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
  • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
• • 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
  • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
  • F01D11/005—Sealing means between non relatively rotating elements
  • F01D11/006—Sealing the gap between rotor blades or blades and rotor
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D9/00—Stators
  • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
  • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
  • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2220/00—Application
  • F05D2220/30—Application in turbines
  • F05D2220/32—Application in turbines in gas turbines
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2240/00—Components
  • F05D2240/10—Stators
  • F05D2240/12—Fluid guiding means, e.g. vanes
• • 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
  • F05D2240/80—Platforms for stationary or moving blades

Definitions

• the invention relates to a guide vane intended to be fixed on a shroud of a stator of a gas turbine engine.
• the invention also relates to an assembly comprising a set of guide vanes and a gas turbine engine comprising such an assembly.
• Gas turbine engines generally include a fan module, a compressor module, a combustion chamber and a turbine module.
• the fan module, the compressor module and the turbine module each include rotating parts (or “rotor”) and fixed parts (or “stator”).
• the fan module comprises a fan casing and a fan rotor capable of being rotated relative to the fan casing.
• the fan rotor includes one or more rows of moving blades. The rotation of the fan rotor has the effect of compressing air which is expelled backwards to produce part of the engine thrust.
• the fan module generally comprises a set of fixed outlet vanes (also called “Outlet Guide Vanes” or “OGV” in English) arranged downstream of the fan rotor and acting as a rectifier.
• This set of fixed blades has the function of straightening and regulating the air flow which flows downstream of the fan rotor to optimize the engine thrust.
• This set of fixed blades also plays a role as a noise reducer.
• the air flow which passes through the set of fixed vanes generally flows between the fixed vanes in an upstream-downstream direction.
• secondary aerodynamic flows can appear near the roots of the fixed blades. Indeed, for each pair of blades facing each other, a pressure gradient between the pressure surface (intrados surface) of a blade and the depressed surface (extrados surface) d An adjacent blade generates a parasitic transverse flow which transports air from the lower surface to the upper surface of the adjacent blade.
• a corner separation or “corner separation” in English
• a vortex or “corner vortex” in English
• one solution consists of inserting between two adjacent fixed blades, a fin having the function of blocking the transverse flow of gas flowing from the lower surface of a fixed blade towards the upper surface of the blade. the adjacent fixed blade.
• Document FR 3 106 614 describes an example of a fin.
• a guide vane intended to be fixed on a stator shroud of a gas turbine engine comprising:
• the profiled part intended to extend in a gas flow to guide the gas flow, the profiled part having an intrados surface and an extrados surface, and
• a platform having a guide surface from which the profiled part extends, a first side surface and a second side surface, the second side surface being able to be arranged facing a first side surface of a blade adjacent identical guide, so that the platform of the guide vane delimits with the platform of the adjacent guide vane a flow path for the gas flow flowing between the profiled part of the guide vane and the profiled part of the adjacent guide vane,
• the guide surface comprising a first guide surface portion extending from the lower surface of the profiled portion to the first lateral surface and a second guide surface portion extending from the upper surface of the profiled part to the second side surface, in which a first junction line is formed at the intersection between the first guide surface part and the first side surface, a second junction line is formed at the intersection between the second guide surface part and the second side surface, a third junction line is formed at the intersection between the first guide surface part and the intrados surface, and a fourth line junction is formed at the intersection between the second guide surface part and the extrados surface, the
• the second radius greater than the first radius makes it possible to create a step (or a step) between the second guide surface of the guide vane and the first guide surface of the adjacent guide vane, preventing parasitic circulation of part of the gas flow from the lower surface of the guide vane to the upper surface of the guide vane.
• the second guide surface has an elevation relative to the first guide surface.
• the third transverse plane is defined as a transverse plane passing through a point of the fourth junction line where the curvature of the fourth junction line is maximum;
• the shroud is an internal rectifier shroud and the guiding surfaces of the guide vane platforms form an internal wall of the gas flow flow path. In another possible embodiment, the shroud is an external rectifier shroud and the guiding surfaces of the guide vane platforms form an external wall of the gas flow flow path.
• the assembly may be a compressor stator rectifier assembly or a turbine stator rectifier assembly or a fan rectifier assembly.
• the invention further relates to a gas turbine engine comprising an assembly as defined above.
• FIG. 1 represents, schematically, in longitudinal section, a gas turbine engine
• FIG. 2 represents, schematically, a stator rectifier assembly of a gas turbine engine
• FIG. 3 represents, schematically, guide vanes assembled on a stator shroud
• FIG. 4 represents, schematically, an assembly of two guide vanes conforming to a first embodiment of the invention
• FIG. 6 represents, schematically, in top view, an assembly of two guide vanes
• FIG. 7A to 7C represent, schematically, the two guide vanes conforming to the first embodiment, in three different transverse sectional planes,
• FIG. 7D represents, schematically, a view from the upper surface of one of the guide vanes of the assembly
• FIG. 7E represents, schematically, a view from the lower surface side of the other of the guide vanes of the assembly
• - Figures 8A to 8C represent, schematically, the two guide vanes conforming to the second embodiment, in three different transverse section planes
• FIG. 8D represents, schematically, a view from the upper surface of one of the guide vanes of the assembly
• the compressor module 4 comprises a low pressure compressor 10 and a high pressure compressor 11.
• the high pressure compressor 11 comprises a high pressure compressor casing 22, fixedly mounted relative to the nacelle 2, a high pressure compressor rotor 23, and a high pressure compressor stator 24.
• the high pressure compressor rotor 23 is able to be rotated relative to the high pressure compressor stator 24, around the longitudinal axis A of the engine 1.
• the high pressure compressor rotor 23 includes moving blades.
• the high-pressure compressor stator 24 includes fixed vanes (also called “guide vanes” or “rectifier vanes”) which are fixedly mounted on the casing 22 of the high-pressure compressor by being interposed between the moving vanes. These fixed vanes have the function of guiding the primary air flow through the high pressure compressor 11.
• the high pressure turbine 12 comprises a high pressure turbine casing 25, mounted fixed relative to the nacelle 2, a high pressure turbine rotor 26, and a high pressure turbine stator 27.
• the high pressure turbine rotor 26 is capable of being driven in rotation relative to the high pressure turbine stator 27, around the longitudinal axis A of the motor 1.
• the high pressure turbine rotor 26 comprises movable blades.
• the high pressure turbine stator 27 comprises fixed blades which are fixedly mounted on the casing 25 of the high pressure turbine by being interposed between the moving blades. These fixed vanes have the function of guiding the primary air flow through the high pressure turbine 12.
• the high pressure turbine rotor 26 is connected to the high pressure compressor rotor 23 via the high pressure shaft 15. Thus, when the engine 1 is in operation, the rotation of the high pressure turbine rotor 26 causes a rotation of the high pressure compressor rotor 23.
• the fixed outlet vanes 9 of the fan module 3, the fixed vanes of the stator 18 of the low pressure compressor 10, the fixed vanes of the high pressure compressor stator 24, the fixed vanes of the high pressure turbine stator 27 and the fixed vanes of the low pressure turbine stator 21 are examples of guide vanes.
• the fan 8 and the low pressure compressor 10 are driven in rotation by the low pressure turbine 13.
• the high pressure compressor 11 is driven in rotation by the high pressure turbine 12.
• the primary air flow flows from upstream to downstream of the gas turbine engine 1 in a primary stream, passing successively through the low pressure compressor 10, the high pressure compressor 11, the combustion chamber 5 where it is mixed with fuel to serve as an oxidizer, the high pressure turbine 12 and the low pressure turbine 13.
• the passage of the primary air flow through the high turbine pressure 12 and the low pressure turbine 13 causes a rotation of the rotors 26 and 29 of the turbines which in turn rotate the rotors 23 and 17 of the high pressure and low pressure compressors, as well as the fan 8 via the high pressure shaft 15 and the low pressure shaft 14.
• the primary air flow escapes from the engine 1 through an exhaust casing 28, located downstream of the low pressure turbine casing 19.
• the secondary air flow (also called “bypass air flow”) flows from upstream to downstream of the gas turbine engine 1 in a secondary stream. This secondary air flow does not pass into the combustion chamber 5 and does not drive the turbines 12 and 13.
• the secondary air flow serves both to cool the periphery of the engine body and makes it possible to generate the major part of the thrust provided by the gas turbine engine.
• the secondary air flow flows through the fixed vanes 9 mounted on the fan housing 7, downstream of the fan 8.
• FIG 2 schematically illustrates a stator rectifier assembly 30 of a gas turbine engine 1.
• the assembly 30 is a fan rectifier assembly.
• it could be a compressor stator rectifier assembly or a turbine stator rectifier assembly.
• the assembly 30 comprises an internal shroud 31, an external shroud 32, extending around the internal shroud 31, and a series of guide vanes 33.
• the internal ferrule 31 has an annular shape having a central axis.
• the external ferrule 32 has an annular shape, having a central axis coinciding with the central axis of the internal ferrule.
• the central axes coincide with the central axis A of the motor.
• Each guide vane 33 extends radially, from the internal shroud 31 to the external shroud 32.
• the guide vanes 33 form a grid making it possible to guide the air flow flowing between the guide vanes 33.
• Figure 3 shows how the guide vanes 33 can be mounted on a shroud 32.
• the guide vanes 33 are identical to each other.
• Each guide vane 33 comprises a first platform 34, a second platform 35 and a profiled part 36, extending radially from the first platform 34 to the second platform 35.
• the first platform 34 is intended to be positioned radially towards the exterior relative to the second platform 35, relative to the axis A of the motor.
• the guide vanes 33 are mounted on the external shroud 32. However, the guide vanes 33 can also be mounted in the same way on the internal shroud 31.
• the first platform 34 of each guide vane 33 comprises protrusions 37 capable of being engaged in circumferential grooves 38 of the shroud 32, in order to fix each guide vane 33 on the shroud 32.
• the guide vanes 33 are thus arranged next to each other over the entire circumference of the shroud 32, so as to form a row of guide vanes.
• the guide vanes 33 of the same row can have a constant angular spacing between two consecutive guide vanes.
• Each first platform 34 has a guide surface from which the profiled part 36 extends.
• each second platform 35 has a guide surface from which the profiled part 36 extends.
• the guide surfaces of the first platforms 34 of the guide vanes 33 form an external wall of the gas flow flow path.
• the guiding surfaces of the second platforms 35 of the guide vanes form an internal wall of the flow path of the gas flow.
• the assembly 30 comprises two rows of guide vanes 33 mounted on the shroud 32.
• Figure 4 represents, schematically, two adjacent guide vanes 33A and 33B of the same row, conforming to a first embodiment of the invention.
• the two guide vanes 33A and 33B are identical to each other.
• Each guide vane 33A, 33B comprises a platform 34A, 34B and a profiled part 36A, 36B.
• the profiled part 36A, 36B has a leading edge 41 A, 41 B, a trailing edge 42A, 42B, an intrados surface 43A, 43B and an extrados surface 44A, 44B.
• the platform 34A, 34B has a guide surface 45A, 45B from which the profiled part 36A, 36B extends, a first side surface 46A, 46B and a second side surface 47A, 47B.
• the second side surface 47B is suitable for being arranged opposite the first side surface 46A of the guide vane adjacent. More precisely, in the example illustrated in Figure 4, the second side surface 47B is suitable for being placed against the first side surface 46A, so that the platforms 34A and 34B of the two adjacent blades 33A and 33B fit together. one with the other.
• the platform 34B of the guide vane 33B delimits with the platform 34A of the adjacent guide vane 33A a flow path for the flow of gas flowing between the profiled part 36B of the guide vane 33B and the profiled part 36A of the adjacent guide vane 33A.
• the guide surface 45A, 45B of each guide vane 33A, 33B comprises a first guide surface part 48A, 48B and a second guide surface part 49A, 49B.
• the first guide surface part 48A, 48B extends from the intrados surface 43A, 43B of the profiled part 36A, 36B to the first side surface 46A, 46B.
• the second guide surface part 49A, 49B extends from the extrados surface 44A, 44B of the profiled part 36A, 36B to the second side surface 47A, 47B.
• a first junction line 51A, 51B is formed at the intersection between the first guide surface part 48A, 48B and the first side surface 46A, 46B.
• the first junction line 51 A, 51 B has a first radius R1 measured from the central axis A of the shroud 32 in a plane transverse to the central axis A.
• a second junction line 52A, 52B is formed at the intersection between the second guide surface part 49A, 49B and the second side surface 47A, 47B.
• the second junction line 52A, 52B has a second radius R2 measured from the central axis A of the ferrule 32, in the plane transverse to the central axis A.
• the second radius R2 is greater than the first radius R1, so as to form a step (or a step) between the second guide surface 49B of the guide vane 33B and the first guide surface 48A of the adjacent guide vane 33A.
• a portion of the second lateral surface 47B is not covered by the first lateral surface 46A and extends into the gas flow forming a wall preventing parasitic circulation of part of the gas flow from the surface d the intrados 43A of the guide vane 33A to the extrados surface 44B of the guide vane 33B.
• a third junction line 53A, 53B is formed at the intersection between the first part of guide surface 48A, 48B and the intrados surface 43A, 43B.
• the third junction line 53A, 53B has a third radius 53 measured from the central axis A of the shell 32, in the plane transverse to the central axis A.
• a fourth junction line 54A, 54B is formed at the intersection between the second part of guide surface 49A, 49B and the extrados surface 44A, 44B.
• the fourth junction line 54A, 54B has a fourth radius R4 measured from the central axis A of the ferrule 32, in the plane transverse to the central axis A.
• the fourth ray R4 is less than the third ray R3.
• the second part of guide surface 49A, 49B forms a depression near the upper surface 44A, 44B of the profiled part 33A, 33B, while it forms an elevation near the second lateral surface 47A , 47B.
• This depression makes it possible to compensate for the obstruction generated by the elevation which has the effect of reducing the passage section of the gas flow between the two profiled parts 36A and 36B.
• Figure 5 represents, schematically, two adjacent guide vanes 33A, 33B of the same row, conforming to a second embodiment of the invention.
• This second embodiment is identical to the first embodiment, except that in this second embodiment, the first guide surface part 48A, 48B and the second guide surface part 49A, 49B are configured such that the fourth ray R4 is equal to the third ray R3.
• the first ray R1 is less than the third ray R3.
• this second embodiment it is the first part of guide surface 48A, 48B which has a depression near the first lateral surface 46A, 46B.
• This depression in the first part of the guide surface 48A, 48B makes it possible to compensate for the obstruction generated by the raising of the second part of the guide surface 49A, 49B near the second lateral surface 47A, 47B, which has the effect of reduce the passage section of the gas flow between the two profiled parts 36A and 36B.
• Figure 6 represents, schematically, in top view, an assembly of two guide vanes 33A and 33B. This view is identical for the two preceding embodiments. As can be seen in Figure 6, the first side surface 46A, 46B and the second side surface 47A, 47B are not planar.
• first side surface 46A, 46B of each platform 34A, 34B has a concave shape and the second side surface 47A, 47B of each platform 34A, 34B has a convex shape, designed to fit with the concave shape of the first side surface 46A, 46B of the adjacent guide vane platform.
• each platform 34A, 34B has a first transverse surface 55A, 55B extending in a first transverse plane P1 located upstream of the leading edge 41 A, 41 B, and a second transverse surface 56A, 56B extending in a second transverse plane P2 located downstream of the trailing edge 42A, 42B.
• the first junction line 51 A, 51 B extends from the first transverse plane P1 to the second transverse plane P2.
• the first ray R1 and the second ray R2 vary continuously from the first transverse plane P1 to the second transverse plane P2.
• the third radius R3 and the fourth radius R4 vary continuously from the leading edge 41 A, 41 B to the trailing edge 42A, 42B of the profiled part 36A, 36B.
• Figure 6 illustrates three distinct cutting planes A-A, B-B and C-C, extending transversely with respect to the central axis A of the ferrule 32 by cutting the profiled part 36A, 36B.
• the cutting plane A-A is located upstream of the cutting plane B-B, which is itself located upstream of the cutting plane C-C, in the direction of flow of the gas flow.
• Figures 7A to 7C represent, schematically, the two guide vanes 33A, 33B respectively in the three different transverse sectional planes A-A, B-B and C-C, in accordance with the first embodiment.
• the second ray R2 is greater than the first ray R1. Furthermore, the fourth ray R4 is less than the third ray R3. Furthermore, a difference between the second ray R2 and the first ray R1 is equal to a difference between the third ray R3 and the fourth ray R4.
• Figure 7D shows a variation of the second ray R2 (in solid lines) relative to the first ray R1 between the first transverse plane P1 and the second transverse plane P2, and a variation of the fourth ray R4 (in dotted lines) relative to the third radius R3 between the leading edge 41 and the trailing edge 42.
• the first radius R1 has a constant value from the first transverse plane P1 to the second transverse plane P2.
• the value of the second ray R2 varies continuously from the first transverse plane P1 to the second transverse plane P2 so that a difference between the second ray R2 and the first ray R1 presents a zero value from the first transverse plane P1 to a third transverse plane P3 located between the first transverse plane P1 and the second transverse plane P2, then this difference increases continuously from a zero value in the third transverse plane P3, until a maximum value h in a fourth transverse plane P4 located between the third transverse plane P3 and the second transverse plane P2, and then this difference decreases continuously from the maximum value in the fourth transverse plane P4 to a zero value in the second plane transverse P2.
• An axial distance between the third transverse plane P3 and the second transverse plane P2 is between 10% and 40% of a chord length of the profiled part 36, the chord length of the profiled part 36 being defined as a distance between a point of intersection between the leading edge 41 and the guide surface 45 of the platform 34 and a point of intersection between the trailing edge 42 and the guide surface 45 of the platform 34.
• the third radius R3 has a constant value from the leading edge 41 to the trailing edge 42.
• the fourth ray R4 has a value which varies continuously from the leading edge 41 to the trailing edge 42, so that the difference between the second ray R2 and the first radius R1 is always equal to the difference between the third ray R3 and the fourth ray R4, in any transverse plane.
• the difference between the third ray R3 and the fourth ray R4 has a maximum value h in the fourth transverse plane P4.
• Figure 7E shows that the first radius R1 is constant from the first transverse plane P1 to the second transverse plane P2 and that the third radius R3 is equal to the first radius R1 from the leading edge 41 to the trailing edge 42 of the profiled part 36.
• Figures 8A to 8C represent, schematically, the two guide vanes 33A and 33B in the three different transverse sectional planes A-A, B-B and C-C, in accordance with the second embodiment.
• the second ray R2 is greater than the first ray R1.
• the third ray R3 and the fourth ray R4 are equal.
• a difference between the third ray R3 and the first ray R1 is equal to a difference between the second ray R2 and the fourth ray R4.
• Figure 8D shows a variation of the second ray R2 relative to the fourth ray R4, while Figure 8E shows a variation of the first ray R1 relative to the third ray R3 between the first transverse plane P1 and the second transverse plane P2.
• the fourth radius R4 has a constant value from the leading edge 41 to the trailing edge 42 of the profiled part 36.
• the value of the second ray R2 varies continuously from the first transverse plane P1 to the second transverse plane P2 so that a difference between the second ray R2 and the fourth ray R4 presents a zero value from the leading edge 41 to a third transverse plane P3 located between the first transverse plane P1 and the second transverse plane P2, then this difference increases continuously from a zero value in the third transverse plane P3, until at a maximum value h/2 in a fourth transverse plane P4 located between the third transverse plane P3 and the second transverse plane P2, and then this difference decreases continuously from the maximum value h/2 in the fourth transverse plane P4 to a zero value in the second transverse plane P2.
• the third transverse plane P3 is located in a zone in which shocks are likely to occur due to the flow of the gas flow at high speeds.
• the third radius R3 has a constant value from the leading edge 41 to the trailing edge 42 of the profiled part 36, equal to the value of the fourth radius R4.
• the difference between the third ray R3 and the first ray R1 also has a maximum value h/2 in the fourth transverse plane P4.

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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)

Applications Claiming Priority (2)

Publications (1)

Family

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Family Applications (1)

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Family Cites Families (5)

• 2022
  • 2022-09-09 FR FR2209065A patent/FR3139595B1/fr active Active
• 2023
  • 2023-09-08 WO PCT/FR2023/051362 patent/WO2024052631A1/fr not_active Ceased
  • 2023-09-08 EP EP23783476.7A patent/EP4584477A1/de active Pending
  • 2023-09-08 US US19/109,912 patent/US20260078683A1/en active Pending
  • 2023-09-08 CN CN202380064993.6A patent/CN119855974A/zh active Pending

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