EP3492701B1 - Canal d'écoulement de turbomachine - Google Patents

Canal d'écoulement de turbomachine Download PDF

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Publication number
EP3492701B1
EP3492701B1 EP18205690.3A EP18205690A EP3492701B1 EP 3492701 B1 EP3492701 B1 EP 3492701B1 EP 18205690 A EP18205690 A EP 18205690A EP 3492701 B1 EP3492701 B1 EP 3492701B1
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EP
European Patent Office
Prior art keywords
flow
flow passage
support rib
guide vanes
passage
Prior art date
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Active
Application number
EP18205690.3A
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German (de)
English (en)
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EP3492701A1 (fr
Inventor
Günter RAMM
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
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MTU Aero Engines AG
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Publication of EP3492701A1 publication Critical patent/EP3492701A1/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
    • F01D5/142—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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/023—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines the working-fluid being divided into several separate flows ; several separate fluid flows being united in a single flow; the machine or engine having provision for two or more different possible fluid flow paths
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • 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
    • F01D5/148—Blades with variable camber, e.g. by ejection of fluid
    • 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
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • 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
    • 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
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • 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
    • F05D2260/00—Function
    • F05D2260/97—Reducing windage losses

Definitions

  • the present invention relates to a method for producing a flow channel for a turbomachine as well as a flow channel and a turbomachine, in particular a gas turbine, with the flow channel.
  • GB 2 226 600 A discloses a turbine assembly having an annular shroud and support rib assembly that provides mechanical strength to the turbine assembly and supports the rear rotor bearing.
  • the turbine assembly also includes an exhaust stator downstream of the shroud and support rib assembly.
  • An object of the present invention is to improve a turbomachine.
  • Claim 12 protects a turbomachine with at least one flow channel described here.
  • Advantageous embodiments of the invention are the subject of the subclaims.
  • an axial direction is parallel to a rotation or
  • a first element is downstream of a second element if it is (axially) closer to an outlet of the flow channel or the turbomachine than the second element. Accordingly, in one embodiment, a first element is upstream of a second element if it is (axially) closer to an inlet of the flow channel or the turbomachine than the second element.
  • one or more of the support ribs have flow resistance-reducing, in particular symmetrical or asymmetrical, outer profiles; in a further development, the support rib(s) is/are each covered with a flow resistance-reducing hollow profile; in another development, the flow resistance-reducing outer profile is integral with a Core of the support rib is formed.
  • a pressure loss and/or vibration excitation can be advantageously reduced.
  • the guide vanes of the guide grille each have a pressure side and a different suction side for flow deflection.
  • a design of at least one (of) the flow passage(s), which is downstream of a support rib, in particular adjacent is adapted to this support rib in such a way that a pressure loss, in particular at least between an upstream front edge of the support rib and a downstream rear edge of one of the guide blades delimiting this flow passage, and / or a vibration excitation, in particular of the support rib, the guide blades delimiting the flow passage and / or a running grid axially following the guide grille, reduced, in particular minimized, for at least the majority of all supporting ribs of the supporting rib arrangement successive in the circumferential direction, a design of a flow passage of the guide grid downstream of this supporting rib, in particular adjacent, is adapted to this supporting rib in order to avoid a pressure loss and/or vibration excitation to reduce, in particular to minimize.
  • the support rib(s) and the downstream flow passage(s) or upstream leading edges of the guide vanes delimiting them are spaced apart axially or by an axial gap.
  • the support rib(s) there is a distance between this support rib, in particular its downstream rear edge, and the flow passage downstream of it, the design of which is or is adapted to this support rib in order to reduce a pressure loss and/or vibration excitation , in particular axially and/or in the circumferential direction, smaller than all other flow passages of the guide grille.
  • this support rib in particular its downstream rear edge, and the flow passage downstream of it, the design of which is or is adapted to this support rib in order to reduce a pressure loss and/or vibration excitation , in particular axially and/or in the circumferential direction, smaller than all other flow passages of the guide grille.
  • the design of which is adapted to this supporting rib in order to reduce a pressure loss and/or vibration excitation is, (in each case) the flow passage of the guide grille closest or adjacent to this support rib downstream behind the support rib arrangement.
  • the efficiency and/or the service life of the turbomachine can be improved.
  • Adapting the design of several of the flow passages downstream of a support rib to these support ribs in order to reduce a pressure loss and/or vibration excitation includes positioning this flow passage in the circumferential direction relative to this support rib in such a way that a wake of the support rib intersects an inlet cross section of the flow passage in a central region of the inlet cross section.
  • one or the flow passage that is downstream of this support rib, in particular adjacent is positioned relative to this support rib in the circumferential direction in such a way that a wake of the support rib Entry cross section of the flow passage intersects in a central area.
  • a flow passage positioned in this way relative to a support rib is also referred to in the present case as (the) flow passage fed by this support rib for more compact representation or clear identification.
  • the wake of a support rib is limited in a conventional manner by the two streamlines that extend from sides of the support rib that are opposite one another in the circumferential direction.
  • the skeleton line or profile center line of a support rib is, in a conventional manner, the connecting line of the circle centers inscribed in a profile or a cross section of the support rib.
  • the end region of the skeleton line extends from a downstream rear edge of the support rib over a maximum of 25%, in particular a maximum of 10%, in one embodiment a maximum of 5%, of the length of the skeleton line.
  • the inlet cross section of a flow passage extends, in particular in the circumferential direction, between the upstream front edges of the guide vanes delimiting the flow passage, its central area in one embodiment extends over at most 80%, in particular at most 60%, and / or at least 10%, in particular at least 25 %, of the inlet cross section or its width in the circumferential direction and / or is equidistantly spaced (in the circumferential direction) from the two leading edges of the guide vanes delimiting the flow passage.
  • the flow is advantageously applied to the guide grid.
  • a pressure loss and/or vibration excitation can be particularly advantageously reduced.
  • the adjustment of the design of the flow passage downstream of this supporting rib to the supporting rib upstream thereof in order to reduce a pressure loss and/or vibration excitation in each case involves changing a shape, in particular also size, of this flow passage compared to one or more of the other flow passages of the guide grid, in particular an additional change in a shape, in particular also size, of several flow passage(s) loaded with support ribs, which are relative to (one) of the support rib(s). ) is or are positioned in the circumferential direction such that a wake of the support rib intersects an inlet cross section of the flow passage in a central area.
  • a shape, in particular also size, of several flow passages loaded with support ribs which is or are positioned relative to one of the support ribs in the circumferential direction in such a way that a wake of the support rib has an inlet cross section of the flow passage intersects in a central region, different (designed) from at least one other of the flow passages, which is not a flow passage adjacent to a support rib, in particular is not fed by a support rib.
  • a pressure loss can occur in one embodiment and/or vibration excitation can be particularly advantageously reduced.
  • this changing the shape, in particular also the size, of at least one (of) the flow passage(s), in particular loaded by a support rib, relative to at least one other (of the) flow passage(s), includes changing, in particular enlarging, one, in particular the middle one , maximum and / or minimum, channel width in the circumferential direction, in one embodiment by at least 1% and / or at most 50%, in particular at most 15%.
  • the support rib(s) for at least one (of) the support rib(s), in particular at least for the majority of all support ribs of the support rib arrangement successive in the circumferential direction, there is or is one, in particular average, maximum and/or minimum, channel width in the circumferential direction of the flow passage, the design of which is or is adapted to this support rib, in particular the flow passage adjacent to the support rib downstream, from at least one other of the flow passage (designed), in one embodiment by at least 1% and / or at most 50%, in particular at most 15%, in particular i.e.
  • a wake of the support rib is advantageously guided into the flow passage.
  • a pressure loss and/or vibration excitation can be particularly advantageously reduced.
  • changing the size and/or shape of at least one (of) the flow passage(s), in particular loaded by a support rib, relative to at least one other (of the) flow passage(s) includes changing a flow passage-side pressure side of one of the two Guide vanes and/or a suction side on the flow passage side of one of the two guide vanes that delimit one flow passage, and/or the profile of one of these two guide vanes or these two guide vanes relative to the other Flow passage or the guide vane or vanes delimiting it, in particular compared to the majority of the other flow passages.
  • Changing the shape of a support rib-loaded flow passage(s) relative to at least one other flow passage(s) includes changing a stagger angle of one or both vanes that delimit the flow passage relative to one or both vanes that delimit the other flow passage.
  • the stagger angle is the angle that the profile chord of the guide vane includes with the axial or circumferential direction.
  • a wake of the support rib is advantageously guided in the flow passage.
  • a pressure loss and/or vibration excitation can be particularly advantageously reduced.
  • the guide grille of the flow channel is a guide grille of a turbine of a gas turbine
  • the support rib arrangement is arranged in a turbine intermediate housing ("midturbine frame" MTF) for connecting two turbines of a gas turbine, in particular a turbine intermediate housing, which has a high and a middle - or low-pressure turbine or a medium and a low-pressure turbine connects to one another or is set up or used for this purpose.
  • Fig. 1 shows a part of a flow channel 1 of a turbomachine according to an embodiment of the present invention or a design of the flow channel 1 according to a method according to an embodiment of the present invention.
  • the flow channel 1 has a guide grid with several guide vanes distributed in the circumferential direction and flow passages delimited by two successive guide vanes, of which in Fig. 1 exemplary guide vanes 20 - 24 and flow passages 50 - 54 (partially) limited by them are shown.
  • the flow channel 1 further has a support rib arrangement with a plurality of support ribs distributed in the circumferential direction, of which in Fig. 1
  • a support rib 10 which is adjacent to the flow passage 51 downstream
  • a support rib 100 which is adjacent to the flow passage 54 downstream
  • the support ribs 10, 100 run parallel to the axial direction, ie they are not arranged or oriented at an angle to the axial direction. In other embodiments, not shown, the support ribs 10 and/or 100 are inclined to the axial direction or oriented in relation to the axial direction, for example with an angle between 5° and 10°, such as 5°, 6°, 7°, 8° , 9° or 10°.
  • a design of these flow passages 51, 54 adjacent to a support rib downstream is or is respectively adapted to the support rib 10 adjacent to it upstream or 100 adjusted to reduce pressure loss and/or vibration excitation.
  • the flow passage 51 is or will be in the circumferential direction (vertically in Fig. 1 ) positioned relative to the support rib 10 in such a way that a caster 12 (cf. Fig. 1 ) and a tangent 14 at a point of a downstream end region of a skeleton line 13 of the support rib 10 intersects an inlet cross section E of the flow passage 51 in a central region, as shown in Fig. 2 is shown.
  • the flow passage 54 is or will be positioned in the circumferential direction relative to the support rib 100 such that a wake or a tangent in a point of a downstream end region of a skeleton line of the support rib 100 intersects an inlet cross section of the flow passage 54 in a central region (not shown).
  • a flow passage-side pressure side 41 of the guide vane 21, which delimits the flow passage 51 is or is changed or adjusted, in particular compared to the flow passage-side pressure sides 40 and 43 of the guide vanes 20 and 23, which delimit the flow passage 50 and 53, respectively.
  • a flow passage-side suction side 32 of the guide vane 22, which delimits the flow passage 51 is or is changed or adapted, in particular compared to the flow passage-side suction sides 30 and 33 of the guide vanes 20 and 23, which delimit the flow passage 50 and 53, respectively.
  • stagger angles ⁇ 51 , ⁇ 52 of the guide vanes 21, 22, which delimit the flow passage 51 are or are changed or adjusted, in particular compared to the stagger angle ⁇ 50 of the guide vanes 20, which delimits the flow passage 50, as in Fig. 2 shown.
  • a running grid 70 of a turbine or a compressor is arranged downstream behind the guide grid with the guide blades 20-24.
  • a running grid 60 of another turbine is arranged upstream in front of the support rib arrangement with the support ribs 10, 100.
  • a compressor guide grid 60 is arranged upstream in front of the support rib arrangement with the support ribs 10, 100.

Claims (12)

  1. Procédé de fabrication d'un canal d'écoulement (1) pour une turbomachine, en particulier une turbine à gaz, lequel présente une grille de guidage comportant plusieurs aubes de guidage (20-24) distribuées sur la circonférence et des passages d'écoulement (50-54) délimités respectivement par deux aubes de guidage consécutives et un arrangement de nervures d'appui comportant plusieurs nervures d'appui (10, 100), pour chacune d'au moins la majorité de toutes les nervures d'appui de l'arrangement de nervures d'appui consécutives dans la direction circonférentielle, une configuration d'un passage d'écoulement (51, 54) de la grille de guidage, lequel est disposé en aval de cette nervure d'appui, étant adaptée à cette nervure d'appui, afin de réduire une perte de pression et/ou une excitation de vibration, caractérisé en ce que l'adaptation de la configuration des plusieurs passages d'écoulement aux nervures d'appui, en aval desquelles ils sont respectivement disposés, comprend un positionnement de ce passage d'écoulement (51, 54) dans la direction circonférentielle par rapport à cette nervure d'appui (10, 100) de telle sorte qu'un sillage (12) coupe une section transversale d'entrée (E) du passage d'écoulement dans une zone centrale, et comprend une modification d'une forme de ce passage d'écoulement par rapport à au moins un autre des passages d'écoulement (50, 52, 53) qui n'est pas un passage d'écoulement adjacent à une nervure d'appui, la modification de la forme comprenant une modification d'un angle de décalage (ß51, ß52) d'au moins une des deux aubes de guidage (22) qui délimitent ce passage d'écoulement, par rapport à une aube de guidage qui délimite un autre passage d'écoulement (50, 52, 53).
  2. Procédé selon la revendication précédente, caractérisé en ce que l'adaptation de la configuration d'au moins un de ces passages d'écoulement à la nervure d'appui en aval de laquelle il est disposé comprend une modification d'une forme de ce passage d'écoulement (51, 54) par rapport à au moins un autre des passages d'écoulement (50, 52, 53).
  3. Procédé selon la revendication précédente, caractérisé en ce que la modification de la taille et/ou de la forme de l'un passage d'écoulement (51, 54) par rapport à l'au moins un autre passage d'écoulement (50, 52, 53) comprend une modification, en particulier un agrandissement, d'une largeur de canal (B) dans la direction circonférentielle
    et/ou une modification d'un côté de pression (41, 44) côté passage d'écoulement d'une des deux aubes de guidage (21, 24) et/ou d'un côté d'aspiration (32) côté passage d'écoulement d'une des deux aubes de guidage (22) qui délimitent ce passage d'écoulement, et/ou d'un profil d'au moins une de ces deux aubes de guidage (21, 22, 24) par rapport à l'autre passage d'écoulement (50, 52, 53) ou à celui de cette aube de guidage ou de ces aubes de guidage (20, 23) qui le délimitent.
  4. Procédé selon l'une des revendications précédentes, caractérisé en ce que la grille de guidage est une grille de guidage antérieure d'une turbine d'une turbine à gaz, en particulier l'arrangement de nervures d'appui est disposé dans un châssis intermédiaire de turbines pour la connexion de deux turbines d'une turbine à gaz.
  5. Canal d'écoulement (1) pour une turbomachine, en particulier une turbine à gaz, qui présente une grille de guidage, comportant plusieurs aubes de guidage (20-24) distribuées sur la circonférence et des passages d'écoulement (50-54) délimités respectivement par deux aubes de guidage consécutives et un arrangement de nervures d'appui comportant au moins une nervure d'appui (10, 100), le canal d'écoulement étant fabriqué par un procédé selon l'une des revendications précédentes.
  6. Canal d'écoulement (1) selon la revendication 5, pour au moins la majorité de toutes les nervures d'appui de l'arrangement de nervure d'appui consécutives dans la direction circonférentielle respectivement, un passage d'écoulement (51, 54), qui est disposé en aval, en particulier adjacent, de cette nervure d'appui (10, 100), est positionné par rapport à cette nervure d'appui dans la direction circonférentielle de telle sorte qu'un sillage (12) coupe une section transversale d'entrée (E) du passage d'écoulement dans une zone centrale, une forme de ce passage d'écoulement étant différente de celle d'au moins un autre des passages d'écoulement, un angle de décalage (ß51, ß52) d'une des deux aubes de guidage, qui délimitent ce passage d'écoulement, étant différent de celui d'au moins un autre des passages d'écoulement.
  7. Canal d'écoulement (1) selon la revendication 5 ou 6, une taille de ce passage d'écoulement étant différente de celle d'au moins un autre des passages d'écoulement.
  8. Canal d'écoulement (1) selon l'une des revendications 5 à 7, une largeur de canal (B) de ce passage d'écoulement étant différente dans la direction circonférentielle de celle d'au moins un autre des passages d'écoulement.
  9. Canal d'écoulement (1) selon l'une des revendications 5 à 8, un côté de pression (41, 44) côté passage d'écoulement d'une des deux aubes de guidage qui délimitent ce passage d'écoulement étant différent de celui d'au moins un autre des passages d'écoulement.
  10. Canal d'écoulement (1) selon l'une des revendications 5 à 9, un côté d'aspiration (32) côté passage d'écoulement d'une des deux aubes de guidage qui délimitent ce passage d'écoulement étant différent de celui d'au moins un autre des passages d'écoulement.
  11. Canal d'écoulement (1) selon l'une des revendications 5 à 10, un profil d'au moins une des deux aubes de guidage qui délimitent ce passage d'écoulement étant différent de celui d'au moins un autre des passages d'écoulement.
  12. Turbomachine, en particulier turbine à gaz, comportant au moins un canal d'écoulement selon l'une des revendications précédentes.
EP18205690.3A 2017-12-01 2018-11-12 Canal d'écoulement de turbomachine Active EP3492701B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102017221684.0A DE102017221684A1 (de) 2017-12-01 2017-12-01 Turbomaschinen-Strömungskanal

Publications (2)

Publication Number Publication Date
EP3492701A1 EP3492701A1 (fr) 2019-06-05
EP3492701B1 true EP3492701B1 (fr) 2023-09-27

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EP (1) EP3492701B1 (fr)
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EP3492701A1 (fr) 2019-06-05
US20190169989A1 (en) 2019-06-06
DE102017221684A1 (de) 2019-06-06
US11396812B2 (en) 2022-07-26
ES2962229T3 (es) 2024-03-18

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