisé en ce que l'au moins un point (12) le plus élevé de l'élévation (11) est disposé en aval de l'au moins un point (14) le plus bas de la cavité (13).
  2. Segment de grille d'aubes (1, 1') selon la revendication 1, dans lequel les positions axiales (12a, 14a) de l'au moins un point (12, 12') le plus élevé de l'élévation (11, 11') et de l'au moins un point (14, 14') le plus bas de la cavité diffèrent l'une de l'autre de 10 % au plus de la largeur axiale de grille (g).
  3. Segment de grille d'aubes (1, 1') selon l'une des revendications précédentes, dans lequel le bord de plate-forme (10a) côté attaque recouvre l'élévation (11') et/ou la cavité.
  4. Segment de grille d'aubes (1') selon l'une des revendications précédentes, dans lequel la surface de plate-forme présente également une élévation supplémentaire (15') qui s'étend jusqu'au côté aspiration (32) de l'autre pale d'aubes (30).
  5. Segment de grille d'aubes (1') selon la revendication 4, dans lequel l'élévation supplémentaire (15') est disposée en amont de la cavité (13').
  6. Segment de grille d'aubes (1') selon la revendication 4 ou 5, dans lequel un point le plus élevé de l'élévation supplémentaire se situe à 15 % au plus, voire à 10 % au plus, de la largeur axiale de grille en aval des bords d'attaque des pales d'aubes.
  7. Segment de grille d'aubes (1') selon l'une des revendications 4 à 6, dans lequel l'élévation supplémentaire (15') comporte au moins un point le plus élevé qui est situé sur une ligne de délimitation de la surface de plate-forme, sur le côté aspiration (32) de l'autre pale d'aubes.
  8. Segment de grille d'aubes (1, 1') selon l'une des revendications précédentes, dans lequel la grille d'aubes est une grille d'aubes directrices ou une grille d'aubes mobiles.
  9. Grille d'aubes destinée à une turbomachine, comprenantau moins un segment de grille d'aubes (1, 1') selon l'une des revendications précédentes.
  10. Canal d'aubes d'une turbomachine, lequel est délimité par un segment de grille d'aubes (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'aubes.
  11. Turbomachine comportant au moins une grille d'aubes selon la revendication 9.
EP17154853.0A 2017-02-06 2017-02-06 Contournage d'une plate-forme de grille d'aube Active EP3358135B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP17154853.0A EP3358135B1 (fr) 2017-02-06 2017-02-06 Contournage d'une plate-forme de grille d'aube
ES17154853T ES2857568T3 (es) 2017-02-06 2017-02-06 Contorneo de una plataforma de una rejilla de paletas
US15/886,977 US10590773B2 (en) 2017-02-06 2018-02-02 Contouring a blade/vane cascade stage

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17154853.0A EP3358135B1 (fr) 2017-02-06 2017-02-06 Contournage d'une plate-forme de grille d'aube

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EP3358135A1 EP3358135A1 (fr) 2018-08-08
EP3358135B1 true EP3358135B1 (fr) 2021-01-27

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EP (1) EP3358135B1 (fr)
ES (1) ES2857568T3 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2819128T3 (es) * 2017-03-03 2021-04-15 MTU Aero Engines AG Contorneo de una plataforma de una rejilla de paletas
JP7232034B2 (ja) * 2018-12-18 2023-03-02 三菱重工業株式会社 タービン翼及びこれを備えた蒸気タービン
US11639666B2 (en) * 2021-09-03 2023-05-02 Pratt & Whitney Canada Corp. Stator with depressions in gaspath wall adjacent leading edges

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7220100B2 (en) 2005-04-14 2007-05-22 General Electric Company Crescentic ramp turbine stage
US7465155B2 (en) * 2006-02-27 2008-12-16 Honeywell International Inc. Non-axisymmetric end wall contouring for a turbomachine blade row
US8459956B2 (en) * 2008-12-24 2013-06-11 General Electric Company Curved platform turbine blade
US8727716B2 (en) 2010-08-31 2014-05-20 General Electric Company Turbine nozzle with contoured band
EP2487329B1 (fr) 2011-02-08 2013-11-27 MTU Aero Engines GmbH Canal d'aube doté d'une définition de contour de la paroi latérale et turbomachine associé
US9194235B2 (en) * 2011-11-25 2015-11-24 Mtu Aero Engines Gmbh Blading
US9103213B2 (en) * 2012-02-29 2015-08-11 General Electric Company Scalloped surface turbine stage with purge trough
EP2787171B1 (fr) 2012-08-02 2016-06-22 MTU Aero Engines GmbH Grille d'aubes avec définition de contour de la paroi latérale et turbomachine
EP2696029B1 (fr) 2012-08-09 2015-10-07 MTU Aero Engines AG Grille d'aube avec définition de contour de la paroi latérale et turbomachine
ES2535096T3 (es) * 2012-12-19 2015-05-05 MTU Aero Engines AG Rejilla de álabe y turbomáquina
US9376927B2 (en) * 2013-10-23 2016-06-28 General Electric Company Turbine nozzle having non-axisymmetric endwall contour (EWC)
WO2015195112A1 (fr) * 2014-06-18 2015-12-23 Siemens Energy, Inc. Configuration de paroi d'extrémité pour moteur de turbine à gaz
DE102015224420A1 (de) * 2015-12-07 2017-06-08 MTU Aero Engines AG Ringraumkonturierung einer Gasturbine
DE102016211315A1 (de) * 2016-06-23 2017-12-28 MTU Aero Engines AG Lauf- oder Leitschaufel mit erhabenen Bereichen

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
EP3358135A1 (fr) 2018-08-08
US20180223670A1 (en) 2018-08-09
ES2857568T3 (es) 2021-09-29
US10590773B2 (en) 2020-03-17

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