EP3477049B1 - Turbine engine compressor with ring comprising elevations - Google Patents
Turbine engine compressor with ring comprising elevations Download PDFInfo
- Publication number
- EP3477049B1 EP3477049B1 EP18194178.2A EP18194178A EP3477049B1 EP 3477049 B1 EP3477049 B1 EP 3477049B1 EP 18194178 A EP18194178 A EP 18194178A EP 3477049 B1 EP3477049 B1 EP 3477049B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- compressor
- elevation
- blades
- blade
- protuberance
- 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.)
- Active
Links
- 238000011144 upstream manufacturing Methods 0.000 claims description 15
- 239000000463 material Substances 0.000 claims description 7
- 230000006835 compression Effects 0.000 description 4
- 238000007906 compression Methods 0.000 description 4
- 238000000926 separation method Methods 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 230000018109 developmental process Effects 0.000 description 2
- 239000002964 rayon Substances 0.000 description 2
- 230000008719 thickening Effects 0.000 description 2
- 229920000297 Rayon Polymers 0.000 description 1
- 238000012550 audit Methods 0.000 description 1
- 230000003416 augmentation Effects 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 210000003679 cervix uteri Anatomy 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000004567 concrete Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000004907 flux Effects 0.000 description 1
- 230000033001 locomotion Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 239000011800 void material Substances 0.000 description 1
Images
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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—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
- 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
- F05D2240/123—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
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/71—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
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/71—Shape curved
- F05D2250/711—Shape curved convex
-
- 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
- F05D2250/712—Shape curved concave
Definitions
- a compressor with a profiled inter-blade surface is provided.
- the invention also relates to an axial turbomachine, in particular an aircraft turbojet or an aircraft turboprop.
- the document US 2007/0059177 A1 discloses a turbojet compressor.
- the compressor has an annular row of blades.
- a platform is associated with each blade and presents a three-dimensional relief extending between two successive blades.
- Each relief has two humps separated by a sinusoidal channel sinking radially into the platform.
- This geometry improves the aerodynamic efficiency of an axial flow compressor blade. However, it shows a high corner separation on the upper surface of the blades.
- the document FROM 10 2015 224 376 A1 shows an inter-blade surface provided with four local extrema (two hollows and two bumps), separated two by two by cylindrical portions and a point of zero gradient.
- the subject of the invention is an axial turbomachine compressor according to claim 1.
- the invention also relates to a turbomachine, in particular an aircraft turbojet, comprising a compressor, remarkable in that the compressor conforms to the invention, preferably the row of blades comprises at least: fifty, or eighty blades.
- each embodiment of the invention can be combined with each object of the invention.
- the compression in the passage increases, as does the flow through it.
- the protrusion and bumps deal with the phenomena of swirls and separations.
- the flow using the passage returns to the upper surface during its compression, which limits corner separation.
- the terms “internal” and “external” refer to positioning relative to the axis of rotation of an axial turbomachine.
- the axial direction corresponds to the direction along the axis of rotation of the turbomachine.
- the radial direction is perpendicular to the axis of rotation. Upstream and downstream refer to the main flow direction of the flow in the turbomachine.
- a blower 16 or fan 16 is coupled to the rotor 12 and generates an air flow which is divided into a primary flow 18 and a secondary flow 20 passing through an annular duct (partially shown).
- the secondary flow can be accelerated so as to generate a thrust reaction necessary for the flight of an aircraft.
- the primary 18 and secondary 20 flows are annular.
- FIG 2 is a sectional view of a compressor of an axial turbomachine such as that of the figure 1 .
- the compressor can be a low-pressure compressor 4.
- the rotor 12 comprises several rows of rotor blades 24, in this case three. It can be a one-piece bladed drum, or include blades fixed by dovetail.
- the rotor blades 24 can extend radially from an individual platform, or from an internal ring 25 of the rotor 12.
- the low-pressure compressor 4 comprises several rectifiers, in this case four, which each contain a row of stator vanes 26.
- the rectifiers are associated with the fan 16 or with a row of rotor vanes to straighten the air flow, so as to convert the speed of the flow into pressure, in particular into static pressure.
- the stator vanes 26 extend essentially radially from an external casing 28. They can be fixed there and immobilized using fixing pins 30. They pass radially through the primary flow 18.
- the stator vanes can be of fixed orientation by relative to the casing 28.
- the blades of the same row are identical and aligned. Each row can include one hundred and twenty blades (26; 24).
- Internal shrouds 32 can be suspended from the internal ends of the stator vanes 26.
- the internal shrouds 32 can cooperate in a sealed manner with the rotor 12 in order to improve the compression ratio of the compressor 4.
- Each blade 26 comprises a leading edge 34, a trailing edge 36, as well as an intrados surface 38 and an extrados surface 40. These surfaces (38; 40) can be curved and domed respectively. Each of these surfaces extends from the leading edge 34 to the corresponding trailing edge 36.
- the blade 26 may comprise a stack of arched aerodynamic profiles 41, the sides of which generate the intrados surface 38 and the extrados surface 40. At the level of the trailing edges 36, the contours of the profiles 41, on the intrados and/or on the extrados, are parallel and/or tangent to the axis of rotation 14 of the compressor.
- the consecutive blades 26 of the annular row define between them a passage 42, also called inter-blade passage 42.
- This passage 42 is circumferentially partitioned by the blades 26, and delimited by the intrados and extrados surfaces.
- the passage 42 has a connecting surface 44 between the two consecutive blades 26, and connects the intrados surface 38 which faces the extrados surface 40 through the passage 42.
- the connecting surface 44 can be delimited axially by an upstream axis 46 and a downstream axis 48 which connect the leading edges 34 and the trailing edges 36 respectively. These axes (46; 48) can be parallel, and can generally define a parallelogram or a trapezoid.
- the connecting surface 44 can be generally flat.
- the connecting surface 44 can be a tubular surface part or a cone surface part, in particular because of the radius of the ferrule and the optional variation in diameter of the ferrule 32 along the axis of rotation 14. It may include four corners 50 corresponding to the intersections between the edges (34; 36) and the support, in this case the ferrule 32, for example internal.
- connection surface 44 an upstream zone 47 extending downstream from the upstream axis 46, and a downstream zone 49 extending upstream from the downstream axis 48.
- the connecting surface 44 has an axial asymmetry with respect to the axis of rotation 14. It has a protuberance 52, in particular a main protuberance 52. This protuberance 52 can occupy most of the connecting surface 44. The axial majority of the protuberance 52 can be contained in the upstream half of the row of blades 26. It forms a radial addition of material on the connecting surface 44. The addition of material can be observed by compared to zones 47 and 49.
- the protuberance 52 also includes a first bump 54 with a first vertex 56, and a second bump 58 with a second vertex 60. These bumps 54 and 58 can be the main bosses of the protuberance 52, that is to say that they form the main volume reliefs.
- the bumps (54; 58) can extend over at most the axial majority of the blades 26.
- the first bump can extend axially over 30% of the chord 62 of the first blade 26, and/or the second bump 58 can extend axially over 20% of the chord 62 of the second blade 26.
- These bumps (54; 58) can be set back axially from the leading edges 34, in particular by 10% the axial length of a chord 62.
- the first vertex 56 may have a main elongation parallel to the chord 62 of the first blade 26.
- the first bump 54 can extend over 50% of the inter-blade passage 42 and extend from the intrados surface 38. Its apex 56 can be at a distance from the intrados surface 38.
- a channel 64 can be formed against the first boss 54, between the intrados surface 38 of the first blade 26 and the first vertex 56.
- the second boss 58 can extend circumferentially over 10% of the passage 42, its vertex 60 can be attached to the extrados surface 40 of the second dawn 26.
- the first bump 54 and the second bump 58 can be at the same level axially. Their vertices (56; 60) can be aligned axially. The bumps (54; 58) are separated from each other, and in particular spaced from each other along the circumference. A pass 66, like a mountain pass, separates the summits circumferentially.
- Curve 67 is the shortest curve of neck 66 between vertices 56 and 60. This curve 67 as well as all the points of neck 66 are raised relative to the regular surface in the absence of protuberance, represented by zones 47 and 49, of constant radius.
- the bumps (54; 58) and the protrusion 52 are represented using level lines 68. These level lines 68 mark variations in radial level relative to a reference surface, in this case the connecting surface 44.
- the figure 4 is a cut of the Figure 3 along axis IV-IV. The position and inclination of the axis of rotation 14 are figurative and may vary in concrete embodiments.
- the blades may include connecting radii 70 at their radial ends.
- the connecting spokes 70 can surround their respective blade 26.
- the connecting surface 44 can extend from the connecting spokes 70 so as to connect them two by two.
- the radial thickness of the connecting radii 70 is less than that of the bumps and possibly the protuberance 52.
- This annular surface 33 can have a constant radius RC outside the passages.
- the annular surface 33 may have axial symmetry. Zones 47 and 49 can extend the annular surface 33 and be tangent there axially. They present arcs of constant radii RC according to the circumference.
- a first dotted line 72 extends zones 47 and 49, and connects them.
- a second dotted line 74 illustrates the general profile of the protuberance 52. The radial distance between these dotted lines (72; 74) highlights the overmaterial, that is to say the radial development that the protuberance 52 forms on the connecting surface 44.
- the continuous line 76 which is spaced from the second dotted line 74 highlights the radial development that the first bump 54 forms on the protuberance 52, i.e. the local thickening of the connecting surface 44.
- the continuous line 76 can pass through the first vertex 56. The latter can be flat.
- the inherent radial thickness of the first bump 54 may be twice greater than the inherent thickness of the protuberance 52. These thicknesses may be maximum thicknesses.
- This teaching can also be applied to an external shell or to a casing via symmetry along the A-A axis.
- FIG. 5 is a cut of the Figure 3 along the VV axis.
- the section is perpendicular to the axis of rotation 14, and passes through the two bosses (54; 58) like the protuberance 52.
- the connecting surface 44 has a constant radius RC.
- This constant radius RC can correspond to that of the first zone 47 and/or to that of the second zone 49.
- the connecting surface 44 shows a variable radius RV.
- the first vertex 56 of the first hump 54 is arranged between the pass 66 and the channel 64.
- the connecting surface 44 is profiled. It presents an increase in radial material relative to its base, in particular generated by the zones (47; 49).
- the radius RV of the connecting surface 44 can vary when it travels over the connecting surface 44 in the circumferential direction 15, in particular by moving by one blade 26 to its neighbor, i.e. between the intrados surface 38 and the extrados surface 40.
- the connection surface can be reproduced identically between each neighboring blade of the same row. This can form several annular rows of identical bumps (54; 58) as well as several annular rows of identical protuberances 52.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
L'invention concerne un compresseur avec une surface inter-aubes profilée. L'invention a également trait à une turbomachine axiale, notamment un turboréacteur d'avion ou un turbopropulseur d'aéronef.A compressor with a profiled inter-blade surface is provided. The invention also relates to an axial turbomachine, in particular an aircraft turbojet or an aircraft turboprop.
Le document
L'invention a pour objectif de résoudre au moins un des problèmes posés par l'art antérieur. Plus précisément, l'invention a pour objectif d'optimiser le taux de compression et les décollements en coin au niveau de l'extrados. L'invention a également pour objectif de proposer une solution simple, résistante, légère, économique, fiable, facile à produire, et commode d'entretien.The invention aims to solve at least one of the problems posed by the prior art. More precisely, the invention aims to optimize the compression rate and corner separations at the level of the extrados. The invention also aims to provide a simple, resistant, lightweight, economical, reliable, easy to produce and easy to maintain solution.
De manière générale, l'invention peut être entendue comme une bosse à deux sommets principaux, et/ou une convexité à deux extrémums radiaux ; entre deux aubes consécutives d'un compresseur.Generally speaking, the invention can be understood as a bump with two main vertices, and/or a convexity with two radial extrema; between two consecutive blades of a compressor.
L'invention a pour objet un compresseur de turbomachine axiale selon la revendication 1.The subject of the invention is an axial turbomachine compressor according to claim 1.
Selon des modes avantageux de l'invention, le compresseur peut comprendre une ou plusieurs des caractéristiques suivantes, prises isolément ou selon toutes les combinaisons techniques possibles :
- La protubérance s'étend sur la majorité de la surface de liaison.
- La première bosse et la deuxième bosse sont disposées en moitié amont de la protubérance et/ou des aubes de la rangée.
- La première bosse est davantage développée radialement que la deuxième bosse depuis la protubérance et/ou depuis le niveau général de la surface de liaison.
- La première bosse s'étend depuis la surface intrados de la première aube, et ledit premier sommet est à distance de ladite surface intrados. Alternativement, le sommet peut être au contact de la surface intrados.
- La deuxième bosse s'étend depuis la surface extrados de la deuxième aube, et ledit sommet est accolé à ladite surface extrados. Alternativement, le sommet peut être à distance de la surface extrados.
- La surface de liaison présente un tiers amont s'étendant depuis les bords d'attaque, la première bosse et la deuxième bosse étant renfermées dans ledit tiers amont.
- La surface de liaison comporte quatre coins définissant un plan moyen, lesdits coins étant disposés aux bords d'attaque et aux bords de fuite des aubes, la protubérance formant une augmentation de matière radiale de la surface de liaison par rapport audit plan moyen, notamment le plan général.
- Axialement, la longueur de la première bosse est comprise entre 30% et 50% ; valeurs comprises ; de la longueur de la première aube.
- Selon la circonférence, la largeur de la première bosse est comprise entre 40% et 60% ; valeurs comprises ; de la largeur du passage inter-aubes.
- Axialement, la longueur de la deuxième bosse est comprise entre 15% et 25% ; valeurs comprises ; de la longueur de la deuxième aube.
- Selon la circonférence, la largeur de la deuxième bosse est comprise entre 5% et 15% ; valeurs comprises ; de la largeur du passage inter-aubes.
- La surface de la deuxième bosse représente au plus 5% de la surface de la protubérance.
- La hauteur radiale maximale de la première bosse est supérieure ou égale au triple de la hauteur radiale maximale de la deuxième bosse, et/ou supérieure ou égale à dix fois la hauteur maximale de la protubérance mesurée en dehors des bosses.
- Le compresseur comprend un stator avec une virole, notamment une virole interne, reliée à la rangée annulaire d'aubes, la surface de liaison étant formée sur ladite virole.
- Selon la circonférence le col s'étend sur 40% à 60% ; valeurs incluses ; du passage inter-aubes.
- La première bosse et la deuxième bosse présentent des extremums, notamment leurs sommets, disposés axialement au même niveau.
- Selon la circonférence, la première bosse est disposée à l'opposé de la deuxième bosse dans le passage inter-aubes.
- La surface de liaison, notamment les bosses et la protubérance, est/sont en contact du flux du compresseur.
- La hauteur radiale maximale de la deuxième bosse est supérieure ou égale au triple de la hauteur radiale maximale de la protubérance mesurée en dehors des bosses.
- Par rapport à la surface de liaison, la protubérance forme une surépaisseur de 0,30 mm.
- La protubérance présente une moitié aval et une moitié amont dans laquelle sont renfermées la première bosse et la deuxième bosse.
- La protubérance traverse circonférentiellement le passage et/ou relie les aubes.
- Chaque aube comprend une corde dont l'angle d'inclinaison par rapport à l'axe de rotation est inférieure ou égale à : 15°, ou 30°, ou 40°.
- La surface de liaison est libre de creux, notamment de creux s'étendant sur au plus : 20%, ou 10%, ou 5% ou 1% de la surface de liaison, chaque creux étant notamment entendu comme un vide de matière par rapport au plan général.
- En tout point, la surface de liaison présente une quantité de matière positive ou nulle par rapport au plan général.
- Le passage comprend un axe amont reliant les bords d'attaque, et un axe aval reliant les bords de fuite, lesdits axes délimitant axialement la surface de liaison.
- La première aube et la deuxième aube sont des aubes consécutives et/ou voisines, et/ou inclinées circonférentiellement d'au plus : 10° ou 5° l'une par rapport à l'autre.
- Les aubes de la rangée annulaire sont alignées circonférentiellement, leurs bords d'attaque et leurs bords de fuite sont alignés circonférentiellement.
- Axialement au niveau du bord de fuite, la surface intrados et/ou la surface extrados est parallèle à l'axe de rotation du compresseur.
- Chaque bosse et/ou la protubérance sont à distance axialement des bords d'attaque et des bords de fuite.
- Chaque aube comprend un rayon de raccordement, la surface de liaison s'étendant depuis les rayons de raccordement de la première aube et de la deuxième aube.
- La bosse est convexe, selon au moins deux directions, et/ou forme un épaississement sur le support.
- Chaque aube comprend une corde et un espace entre sa surface intrados et ladite corde, le premier sommet étant majoritairement ou totalement à l'intérieur dudit espace, et/ou la première bosse étant majoritairement en dehors dudit espace.
- Perpendiculairement à la corde, l'envergure de la deuxième bosse est inférieure à l'envergure de l'aube.
- Par rapport au plan général, les bosses présentent des inclinaisons supérieures à celles de la protubérance.
- The protuberance extends over the majority of the bonding surface.
- The first boss and the second boss are arranged half upstream of the protuberance and/or the blades of the row.
- The first bump is more developed radially than the second bump from the protuberance and/or from the general level of the connecting surface.
- The first bump extends from the intrados surface of the first blade, and said first vertex is at a distance from said intrados surface. Alternatively, the top can be in contact with the intrados surface.
- The second boss extends from the extrados surface of the second blade, and said vertex is attached to said extrados surface. Alternatively, the apex may be remote from the extrados surface.
- The connecting surface has an upstream third extending from the leading edges, the first bump and the second bump being enclosed in said upstream third.
- The connecting surface has four corners defining a mean plane, said corners being arranged at the leading edges and at the trailing edges of the blades, the protuberance forming an increase in radial material of the connecting surface relative to said mean plane, in particular the general plan.
- Axially, the length of the first bump is between 30% and 50%; values included; of the length of the first blade.
- Depending on the circumference, the width of the first bump is between 40% and 60%; values included; of the width of the inter-blade passage.
- Axially, the length of the second bump is between 15% and 25%; values included; of the length of the second blade.
- Depending on the circumference, the width of the second bump is between 5% and 15%; values included; of the width of the inter-blade passage.
- The surface of the second bump represents at most 5% of the surface of the protuberance.
- The maximum radial height of the first bump is greater than or equal to three times the maximum radial height of the second bump, and/or greater than or equal to ten times the maximum height of the protuberance measured outside the bumps.
- The compressor comprises a stator with a shroud, in particular an internal shroud, connected to the annular row of blades, the connecting surface being formed on said shroud.
- Depending on the circumference the cervix extends 40% to 60%; values included; of the inter-blade passage.
- The first bump and the second bump have extrema, in particular their vertices, arranged axially at the same level.
- According to the circumference, the first boss is arranged opposite the second boss in the inter-blade passage.
- The bonding surface, including the bumps and protrusion, is/are in contact with the compressor flow.
- The maximum radial height of the second bump is greater than or equal to three times the maximum radial height of the protuberance measured outside the bumps.
- Compared to the connection surface, the protuberance forms an extra thickness of 0.30 mm.
- The protuberance has a downstream half and an upstream half in which the first bump and the second bump are enclosed.
- The protrusion circumferentially crosses the passage and/or connects the blades.
- Each blade comprises a rope whose angle of inclination relative to the axis of rotation is less than or equal to: 15°, or 30°, or 40°.
- The connecting surface is free of hollows, in particular hollows extending over at most: 20%, or 10%, or 5% or 1% of the connecting surface, each hollow being understood in particular as a void of material in relation to on a general level.
- At any point, the connection surface has a positive or zero quantity of material compared to the general plane.
- The passage comprises an upstream axis connecting the leading edges, and a downstream axis connecting the trailing edges, said axes axially delimiting the connection surface.
- The first blade and the second blade are consecutive and/or neighboring blades, and/or circumferentially inclined by at most: 10° or 5° relative to each other.
- The blades of the annular row are circumferentially aligned, their leading edges and their trailing edges are circumferentially aligned.
- Axially at the trailing edge, the intrados surface and/or the extrados surface is parallel to the axis of rotation of the compressor.
- Each bump and/or protrusion is spaced axially from the leading edges and trailing edges.
- Each blade includes a connecting radius, the connecting surface extending from the connecting radii of the first blade and the second blade.
- The bump is convex, in at least two directions, and/or forms a thickening on the support.
- Each blade comprises a chord and a space between its intrados surface and said chord, the first vertex being mainly or totally inside said space, and/or the first bump being mainly outside said space.
- Perpendicular to the chord, the span of the second hump is less than the span of the blade.
- Compared to the general plane, the bumps have inclinations greater than those of the protuberance.
L'invention a également pour objet une turbomachine, notamment un turboréacteur d'aéronef, comprenant un compresseur, remarquable en ce que le compresseur est conforme à l'invention, préférentiellement la rangée d'aubes comprend au moins : cinquante, ou quatre-vingt aubes.The invention also relates to a turbomachine, in particular an aircraft turbojet, comprising a compressor, remarkable in that the compressor conforms to the invention, preferably the row of blades comprises at least: fifty, or eighty blades.
De manière générale, chaque mode de réalisation de l'invention est combinable à chaque objet de l'invention.Generally speaking, each embodiment of the invention can be combined with each object of the invention.
La compression dans le passage augmente, tout comme le débit le traversant. Dans les conditions de fonctionnement d'un compresseur, la protubérance et les bosses traitent les phénomènes de tourbillons et de décollements. Le flux empruntant le passage regagne l'extrados au cours de sa compression, ce qui limite le décollement en coin.The compression in the passage increases, as does the flow through it. Under the operating conditions of a compressor, the protrusion and bumps deal with the phenomena of swirls and separations. The flow using the passage returns to the upper surface during its compression, which limits corner separation.
-
La
figure 1 représente une turbomachine axiale selon l'invention.Therefigure 1 represents an axial turbomachine according to the invention. -
La
figure 2 est un schéma d'un compresseur de turbomachine selon l'invention.Therefigure 2 is a diagram of a turbomachine compressor according to the invention. -
La
figure 3 illustre deux aubes de compresseur bordant une surface de liaison selon l'invention.ThereFigure 3 illustrates two compressor blades bordering a connecting surface according to the invention. -
La
figure 4 est une coupe de lafigure 3 selon l'axe IV-IV.Therefigure 4 is a cut of theFigure 3 along axis IV-IV. -
La
figure 5 est une coupe de lafigure 3 selon l'axe V-V.Therefigure 5 is a cut of theFigure 3 along the VV axis.
Dans la description qui va suivre, les termes « interne » et « externe » renvoient à un positionnement par rapport à l'axe de rotation d'une turbomachine axiale. La direction axiale correspond à la direction le long de l'axe de rotation de la turbomachine. La direction radiale est perpendiculaire à l'axe de rotation. L'amont et l'aval sont en référence au sens d'écoulement principal du flux dans la turbomachine.In the description which follows, the terms “internal” and “external” refer to positioning relative to the axis of rotation of an axial turbomachine. The axial direction corresponds to the direction along the axis of rotation of the turbomachine. The radial direction is perpendicular to the axis of rotation. Upstream and downstream refer to the main flow direction of the flow in the turbomachine.
La
Une soufflante 16 ou ventilateur 16 est couplé au rotor 12 et génère un flux d'air qui se divise en un flux primaire 18 et en un flux secondaire 20 traversant un conduit annulaire (partiellement représenté). Le flux secondaire peut être accéléré de sorte à générer une réaction de poussée nécessaire au vol d'un avion. Les flux primaire 18 et secondaire 20 sont annulaires.A
La
Le rotor 12 comprend plusieurs rangées d'aubes rotoriques 24, en l'occurrence trois. Il peut être un tambour monobloc aubagé, ou comprendre des aubes à fixation par queue d'aronde. Les aubes rotoriques 24 peuvent s'étendre radialement depuis une plateforme individuelle, ou depuis une couronne interne 25 du rotor 12.The
Le compresseur basse-pression 4 comprend plusieurs redresseurs, en l'occurrence quatre, qui contiennent chacun une rangée d'aubes statoriques 26. Les redresseurs sont associés au fan 16 ou à une rangée d'aubes rotoriques pour redresser le flux d'air, de sorte à convertir la vitesse du flux en pression, notamment en pression statique.The low-
Les aubes statoriques 26 s'étendent essentiellement radialement depuis un carter extérieur 28. Elles peuvent y être fixées et immobilisées à l'aide d'axes de fixation 30. Elles traversent radialement le flux primaire 18. Les aubes statoriques peuvent être à orientation fixe par rapport au carter 28. Avantageusement, les aubes d'une même rangée sont identiques et alignées. Chaque rangée peut comprendre cent vingt aubes (26 ; 24).The stator vanes 26 extend essentially radially from an
Des viroles internes 32 peuvent être suspendues aux extrémités internes des aubes statoriques 26. Les viroles internes 32 peuvent coopérer de manière étanche avec le rotor 12 afin d'améliorer le taux de compression du compresseur 4.Internal shrouds 32 can be suspended from the internal ends of the stator vanes 26. The
La
La rangée peut être une des rangées présentées en relation avec les figures précédentes. Les aubes et leur support, éventuellement la virole interne 32, sont représentés en plan. L'axe de rotation 14 est tracé à une position figurative, et fournit un repère spatial.The row may be one of the rows presented in relation to the previous figures. The blades and their support, possibly the
Chaque aube 26 comprend un bord d'attaque 34, un bord de fuite 36, ainsi qu'une surface intrados 38 et une surface extrados 40. Ces surfaces (38 ; 40) peuvent être incurvées et bombées respectivement. Chacune de ces surfaces s'étend du bord d'attaque 34 au bord de fuite 36 correspondant. L'aube 26 peut comporter un empilement de profils aérodynamiques 41 cambrés, dont les côtés génèrent la surface intrados 38 et la surface extrados 40. Au niveau des bords de fuite 36, les contours des profils 41, en intrados et/ou en extrados, sont parallèles et/ou tangents à l'axe de rotation 14 du compresseur.Each
Les aubes 26 consécutives de la rangée annulaire définissent entre elle un passage 42, également appelé passage inter-aubes 42. Ce passage 42 est cloisonné circonférentiellement par les aubes 26, et délimités par les surfaces intrados et extrados. Le passage 42 présente une surface de liaison 44 entre les deux aubes 26 consécutives, et relie la surface intrados 38 qui est en regard de la surface extrados 40 au travers du passage 42.The
La surface de liaison 44 peut être délimitée axialement par un axe amont 46 et un axe aval 48 qui relient les bords d'attaque 34 et les bords de fuite 36 respectivement. Ces axes (46 ; 48) peuvent être parallèles, et peuvent généralement définir un parallélogramme ou un trapèze. La surface de liaison 44 peut être généralement plane.The connecting
Plus précisément, la surface de liaison 44 peut être une partie de surface tubulaire ou une partie de surface de cône, notamment en raison du rayon de la virole et de l'optionnelle variation de diamètre de la virole 32 le long de l'axe de rotation 14. Elle peut comprendre quatre coins 50 correspondant aux intersections entre les bords (34 ; 36) et le support, en l'occurrence la virole 32, par exemple interne.More precisely, the connecting
La surface de liaison 44 une zone amont 47 s'étendant vers l'aval depuis l'axe amont 46, et une zone aval 49 s'étendant vers l'amont depuis l'axe aval 48.The
La surface de liaison 44 présente une asymétrie axiale par rapport à l'axe de rotation 14. Elle présente une protubérance 52, notamment une protubérance principale 52. Cette protubérance 52 peut occuper la majeure partie de la surface de liaison 44. La majorité axiale de la protubérance 52 peut être contenue dans la moitié amont de la rangée d'aubes 26. Elle forme un ajout de matière radial sur la surface de liaison 44. L'ajout de matière peut être observé par rapport aux zones 47 et 49.The connecting
La protubérance 52 comprend également une première bosse 54 avec un premier sommet 56, et une deuxième bosse 58 avec un deuxième sommet 60. Ces bosses 54 et 58 peuvent être les bosses principales de la protubérance 52, c'est-à-dire qu'elles en forment les reliefs de volume principaux.The
Les bosses (54 ; 58) peuvent s'étendre sur au plus la majorité axiale des aubes 26. La première bosse peut s'étendre axialement sur 30% de la corde 62 de la première aube 26, et/ou la deuxième bosse 58 peut s'étendre axialement sur 20% de la corde 62 de la deuxième aube 26. Ces bosses (54 ; 58) peuvent être en retrait axialement des bords d'attaque 34, notamment de 10% la longueur axiale d'une corde 62. Le premier sommet 56 peut présenter un allongement principal parallèle à la corde 62 de la première aube 26.The bumps (54; 58) can extend over at most the axial majority of the
Selon la circonférence 15, la première bosse 54 peut s'étendre sur 50% du passage inter-aubes 42 et s'étendre depuis la surface intrados 38. Son sommet 56 peut être à distance de la surface intrados 38. Un chenal 64 peut être formé contre la première bosse 54, entre la surface intrados 38 de la première aube 26 et le premier sommet 56. La deuxième bosse 58 peut s'étendre circonférentiellement sur 10% du passage 42, son sommet 60 peut être accolé à la surface extrados 40 de la deuxième aube 26.Depending on the
La première bosse 54 et la deuxième bosse 58 peuvent être au même niveau axialement. Leurs sommets (56 ; 60) peut être alignés axialement. Les bosses (54 ; 58) sont séparées l'une de l'autre, et notamment distantes l'une de l'autre selon la circonférence. Un col 66, tel un col de montagne, sépare les sommets circonférentiellement.The
La courbe 67 est la courbe du col 66 la plus courte entre les sommets 56 et 60. Cette courbe 67 ainsi que tous les points du col 66 sont en surélévation par rapport à la surface régulière en absence de protubérance, représentée par les zones 47 et 49, de rayon constant.
Les bosses (54 ; 58) et la protubérance 52 sont représentés à l'aide de lignes de niveau 68. Ces lignes de niveau 68 marquent des variations de niveau radial par rapport à une surface de référence, en l'occurrence la surface de liaison 44. La
De manière générale, les aubes peuvent comprendre des rayons de raccordement 70 à leurs extrémités radiales. Les rayons de raccordement 70 peuvent entourer leur aube 26 respective. La surface de liaison 44 peut s'étendre depuis les rayons de raccordement 70 de manière à les relier deux à deux. L'épaisseur radiale des rayons de raccordement 70 est inférieure à celle des bosses et éventuellement de la protubérance 52.Generally speaking, the blades may include connecting
Le bord d'attaque 34 et le bord de fuite 36 de la première aube s'étendant radialement depuis la surface annulaire 33 de la virole interne 32. Cette surface annulaire 33 peut présenter un rayon constant RC en dehors des passages. La surface annulaire 33 peut présenter une symétrie axiale. Les zones 47 et 49 peuvent prolonger la surface annulaire 33 et y être tangentes axialement. Elles présentent des arcs de rayons constants RC selon la circonférence.The leading
Un premier trait pointillé 72 prolonge les zones 47 et 49, et les relie. Un deuxième trait pointillé 74 illustre le profil général de la protubérance 52. L'écart radial entre ces traits pointillés (72 ; 74) met en évidence la surmatière, c'est-à-dire le développement radial que forme la protubérance 52 sur la surface de liaison 44. De même, la ligne continue 76 qui est écartée du deuxième trait pointillé 74 met en évidence le développement radial que forme la première bosse 54 sur la protubérance 52, soit l'épaississement local de la surface de liaison 44. La ligne continue 76 peut passer par le premier sommet 56. Ce dernier peut être plat.A first dotted
L'épaisseur radiale propre de la première bosse 54 peut être deux fois supérieure à l'épaisseur propre de la protubérance 52. Ces épaisseurs peuvent être des épaisseurs maximales.The inherent radial thickness of the
Par rapport au plan général 80 de la surface de liaison 44, les bosses (54 ; 58) présentent des inclinaisons supérieures à celles de la protubérance 52. Le plan général 80 peut joindre au moins un ou plusieurs ou chaque coin de la surface de liaison 44. En amont et en aval, la protubérance 52 présente des pentes plus faibles que les pentes attenantes des bosses.With respect to the
Le présent enseignement peut également être appliqué à une virole externe ou à un carter via une symétrie selon l'axe A-A.This teaching can also be applied to an external shell or to a casing via symmetry along the A-A axis.
La
Autour de l'axe de rotation 14, la surface de liaison 44 présente un rayon constant RC. Ce rayon constant RC peut correspondre à celui de la première zone 47 et/ou à celui de la deuxième zone 49. Au niveau des bosses (54 ; 58), elle montre un rayon variable RV. Le premier sommet 56 de la première bosse 54 est disposé entre le col 66 et le chenal 64.Around the axis of
La surface de liaison 44 est profilée. Elle présente une augmentation de matière radiale par rapport à sa base, notamment générée par les zones (47 ; 49). En un point donné de l'axe de rotation 14 disposé au niveau des bosses, le rayon RV de la surface de liaison 44 peut varier lorsqu'il parcourt la surface de liaison 44 suivant la direction circonférentielle 15, notamment en se déplaçant d'une aube 26 à sa voisine, soit entre la surface intrados 38 et la surface extrados 40. Bien que seulement deux aubes ne soient représentées, le présent enseignement peut s'appliquer à toute leur rangée annulaire, ou à plusieurs, ou à chaque rangée annulaire d'aubes statoriques du compresseur. De même, la surface de liaison peut être reproduite à l'identique entre chaque aube voisine d'une même rangée. Cela peut former plusieurs rangées annulaires de bosses (54 ; 58) identiques ainsi que plusieurs rangées annulaires de protubérances 52 identiques.The connecting
Claims (15)
- Axial-flow turbomachine compressor (4; 6), in particular a low-pressure compressor (4) of an axial-flow turbomachine (2), the compressor (4; 6) comprising:- an annular row of blades (26), each blade (26) comprising a leading edge (34), a trailing edge (36), a pressure face (38) and a suction face (40) extending from the leading edge (34) to the trailing edge (36),- a between-blades passage (42) with a connecting surface (44) that links the pressure face (38) of a first blade (26) to the suction face (40) of a second blade (26) of the row,the connecting surface (44) comprising:- a main protuberance (52) comprising a first elevation (54) and a second elevation (58), each having a peak (56; 60), respectively a first peak (56) and a second peak (60);- an upstream zone (47) upstream of the protuberance (52) and a downstream zone (49) downstream of the protuberance (52), said zones (47; 49) each being of constant radius RC over the circumference and extending each from the suction face (40) of the first blade (26) to the pressure face (38) of the second blade (26);- a col (66) that links the first elevation (54) and the second elevation (58) and having a curve (67) of a shortest length between the deux peaks (56; 60), all points of the curve (68) being radially more distant from the axis of the compressor (4; 6) than said zones (47; 49) with constant radius RC.
- Compressor (4; 6) according to claim 1, characterized in that the second elevation (58) extends from the suction face (40) of the second blade (26), and the second peak (60) is immediately adjoining said suction face (40).
- Compressor (4; 6) according to one of claims 1 or 2, characterized in that the connecting surface (44) comprises four corners (50) defining a general plane (80), said corners (50) being located at the leading edges (34) and the trailing edges (36) of the blades (26), with the protuberance (52) forming a radial increase in material of the connecting surface (44) compared to said general plane (80).
- Compressor (4; 6) according to one of claims 1 to 3, characterized in that the protuberance (52) extends over a majority of the connecting surface (44).
- Compressor (4; 6) according to one of claims 1 to 4, characterized in that the first elevation (54) and the second elevation (58) are arranged on an upstream half of the protuberance (52) and/or of the blades (26) of the row of blades.
- Compressor (4; 6) according to one of claims 1 to 5, characterized in that the first elevation (54) is radially more developed than the second elevation (58) from the protuberance (52) and/or from the general plane (80) of the connecting surface (44).
- Compressor (4; 6) according to one of claims 1 to 6, characterized in that the first elevation (54) extends from the pressure face (38) of the first blade (26), and said first peak (56) is distant from said pressure face (38).
- Compressor (4; 6) according to one of claims 1 to 7, characterized in that, axially, the length of the first elevation 854) is between 30% and 50% - inclusive - of the length of the first blade (26).
- Compressor (4; 6) according to one of claims 1 to 8, characterized in that, circumferentially, the width of the first elevation (54) is between 40% and 60% - inclusive - of the width of the between-blades passage (42).
- Compressor (4; 6) according to one of claims 1 to 9, characterized in that, axially, the length of the second elevation (58) is between 15% and 25% - inclusive - of the length of the second blade (26).
- Compressor (4; 6) according to one of claims 1 to 10, characterized in that, circumferentially, the width of the second elevation (58) is between 5% and 15% - inclusive - of the width of the between-blades passage (42).
- Compressor (4; 6) according to one of claims 1 to 11, characterized in that the maximum radial height of the first elevation (54) is greater than or equal to three times the maximum radial height of the second elevation (58), and/or greater than or equal to ten times the maximum height of the protuberance (52) measured outside the elevations (54; 58).
- Compressor (4; 6) according to one of claims 1 to 12, characterized in that, over the circumference, the col (66) extends over 40% to 60% - inclusive - of the between-blades passage (42).
- Compressor (4; 6) according to one of claims 1 to 13, characterized in that the peaks (56; 60) are arranges axially at the same level.
- Turbomachine (2), in particular an aircraft jet engine, comprising a compressor (4; 6), characterized in that the compressor is according to one of claims 1-14, the annular row of blades (26) comprising at least: fifty, or eighty blades (26).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
BE2017/5764A BE1025668B1 (en) | 2017-10-26 | 2017-10-26 | DAMPER VIROLET FOR TURBOMACHINE COMPRESSOR |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3477049A1 EP3477049A1 (en) | 2019-05-01 |
EP3477049B1 true EP3477049B1 (en) | 2023-11-22 |
Family
ID=60320604
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP18194178.2A Active EP3477049B1 (en) | 2017-10-26 | 2018-09-13 | Turbine engine compressor with ring comprising elevations |
Country Status (3)
Country | Link |
---|---|
US (1) | US11377960B2 (en) |
EP (1) | EP3477049B1 (en) |
BE (1) | BE1025668B1 (en) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR20190046118A (en) * | 2017-10-25 | 2019-05-07 | 두산중공업 주식회사 | Turbine Blade |
BE1026579B1 (en) * | 2018-08-31 | 2020-03-30 | Safran Aero Boosters Sa | PROTUBERANCE VANE FOR TURBOMACHINE COMPRESSOR |
DE102021109844A1 (en) | 2021-04-19 | 2022-10-20 | MTU Aero Engines AG | Gas Turbine Blade Assembly |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2918254A (en) * | 1954-05-10 | 1959-12-22 | Hausammann Werner | Turborunner |
GB0518628D0 (en) | 2005-09-13 | 2005-10-19 | Rolls Royce Plc | Axial compressor blading |
US8366399B2 (en) * | 2006-05-02 | 2013-02-05 | United Technologies Corporation | Blade or vane with a laterally enlarged base |
US7887297B2 (en) * | 2006-05-02 | 2011-02-15 | United Technologies Corporation | Airfoil array with an endwall protrusion and components of the array |
US8511978B2 (en) * | 2006-05-02 | 2013-08-20 | United Technologies Corporation | Airfoil array with an endwall depression and components of the array |
FR2928173B1 (en) * | 2008-02-28 | 2015-06-26 | Snecma | DAWN WITH 3D PLATFORM COMPRISING A BULB INTERAUBES. |
ES2440563T3 (en) * | 2011-02-08 | 2014-01-29 | MTU Aero Engines AG | Blade channel with side wall contours and corresponding flow apparatus |
US9194235B2 (en) * | 2011-11-25 | 2015-11-24 | Mtu Aero Engines Gmbh | Blading |
EP2696029B1 (en) * | 2012-08-09 | 2015-10-07 | MTU Aero Engines AG | Blade row with side wall contours and fluid flow engine |
DE102015224376A1 (en) * | 2015-12-04 | 2017-06-08 | MTU Aero Engines AG | Bucket channel, blade grid and turbomachine |
DE102016211315A1 (en) * | 2016-06-23 | 2017-12-28 | MTU Aero Engines AG | Runner or vane with raised areas |
EP3388626B1 (en) * | 2017-04-12 | 2019-11-13 | MTU Aero Engines GmbH | Contouring of a blade row platform |
-
2017
- 2017-10-26 BE BE2017/5764A patent/BE1025668B1/en active IP Right Grant
-
2018
- 2018-09-13 EP EP18194178.2A patent/EP3477049B1/en active Active
- 2018-09-27 US US16/143,642 patent/US11377960B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
US11377960B2 (en) | 2022-07-05 |
BE1025668A1 (en) | 2019-05-21 |
EP3477049A1 (en) | 2019-05-01 |
US20190128121A1 (en) | 2019-05-02 |
BE1025668B1 (en) | 2019-05-27 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP3477050B1 (en) | Turbomachine compressor with asymmetricly contoured wall ring | |
EP2977549B1 (en) | Axial turbomachine blading and corresponding turbomachine | |
EP3477049B1 (en) | Turbine engine compressor with ring comprising elevations | |
EP3273003B1 (en) | Vane segment of an axial turbomachine compressor | |
BE1026579B1 (en) | PROTUBERANCE VANE FOR TURBOMACHINE COMPRESSOR | |
EP2801702A1 (en) | Inner shroud of turbomachine with abradable seal | |
EP2977548B1 (en) | Blade and corresponding turbomachine | |
EP3290656B1 (en) | Inner shroud and orientable vane of an axial turbomachine compressor and manufacturing process | |
WO2017017392A1 (en) | Air-flow straightening assembly having improved aerodynamic performances | |
BE1026276B1 (en) | INTER-BLADES OF AXIAL TURBOMACHINE COMPRESSOR | |
BE1026325B1 (en) | RUBBER WITH SCALABLE PROFILING FOR TURBOMACHINE COMPRESSOR | |
EP2721305B1 (en) | Method for diffusing a gas turbine compression stage, and diffusion stage for implementing same | |
EP3477052B1 (en) | Gas turbine engine compressor with a non-axisymmetric profile of an inter-blade surface | |
EP3382155B1 (en) | Sealing system for a turbomachine and corresponding turbomachine | |
EP2977550B1 (en) | Axial turbomachine blade and corresponding turbomachine | |
BE1027709B1 (en) | TURBOMACHINE COMPRESSOR STAGE | |
WO2024033065A1 (en) | Variable vane of an aircraft turbine engine stator, and aircraft turbine engine | |
BE1026006B1 (en) | VARIABLE TIMING AUB SYSTEM FOR TURBOMACHINE COMPRESSOR | |
WO2020039142A1 (en) | Channelling furrow upstream of a blade | |
FR3087828A1 (en) | MOBILE TURBOMACHINE BLADES |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
AX | Request for extension of the european patent |
Extension state: BA ME |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE |
|
17P | Request for examination filed |
Effective date: 20191025 |
|
RBV | Designated contracting states (corrected) |
Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: EXAMINATION IS IN PROGRESS |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: EXAMINATION IS IN PROGRESS |
|
17Q | First examination report despatched |
Effective date: 20210830 |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: GRANT OF PATENT IS INTENDED |
|
INTG | Intention to grant announced |
Effective date: 20230602 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE PATENT HAS BEEN GRANTED |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: EP |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R096 Ref document number: 602018061361 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: FG4D Free format text: LANGUAGE OF EP DOCUMENT: FRENCH |
|
REG | Reference to a national code |
Ref country code: LT Ref legal event code: MG9D |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: MP Effective date: 20231122 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20240223 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20240322 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231122 |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MK05 Ref document number: 1634040 Country of ref document: AT Kind code of ref document: T Effective date: 20231122 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: NL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231122 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: AT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231122 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: ES Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231122 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: NL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231122 Ref country code: LT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231122 Ref country code: IS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20240322 Ref country code: GR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20240223 Ref country code: ES Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231122 Ref country code: BG Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20240222 Ref country code: AT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231122 Ref country code: PT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20240322 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231122 Ref country code: RS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231122 Ref country code: PL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231122 Ref country code: NO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20240222 Ref country code: LV Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231122 Ref country code: HR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231122 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231122 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: CZ Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231122 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231122 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SM Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231122 Ref country code: SK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231122 Ref country code: RO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231122 Ref country code: IT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231122 Ref country code: EE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231122 Ref country code: DK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231122 Ref country code: CZ Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20231122 |