EP3431708B1 - Dispositif d'écoulement environnant, turbomachine et application associée - Google Patents

Dispositif d'écoulement environnant, turbomachine et application associée Download PDF

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Publication number
EP3431708B1
EP3431708B1 EP18178413.3A EP18178413A EP3431708B1 EP 3431708 B1 EP3431708 B1 EP 3431708B1 EP 18178413 A EP18178413 A EP 18178413A EP 3431708 B1 EP3431708 B1 EP 3431708B1
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EP
European Patent Office
Prior art keywords
flow bypass
flow
bypass structure
arrangement
structures
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
EP18178413.3A
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German (de)
English (en)
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EP3431708A1 (fr
Inventor
Martin Hoeger
Fadi Maatouk
Günter RAMM
Yavuz Gündogdu
Irene Raab
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MTU Aero Engines AG
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MTU Aero Engines AG
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Publication of EP3431708A1 publication Critical patent/EP3431708A1/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
    • 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
    • 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
    • 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
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge 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
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge 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
    • F05D2240/128—Nozzles
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/34—Arrangement of components translated

Definitions

  • the present invention relates to a flow arrangement with flow structures for arrangement in the hot gas duct of a turbo machine.
  • the turbo engine can be, for example, a jet engine, e.g. B. a turbofan engine.
  • the flow machine is functionally divided into a compressor, combustion chamber and turbine.
  • the air that is sucked in is compressed by the compressor and burned in the downstream combustion chamber with the added kerosene.
  • the resulting hot gas a mixture of combustion gas and air, flows through the downstream turbine and is expanded in the process.
  • the volume through which the hot gas flows i.e. the path from the combustion chamber via the turbine to the nozzle, is referred to as the "hot gas channel".
  • the flow-around arrangement in question is intended to be arranged in the hot gas duct and has several flow-around structures. At least some of these are designed as deflecting vanes, while others are preferably support struts or corresponding cladding. Like the above reference to a jet engine, this is intended to illustrate the present subject matter, but not initially restrict its generality.
  • the turbo machine can also be a stationary gas or steam turbine, for example.
  • the present invention is based on the technical problem of specifying a particularly advantageous flow arrangement for arrangement in the hot gas duct of a turbo machine.
  • this object is achieved with the flow arrangement according to claim 1.
  • This has a first and a second flow structure, wherein the second flow structure is provided as a deflection vane and has a smaller profile thickness than the first flow structure, which is arranged on the suction side of the second flow structure.
  • the flow structures are arranged with a partial axial overlap, at the same time the rear edge of the second flow structure is offset axially downstream relative to that of the first flow structure.
  • different flow structures which are provided axially one after the other in separate sections in a conventional design, are pushed into one another a little (axial overlap), but not completely.
  • the rear edge of the second flow structure (hereinafter also “thin deflecting vane”) is offset to the rear, suction can be generated at the rear edge of the first flow structure (hereinafter also “thick vane”).
  • the thin deflecting vane causes relief and smooth outflow at the rear edge of the thick vane (Kutta condition). With a view to the uniformity of the flow to the downstream rotor, this can be of advantage and also help to improve the overall efficiency of the turbine, for example by approx. 0.25% to 0.5%.
  • Each of the flow structures has a leading edge and a trailing edge, with two opposing side surfaces of the respective flow structure extending therebetween.
  • the profile thickness is taken between the side surfaces.
  • the camber line extends in the middle between the side surfaces between the front and rear edges of the respective flow structure, and the profile thickness then results as the largest circle diameter on the camber line (the circle touches the side surfaces, the center is on the camber line).
  • the thin deflecting vane can, for example, have a profile thickness that is at least 50%, 60%, 70% or 80% smaller than the first flow structure, with possible (independent) upper limits at, for example, a maximum of 99%, 97% or 95% ( increasingly preferred in the order in which they are named).
  • the design of the respective structure in its respective radial center is used as a basis.
  • the shape at half the height (taken radially) of the corresponding flow structure or the deflecting vane or the vane blade is therefore considered in each case.
  • the influence on the flow can be greatest in the radial center of the gas duct.
  • the respective structures are preferably designed accordingly over their entire height relative to one another (at least in the case of a comparison at the same percentage in each case).
  • axial refers to the longitudinal axis of the turbomachine, which, for example, coincides with an axis of rotation of the rotors.
  • “Radial” relates to the radial directions perpendicular to it, pointing away therefrom, and “revolving” or “revolving” or the “revolving direction” relate to the rotation about the longitudinal axis.
  • the first and the second flow structure are, for example, due to the axial overlap, also arranged one after the other in the direction of rotation.
  • axial overlap means, for example, that a projection of the first flow structure radially onto the longitudinal axis has an overlap with a projection of the second flow structure radially onto the longitudinal axis.
  • the flow-around arrangement can of course have a plurality of first and second flow-around structures, for example at least 4, 5 or 6 each, with possible (independent) upper limits of, for example, at most 30, 20 or 15, respectively and the second flow structures are then preferably structurally identical and arranged rotationally symmetrically.
  • first and second flow-around structures for example at least 4, 5 or 6 each, with possible (independent) upper limits of, for example, at most 30, 20 or 15, respectively and the second flow structures are then preferably structurally identical and arranged rotationally symmetrically.
  • third and possibly fourth or also further flow structures which are then also designed as thin deflecting blades.
  • Circumferentially between two thick blades there can be at least two and preferably no more than nine, eight, seven, six, five, four or three thin deflecting blades.
  • the first flow structure is provided as a load-bearing support strut or as a cladding, in particular as a cladding of a load-bearing support strut.
  • the support strut is a load-bearing component of the turbomachine; it preferably carries the bearing of the turbine shaft, in particular of the high-pressure turbine shaft (together with further circumferentially arranged support struts).
  • the bearing is preferably arranged in the intermediate turbine housing, in the so-called mid turbine frame.
  • the support struts can each extend radially outward away from the bearing and thus keep the bearing centered in the housing, in a spoke-like manner.
  • the first flow structure is preferably a covering in which, for example, a supply line can also be routed; it is preferably a covering of a support strut, that is to say, for aerodynamic reasons, it is attached to the actually load-bearing component. In this case, too, supply lines etc. can then also be routed.
  • a panel is also known as fairing.
  • the load-bearing function or the enclosing of the support strut require a certain structure size, i.e. large profile thickness. This is aerodynamically disadvantageous, but this is at least partially compensated for by the combination with the thin deflecting vane.
  • the first flow structure can generally also be provided in a non-deflecting manner; it is preferably weakly deflecting by less than 5 °, but has no effect on the flow (no impulse is transmitted to the flow due to the change in radius and the rate of swirl).
  • the first bypass structure (thick vane) faces the thin deflecting vane with its underside surface. More deflection is necessary on the underside of the thick blade because its underside surface is due to the high thickness in the Runs essentially axially into the rear edge, for example tilted by no more than 10 ° or 5 ° to the axial direction.
  • the thin deflection vane generates acceleration (nozzle effect) at the rear edge of the thick vane. The trailing edge is then "sucked away".
  • the thin deflecting vane has its maximum curvature where it has the axial overlap with the first flow structure.
  • This high-curvature design is akin to a wing with the Fowler flap extended, which further increases the suction created at the trailing edge of the thick vane.
  • the rear edge of the thin deflecting vane is offset by at least 0.5 times, further and particularly preferably at least 0.7 or 0.9 times the axial length of the blades of a rotor arranged directly downstream to the rear edge of the first flow structure ( axially downstream).
  • Upper limits which in general can also be of interest independently of the lower limits, are at most 4 times, further and particularly preferably at most 2.6 or 2.2 times.
  • the "axial length" results from the axial portion of the chord length of the rotor blades (if it is equipped with different blades, an average value calculated over these is considered).
  • the leading edge of the thin turning vane is offset axially downstream from that of the thick vane.
  • An advantageous upper limit is (regardless of this) preferably at most 0.9 times.
  • the thin deflecting vane has a chord length which is at least 1 times, preferably at least 1.5 times, a chord length of the blades of the rotor arranged directly downstream. If this is equipped with different blades, an average value is again considered.
  • Advantageous upper limits of the chord length of the thin deflection vane are, in the order in which they are named, increasingly preferably at most 8, 7, 6, 5, 4 or 3 times the chord length of the subsequent rotor. A chord length of approximately 2 to 3 times is particularly preferred.
  • the flow-around arrangement has a third flow-around structure, which is provided as a thin deflecting vane analogously to the second flow-around structure, but is not structurally identical to the second flow-around structure.
  • the third flow-around structure is arranged on the top side of the thick vane (the thick vane is on the suction side of the third flow-around structure). At least two different thin deflecting blades are then provided around between two thick blades.
  • the rear edge of the third flow-around structure is preferably offset axially downstream relative to that of the thick blade; it is preferably axially offset-free (not offset) from that of the second flow-around structure, which preferably also applies to a fourth or generally further flow-around structures.
  • the third flow around structure has a smaller chord length than the second flow structure.
  • more deflection may be required on the underside of the first flow structure, which is achieved with the greater chord length of the second flow structure.
  • more than two different thin deflecting blades are provided circumferentially between two first flow structures, these preferably have a decreasing chord length overall from the bottom of one thick blade to the top of the other thick blade. With the variable chord length, the free flow cross-section can be adjusted in such a way that a uniform flow to the subsequent rotor is achieved.
  • the third flow structure has a smaller curvature than the second. More deflection is thus achieved with a more strongly curved second flow structure on the underside of the thick blade, see above. If more than two different thin deflection blades are provided circumferentially between two first flow structures, they preferably have a decreasing curvature overall from the bottom of one thick blade to the top of the other thick blade.
  • a further thin deflecting vane is provided (fourth flow structure), the second, third and fourth flow structure not being identical to one another.
  • the fourth flow-around structure is arranged on the suction side of the third flow-around structure.
  • Deflection blades are arranged circumferentially between two thick blades, a fourth flow structure is also arranged on the pressure side of the second flow structure.
  • the fourth flow structure has a greater chord length than the third flow structure or it is more curved, preferably both.
  • the chord length and / or curvature preferably increases from the third flow structure via the fourth to the second flow structure.
  • At least four flow structures are arranged, each of which is designed as a deflecting blade.
  • Upper limits that are independent of this lower limit can be at most twelve, eleven, ten or nine deflection vanes, increasingly preferably in the order in which they are named. Exactly four deflection blades can be particularly preferred.
  • the second, third, fourth and a fifth flow structure can then preferably be arranged between the first flow structures that are next to one another, cf. also the description above with further details.
  • the rear edges of the latter can also be offset from one another, that is to say staggered.
  • an equidistant arrangement of the trailing edges of the deflecting blades is generally also possible, but a non-equidistant arrangement can be preferred.
  • At least the deflecting blades arranged between the two next adjacent first flow structures in the direction of rotation are designed as a multiple segment.
  • the first flow structure can also be provided as part of the multiple segment.
  • a subdivision can also be advantageous in that only the deflecting blades are combined in multiple segments or also in a ring, with the first flow structures then being combined with them.
  • the first flow structure or structures are then cast for themselves; in order to then realize the axial overlap, a recess can then be made in each of the rear edges of the first flow structures, e.g. B. be milled into which the segment or the ring with the guide vanes is pushed in.
  • the flow structures of the multiple segment or ring are integral with one another, that is, cannot be separated from one another in a non-destructive manner; they can preferably be monolithic, in particular formed from one cast.
  • the invention also relates to a turbomachine with a flow-around arrangement disclosed in the present case; this can in particular be arranged in the intermediate turbine housing.
  • the invention also relates to the use of a flow-around arrangement disclosed in the present case in a turbo-engine, in particular an aircraft engine.
  • FIG 1a shows a flow machine 1 in section, specifically a jet engine.
  • Figure 1b shows a schematic detailed view of this, the following comments relate on both figures.
  • the turbomachine 1 is divided into compressor 1a, combustion chamber 1b and turbine 1c. Both the compressor 1a and the turbine 1c are each made up of several stages; each stage is usually composed of a guide and a rotor blade ring. During operation, the rotor blade rings rotate about the longitudinal axis 2 of the turbomachine 1.
  • the turbine shaft 3 is guided in a bearing 4, which is held in the rest of the turbomachine 1 by support struts 5 (partly dashed).
  • each of the support struts 5 is jacketed for aerodynamic and thermal reasons, namely from a first Umströmungs Quilt 6, illustrating a cover and is also known as fairing.
  • This section is a so-called turbine center frame. In the turbo machine according to the invention, this is designed integrally with the following guide vane ring.
  • Figure 2 shows part of the flow-around arrangement 20 according to the invention, which is arranged in the intermediate turbine housing in the hot gas duct. A section is shown, the cut surface lies radially in the center of the hot gas duct and parallel to the longitudinal axis 2.
  • second flow structures 21 and third flow structures 22 can be seen, each as a deflection vane with a suction side (in the figure above ) and a pressure side (in the figure below) are formed.
  • the profile thickness of these thin deflecting vanes is only around 30% of the profile thickness of the first flow structures 6 (in the schematic representation according to FIG Figure 2 the thin turning vanes are shown in simplified form as lines without a profile thickness).
  • the flow structures 6, 21, 22 each have a front edge 6a, 21a, 22a and, downstream of this, a respective rear edge 6b, 21b, 22b.
  • the thin deflecting vanes are provided axially with an overlap with respect to the first flow structures 6, but are also provided offset to a certain extent.
  • the rear edges 21b, 22b of the second and third flow structures 21, 22 are offset axially downstream relative to the rear edges 6b of the first flow structures 6.
  • the second flow structure 21 has its strongest curvature in the area of the axial overlap with the first flow structure 6. As a result, a strong suction is generated and the flow accelerates away from the rear edge 6b of the aerodynamically rather unfavorable first flow structure 6. The wake becomes finer and more even, cf. also the representation in the introduction to the description.
  • the second flow around structure 21 is therefore more curved than the third flow around structure 22 and it has a greater chord length.
  • the first flow structure 6 is arranged on the pressure side of the third flow structure 22, this presses the flow at the rear edge 6b a little way down and thus relieves the rear edge 6b.
  • FIG 3 shows an enlarged representation of the configuration from Figure 2 with the suction field 23 on the top of the thin deflecting vane 21.
  • Both deflecting vanes 21, 22 form with the flow structure 6 in their inlet area narrowing flow channels 24, 25, which lead to a further relief of the flow at the rear edge 6b. Downstream of the rear edge 6b, a further narrowing flow channel follows up to the narrow spacing 26, which, together with the blade curvature, creates the suction field.
  • flow structures 6 with a high thickness and thickness reserves x d / L> 50% are possible, which can accommodate more and larger supply lines and support elements. A reduction in the number of blades, friction loss and weight becomes possible.
  • the flow-around arrangement 20 is constructed overall (over the entire circumference) of 9 first, second and third flow-around structures 6, 21, 22, that is to say has 18 thin deflecting blades.
  • a fourth flow structure also designed as a thin deflection blade, could also be provided, so that three different thin deflection blades would be arranged between two first flow structures 6 (in this case a total of 27 thin deflection blades would be provided), cf. also the introduction to the description. Regardless of this, it is preferred to combine the flow structures 6, 21, 22 in groups in multiple segments.
  • the axial offset can be advantageous in terms of production technology or, conversely, it would sometimes be considerably more complex to achieve the same flow guidance at the rear edge 6b of the first flow structure 6 by means of a first flow structure 6 drawn backwards for a long time.
  • the axial offset between the rear edges 21b, 22b of the second and third flow structures 21, 22 to the rear edges 6b of the first flow structures 6 corresponds to about 1.5 axial lengths of a subsequent rotor 30, specifically its blades 31.
  • the refinement and equalization of the flow described is also advantageous for the operation of the rotor 30.

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

Claims (14)

  1. Dispositif d'écoulement environnant (20) destiné à être disposé dans le conduit de gaz chaud d'une turbomachine (1), comportant une première structure d'écoulement environnant (6) et une deuxième structure d'écoulement environnant (21), lesquelles structures d'écoulement environnant (6, 21) comportent chacune un bord d'attaque (6a, 21a) par rapport à l'écoulement autour dans le conduit de gaz chaud et, en aval de ceux-ci, comportent un bord de fuite (6b, 21b), dans lequel la deuxième structure d'écoulement environnant (21) est réalisée sous la forme d'une aube de déviation ayant un côté aspiration et un côté refoulement et ayant une épaisseur de profil inférieure à celle de la première structure d'écoulement environnant (6) qui est disposée sur le côté aspiration de la deuxième structure d'écoulement environnant (21), dans lequel la deuxième structure d'écoulement (21) présente un chevauchement axial partiel avec la première structure d'écoulement environnant (6) par rapport à un axe longitudinal (2) de la turbomachine (1), mais en même temps le bord de fuite (21b) de la deuxième structure d'écoulement environnant (21) est décalé axialement en aval du bord de fuite (6b) de la première structure d'écoulement environnant (6), caractérisé en ce que le bord de fuite (21b) de la deuxième structure d'écoulement environnant (21) est décalé par rapport au bord de fuite (6b) de la première structure d'écoulement environnant (6) d'au moins 0,5 fois et d'au plus 4,0 fois une longueur axiale de l'aubage (31) d'un rotor qui est destiné à être disposé axialement en aval directement à la suite du dispositif d'écoulement environnant (20).
  2. Dispositif d'écoulement environnant (20) selon la revendication 1, dans lequel la première structure d'écoulement environnant (6) est réalisée sous la forme d'une entretoise de support ou d'un revêtement d'une telle entretoise.
  3. Dispositif d'écoulement environnant (20) selon la revendication 1 ou 2, dans lequel la deuxième structure d'écoulement environnant (21) présente une courbure maximale à l'emplacement où elle présente le chevauchement axial avec la première structure d'écoulement environnant (6).
  4. Dispositif d'écoulement environnant (20) selon l'une des revendications précédentes, dans lequel le bord d'attaque (21a) de la deuxième structure d'écoulement environnant (21) est décalée axialement en aval du bord d'attaque (6a) de la première structure d'écoulement environnant (6) d'au moins 0,4 fois et d'au plus 0,9 fois une longueur axiale de la première structure d'écoulement environnant (6).
  5. Dispositif d'écoulement environnant (20) selon l'une des revendications précédentes, dans lequel la deuxième structure d'écoulement environnant (21) a une longueur de corde qui est au moins 1 fois et au plus 8 fois une longueur de corde de l'aubage (31) d'un rotor destiné à être disposé axialement en aval directement à la suite du dispositif d'écoulement environnant (20).
  6. Dispositif d'écoulement environnant (20) selon l'une des revendications précédentes, comprenant une troisième structure d'écoulement environnant (22) qui est réalisée sous la forme d'une aube de déviation ayant un côté aspiration et un côté refoulement et qui a une épaisseur de profil inférieure à celle de la première structure d'écoulement environnant (6), mais les deuxième et troisième structures d'écoulement environnant (21, 22) sont de formes différentes, dans lequel la première structure d'écoulement environnant (6) est disposée sur le côté refoulement de la troisième structure d'écoulement environnant (22).
  7. Dispositif d'écoulement environnant (20) selon la revendication 6, dans lequel le troisième dispositif d'écoulement environnant (22) a une longueur de corde inférieure à celle de la deuxième structure d'écoulement environnant (21).
  8. Dispositif d'écoulement environnant (20) selon la revendication 6 ou 7, dans lequel la troisième structure d'écoulement environnant (22) a une courbure inférieure à celle de la deuxième structure d'écoulement environnant (21).
  9. Dispositif d'écoulement environnant (20) selon l'une des revendications 6 à 8, comprenant une quatrième structure d'écoulement environnant qui est réalisée sous la forme d'une aube de déviation ayant un côté aspiration et un côté refoulement et qui a une épaisseur de profil inférieure à celle de la première structure d'écoulement environnant (6), mais les deuxième, troisième et quatrième structures d'écoulement environnant (21, 22) sont de formes différentes, dans lequel la quatrième structure d'écoulement environnant est disposée sur le côté aspiration de la troisième structure d'écoulement environnant (22).
  10. Dispositif d'écoulement environnant (20) selon la revendication 9, dans lequel la quatrième structure d'écoulement environnant a une longueur de corde et/ou une courbure supérieures à celles de la troisième structure d'écoulement environnant (22).
  11. Dispositif d'écoulement environnant (20) selon l'une des revendications précédentes, dans lequel au moins deux et pas plus de douze structures d'écoulement environnant (21, 22), réalisées chacune sous la forme d'une aube de déviation ayant un côté aspiration et un côté refoulement, sont disposées de manière circonférentielle entre deux premières structures d'écoulement environnant (6) qui sont directement adjacentes dans la direction circonférentielle.
  12. Dispositif d'écoulement environnant (20) selon la revendication 11, dans lequel au moins les structures d'écoulement environnant (21, 22), disposées entre les deux premières structures d'écoulement environnant (6) directement adjacentes dans la direction circonférentielle, sont réalisées sous forme de segments multiples.
  13. Turbomachine (1) comportant un dispositif d'écoulement environnant (20) selon l'une des revendications précédentes, en particulier disposé dans un carter intermédiaire de turbine.
  14. Utilisation d'un dispositif d'écoulement environnant (20) selon l'une des revendications 1 à 12 dans une turbomachine (1), en particulier dans un moteur d'avion.
EP18178413.3A 2017-07-19 2018-06-19 Dispositif d'écoulement environnant, turbomachine et application associée Active EP3431708B1 (fr)

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DE102017212311.7A DE102017212311A1 (de) 2017-07-19 2017-07-19 Umströmungsanordung zum Anordnen im Heißgaskanal einer Strömungsmaschine

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EP3431708A1 EP3431708A1 (fr) 2019-01-23
EP3431708B1 true EP3431708B1 (fr) 2020-10-14

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EP (1) EP3431708B1 (fr)
DE (1) DE102017212311A1 (fr)
ES (1) ES2832464T3 (fr)

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FR3115560B1 (fr) * 2020-10-27 2024-02-09 Office National Detudes Rech Aerospatiales Element de carenage pour entourer un obstacle dans un ecoulement de fluide

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Also Published As

Publication number Publication date
DE102017212311A1 (de) 2019-01-24
EP3431708A1 (fr) 2019-01-23
US20190024521A1 (en) 2019-01-24
US11371370B2 (en) 2022-06-28
ES2832464T3 (es) 2021-06-10

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