EP3055506B1 - Turbomaschinenteil mit nicht-axialsymmetrischer oberfläche - Google Patents

Turbomaschinenteil mit nicht-axialsymmetrischer oberfläche Download PDF

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Publication number
EP3055506B1
EP3055506B1 EP14824048.4A EP14824048A EP3055506B1 EP 3055506 B1 EP3055506 B1 EP 3055506B1 EP 14824048 A EP14824048 A EP 14824048A EP 3055506 B1 EP3055506 B1 EP 3055506B1
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Prior art keywords
curve
blade
blades
part according
intrados
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EP14824048.4A
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English (en)
French (fr)
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EP3055506A1 (de
Inventor
Damien Joseph CELLIER
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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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
    • F01D5/142—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
    • 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
    • F04D29/322—Blade mountings
    • 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
    • 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
    • F04D29/26—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
    • F04D29/324—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
    • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
    • F04D29/329—Details of the hub
    • 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
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • 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
    • F04D29/40—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
    • F04D29/544—Blade shapes
    • 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
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/80—Platforms for stationary or moving blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2250/00—Geometry
    • F05B2250/70—Shape
    • F05B2250/71—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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/50—Building or constructing in particular ways
    • 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
    • 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

Definitions

  • the present invention relates to a turbomachine compressor part comprising blades and a platform having a non-axisymmetric surface.
  • turbomachine rotors that is to say the assembly formed of a hub on which are fixed blades (or blades) extending radially, as visible on the figure 1a
  • computer modeling tools that is to say the assembly formed of a hub on which are fixed blades (or blades) extending radially, as visible on the figure 1a
  • pallet / platform assemblies in other words the assembly formed by a blade and the local surface of the hub or casing on which the blade is fixed, as represented for example by the figure 1b ) optimized by "contouring” (i.e. by definition of hollows and bumps in the wall) that offer excellent performance in supersonic flow.
  • the platform has in particular a circumferential depression extending axially between the leading edge and the trailing edge of the blade.
  • axisymmetric geometries remain perfectible, in particular at the compressor stages of the turbomachine: the search for an aeromechanical geometrical optimum on the rotors / stators leads today to obtaining parts having a locally non-axisymmetric wall (i.e. a section on a plane perpendicular to the axis of rotation is not circular) at the level of the vein, i.e. set of channels between the blades for fluid flow (in other words the inter-blade sections), given the particular conditions that prevail there.
  • the non-axisymmetric vein defines a generally annular surface of a three-dimensional space (a "slice" of the turbomachine). Examples of asymmetrical geometries are presented in US201101044818 A1 and in EP1762700 A2 .
  • This particular non-axisymmetric geometry of the workpiece surface provides unparalleled fluid flow control, resulting in increased efficiency.
  • the mechanical strength is not degraded so far.
  • the invention relates to a turbomachine comprising a part according to the first aspect.
  • the present invention relates to a turbomachine compressor part 1, having at least two blades 3 and a platform 2 to which the blades 3 extend.
  • the term platform is here interpreted in a broad sense and refers generally to any element of the engine.
  • the platform 2 can be monobloc (and thus support all the blades of the part 1), or formed of a plurality of elementary members each supporting a single blade 3 (a "foot” of the blade 3) so as to constitute a dawn of the type represented by the figure 1b .
  • the platform 2 may delimit a radially inner wall of the part 1 (the gas passes around) by defining a hub, and / or a radially outer wall of the part 1 (the gas passes inside, the blades 3 extend towards the center) then defining a casing of the part 1. It should be noted that the same part 1 can simultaneously comprise these two types of platform 2 (see figure 1c ).
  • part 1 can be of many types, in particular a rotor stage (DAM ("Aubade Monobloc disc”), or impeller, depending on the integral nature or not of the assembly) or a stator stage ( fixed or VSV (Variable Stator Vane) rectifier), according to the invention at a compressor, and in particular the High Pressure Compressor (HPC), see figure 1a already introduced.
  • DAM Aubade Monobloc disc
  • VSV Very Stator Vane
  • HPC High Pressure Compressor
  • the present part 1 is distinguished by a particular geometry (non-axisymmetric) of a surface S of a platform 2 of the part 1, of which we observe an example of advantageous modeling on the figure 2 .
  • the surface S extends between two blades 3 (one of which is not represented on the figure 2 to better observe the surface S, but we see a hole at its location), which limit it laterally.
  • the surface S is indeed a part of a larger surface defining a substantially toroidal shape around the part 1, which is here as explained a rotor stage.
  • the wall is made up of a plurality of surfaces. identical duplicates between each pair of blades 3.
  • the surface S ' also visible on the figure 2 is thus a duplication of the surface S.
  • This structure corresponds to an embodiment in which the platform 2 is composed of a plurality of elementary members each being a foot supporting a blade 3 with which it forms a blade. Each of these blade roots thus extends on both sides of the blade 3, hence the surface S comprises juxtaposed surfaces associated with two distinct blade roots.
  • the piece 1 is then a set of at least two vanes (blade / blade blade assembly) juxaposed.
  • the surface S is limited upstream by a first extremal plane, the "separation plane" PS and downstream by a second extremal plane, the "plane of connection” PR, which each define an axisymmetric, continuous and continuous derivative contour (the curve corresponding to the intersection between each of the planes PR and PS and the surface of the part 1 as a whole is closed and forms a loop).
  • the surface S has a substantially rectangular shape and extends continuously between the two end planes PS, PR, and the two blades 3 of a pair of consecutive blades. One of the blades of this pair of blades is the first blade 3I. It has indeed its intrados on the surface S. The other blade is the second blade 3E. It has indeed its extrados on the surface S.
  • Each "second blade” 3E is the "first blade” 3I of a neighboring surface such as the surface S 'in the figure 2 (Since each blade 3 has a lower surface and an upper surface).
  • Surface S is defined by building curves, also called "Construction Plans”. At least three curves of constructions PC-A, PC-C and PC-F are necessary to obtain the geometry of the present surface S.
  • each construction curve is a curve of class C 1 representing the value of a radius of said surface S as a function of a position between the intrados of the first blade 3I and the extrados of the second blade 3E according to a plan substantially parallel to the extremal planes PS, PR.
  • radius is understood the distance between a point of the surface and the axis of the part 1.
  • An axisymmetric surface thus has a constant radius.
  • the three curves extend on substantially parallel planes.
  • the first PC-C curve is a "central" curve.
  • the second curve PC-F is a "leakage” curve because disposed near the trailing edge BF of the blades 3 between which it extends.
  • the third PC-A curve is an "attack” curve because disposed near the leading edge BA of the blades 3 between which it extends.
  • each PC-A, PC-C, PC-F construction curve is also defined by a position along a rope of a blade 3 extending from the edge of BA attack at the trailing edge BF of the blade 3.
  • the third curve PC-A is associated with a position situated between 0% and 25% in relative length of blade rope 3
  • the first curve PC-C is associated with a position located between 30% and 60% relative length of blade rope 3
  • the second PC-F curve is associated with a position between 65% and 100% relative length of blade rope 3.
  • each curve PC-A, PC-C and PC-F has a specific geometry. We will see later the aerodynamic effects of these geometries.
  • the Figures 3a to 3d represent a plurality of examples of each of these curves PC-A, PC-C and PC-F, compared with an axisymmetric reference (constant radius).
  • the third curve PC-A has a minimum (overall) at the first blade 3I (therefore, it is increasing in the vicinity of the first blade 3I). In other words, the passage section is increased at the intrados.
  • the curve can be strictly increasing over the entire width of the surface S, or be increasing then decreasing and thus form a bump. In all cases, such a hump is such that the third PC-A curve is higher at the level of the second blade 3E than at the first blade 3I (because of the minimum at the first blade 3I), and he even desirable the third curve PC-A has a maximum (overall) at the second blade 3E (therefore, it is increasing in the vicinity of the second blade 3E).
  • the present geometry facilitates the bypassing of the leading edge BA of the second pale 3I by local convergence, since the vein section is maximum in part intrados.
  • a third strictly increasing PC-A curve is preferable because such a profile is free of bumps that could interfere with the migration of the fluid entering the vein.
  • this curve PC-A is not limited to a profile in particular on its extrados part (it is important only that it be at least increasing over an interval bounded by the first blade 3I and that its lowest point is at the level of this intrados blade 3I), although a generally increasing profile is preferred.
  • the figure 3b illustrates the first PC-C curve.
  • the latter is increasing in the vicinity of the second blade 3E, which means a reduction of the passage section at the extrados.
  • PC-A Like the third curve PC-A, it can be strictly increasing over the entire width of the surface S, or be decreasing then increasing and thus form a hollow.
  • This PC-C curve is not limited to a profile in particular on its intrados part (it is only important that it be at least increasing over an interval bounded by the second blade 3E).
  • the third PC-A curve is less than the first PC-C curve in the vicinity of the second blade 3E.
  • the amplitude of the third PC-A curve is less than that of the first PC-C curve. This further leads to a better bypass of the second blade 3E by overconvergence.
  • the Figures 3c and 3d illustrate two possible categories of geometries for the second PC-F curve.
  • the second curve must be decreasing in the vicinity of the second blade 3E, in order to increase the passage section at the extrados.
  • the passage section at the intrados is reduced, in other words that at the first blade 31 the first PC-C curve is smaller than the second PC-F curve.
  • the curve is strictly decreasing (or almost), or alternatively via a bump.
  • the second curve PC-F thus has a local maximum between the lower surface of the first blade 3I and the upper surface of the second blade 3E. This maximum is located approximately in the central part of the curve.
  • the second curve PC-F is decreasing, then increasing (up to the hump) and finally decreasing.
  • Such a central hump structure allows a ramp phenomenon (see below) limiting the migration of fluid from the lower surface to the upper surface (ie from the first blade 3I to the second blade 3E).
  • Some parameters of the extremal control points are fixed so as to respect the conditions on the growth / decay of each curve PC-A, PC-C, PC-F as defined before.
  • Intermediate control points may also be included, for example to form a hump on the second PC-F curve.
  • criteria can be chosen as criteria to be optimized when modeling each curve.
  • mechanical properties such as mechanical stress resistance, frequency responses, blade displacements 3, aerodynamic properties such as yield, pressure rise, flow capacity or the pumping margin, etc.
  • optimization consists in varying (generally randomly) these various parameters under stress, until they determine their optimal values for a predetermined criterion.
  • a “smoothed" curve is then obtained by interpolation from the determined crossing points.
  • the number of necessary calculations is then directly linked (linearly or even exponentially) to the number of input parameters of the problem.
  • connection curve (visible for example at the figure 1b ), which can be the subject of a specific modeling, notably also via the use of splines and user control points.
  • the surface is initially raised on a first part of the rope of the blade, and then lowered on a second part.
  • the bump on the second PC-F curve limits the fluid migration from the lower surface to the upper surface, resulting in even better control of the corner flow.
  • the new geometry also has a contribution in terms of mechanical situation, favoring the control of the blade / platform connection. The maximum stress is reduced.

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

Claims (13)

  1. Turbomaschinenkompressorteil (1), umfassend mindestens eine erste und eine zweite Schaufel (3, 3I, 3E) und eine Plattform (2), ab der sich die Schaufeln (3, 3I, 3E) erstrecken,
    wobei die Plattform (2) eine nicht-axialsymmetrische Oberfläche (S) aufweist, die von einer ersten und einer zweiten Abschlussebene (PS, PR) begrenzt und von mindestens drei Konstruktionskurven (PC-A, PC-C, PC-F) der Klasse C1 definiert ist, die jeweils den Wert eines Radius der Oberfläche (S) in Abhängigkeit von einer Position zwischen der Unterseite der ersten Schaufel (3I) und der Oberseite der zweiten Schaufel (3E) gemäß einer zu den Abschlussebenen (PS, PR) etwa parallelen Ebene darstellen, davon:
    - eine zunehmende erste Kurve (PC-C) in der Nähe der zweiten Schaufel (3E);
    - eine zweite und in der Nähe der zweiten Schaufel (3E) abnehmende Kurve (PC-F), die zwischen der ersten Kurve (PC-C) und einer Hinterkante (BF) der ersten und zweiten Schaufel (3, 3I, 3E) angeordnet ist;
    dadurch gekennzeichnet, dass die Oberfläche weiterhin definiert ist von:
    - einer dritten Kurve (PC-A), die zwischen der ersten Kurve (PC-C) und einer Vorderkante (BA) der ersten und zweiten Schaufel (3, 3I, 3E), angeordnet ist und im Bereich der ersten Schaufel (3I) ein Minimum aufweist.
  2. Teil nach Anspruch 1, wobei die dritte Kurve (PC-A) zwischen der Unterseite der ersten Schaufel (3I) und der Oberseite der zweiten Schaufel (3E) strikt zunehmend ist.
  3. Teil nach einem der Ansprüche 1 und 2, wobei die dritte Kurve (PC-A) in der Nähe der zweiten Schaufel (3E) kleiner als die erste Kurve (PC-C) ist.
  4. Teil nach einem der vorangehenden Ansprüche, wobei die erste Kurve (PC-C) zwischen der Unterseite der ersten Schaufel (3I) und der Oberseite der zweiten Schaufel (3E) strikt zunehmend ist.
  5. Teil nach einem der vorangehenden Ansprüche, wobei die zweite Kurve (PC-F) zwischen der Unterseite der ersten Schaufel (3I) und der Oberseite der zweiten Schaufel (3E) ein lokales Maximum aufweist.
  6. Teil nach einem der vorangehenden Ansprüche, wobei jede Konstruktionskurve (PC-A, PC-C, PC-F) ebenfalls durch eine Position entlang einer Sehne einer Schaufel (3I, 3E) definiert ist, die sich von der Vorderkante (BA) zur Hinterkante der Schaufel (3, 3I, 3E) erstreckt.
  7. Teil nach Anspruch 6, wobei die erste Kurve (PC-C) einer Position zugeordnet ist, die sich zwischen 0% und 60% relativer Sehnenlänge einer Schaufel (3, 3I, 3E) befindet, und die zweite Kurve (PC-F) einer Position zugeordnet ist, die sich zwischen 65% und 100% relativer Sehnenlänge einer Schaufel (3, 3I, 3E) befindet.
  8. Teil nach Anspruch 7, wobei die dritte Kurve (PC-A) einer Position zugeordnet ist, die sich zwischen 0% und 25% in relativer Sehnenlänge einer Schaufel (3, 3I, 3E) befindet, und die erste Kurve (PC-C) einer Position zugeordnet ist, die sich zwischen 30% und 60% relativer Sehnenlänge einer Schaufel (3, 3I, 3E) befindet.
  9. Teil nach einem der vorangehenden Ansprüche, wobei die Plattform (2) eine ringförmige Form aufweist, entlang der eine Vielzahl von Schaufeln (3I, 3E) gleichmäßig angeordnet sind.
  10. Teil nach Anspruch 9, wobei die Plattform (2) dieselbe nicht-axialsymmetrische Oberfläche (S) zwischen jedem Paar aufeinanderfolgender Schaufeln (3, 3I, 3E) aufweist.
  11. Teil nach Anspruch 10, das ein Schaufelrad oder eine Kompressorleitschaufel ist.
  12. Teil nach einem der vorangehenden Ansprüche, für das die Konstruktionskurve (PC-A, PC-C, PC-F) anhand von Daten, verarbeitet von Verarbeitungsmittel, modelliert wurde in den Schritten:
    (a) Parametrieren der Konstruktionskurve (PC-A, PC-C, PC-F) als Kurve der Klasse C1, die den Wert des Radius der Oberfläche (S) in Abhängigkeit von einer Position zwischen der Unterseite der ersten Schaufel (3I) und der Oberseite der zweiten Schaufel (3E) darstellt, wobei die Kurve definiert ist durch:
    - zwei abschließende Kontrollpunkte jeweils auf jeder der zwei Schaufeln (3, 3I, 3E), zwischen denen sich die Oberfläche (S) erstreckt;
    - mindestens ein Spline;
    wobei die Parametrierung gemäß einem oder mehreren Parametern durchgeführt wird, die mindestens einen der abschließenden Kontrollpunkte definieren;
    (b) Bestimmen optimierter Werte der Parameter der Kurve.
  13. Turbomaschine, umfassend ein Teil (1) nach einem der vorangehenden Ansprüche.
EP14824048.4A 2013-10-11 2014-10-10 Turbomaschinenteil mit nicht-axialsymmetrischer oberfläche Active EP3055506B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1359895A FR3011888B1 (fr) 2013-10-11 2013-10-11 Piece de turbomachine a surface non-axisymetrique
PCT/FR2014/052586 WO2015052455A1 (fr) 2013-10-11 2014-10-10 Pièce de turbomachine à surface non-axisymétrique

Publications (2)

Publication Number Publication Date
EP3055506A1 EP3055506A1 (de) 2016-08-17
EP3055506B1 true EP3055506B1 (de) 2019-04-17

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CN (1) CN105637181B (de)
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FR3015552B1 (fr) * 2013-12-19 2018-12-07 Safran Aircraft Engines Piece de turbomachine a surface non-axisymetrique
BE1025667B1 (fr) 2017-10-26 2019-05-27 Safran Aero Boosters S.A. Virole asymetrique pour compresseur de turbomachine
BE1025666B1 (fr) * 2017-10-26 2019-05-27 Safran Aero Boosters S.A. Profil non-axisymetrique de carter pour compresseur turbomachine
BE1026276B1 (fr) 2018-05-14 2019-12-17 Safran Aero Boosters Sa Bosse inter-aubes de compresseur de turbomachine axiale
BE1026325B1 (fr) 2018-05-31 2020-01-13 Safran Aero Boosters Sa Virole a profilage evolutif pour compresseur de turbomachine
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Publication number Publication date
BR112016007568B1 (pt) 2021-12-28
FR3011888B1 (fr) 2018-04-20
CA2926003A1 (fr) 2015-04-16
RU2675980C2 (ru) 2018-12-25
US20160245299A1 (en) 2016-08-25
RU2016118151A3 (de) 2018-07-19
CN105637181B (zh) 2017-07-07
FR3011888A1 (fr) 2015-04-17
WO2015052455A1 (fr) 2015-04-16
CN105637181A (zh) 2016-06-01
US10352330B2 (en) 2019-07-16
RU2016118151A (ru) 2017-11-16
BR112016007568A2 (pt) 2017-08-01
EP3055506A1 (de) 2016-08-17
CA2926003C (fr) 2022-03-22

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