EP2762681B1 - Rotor drum of an axial turbomachine and corresponding turbomachine - Google Patents

Rotor drum of an axial turbomachine and corresponding turbomachine Download PDF

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Publication number
EP2762681B1
EP2762681B1 EP13153799.5A EP13153799A EP2762681B1 EP 2762681 B1 EP2762681 B1 EP 2762681B1 EP 13153799 A EP13153799 A EP 13153799A EP 2762681 B1 EP2762681 B1 EP 2762681B1
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EP
European Patent Office
Prior art keywords
drum
wall
retaining surfaces
annular
accordance
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
Application number
EP13153799.5A
Other languages
German (de)
French (fr)
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EP2762681A1 (en
Inventor
Christophe Remy
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aero Boosters SA
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Safran Aero Boosters SA
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Safran Aero Boosters SA filed Critical Safran Aero Boosters SA
Priority to EP13153799.5A priority Critical patent/EP2762681B1/en
Priority to CA2841344A priority patent/CA2841344A1/en
Priority to RU2014103113A priority patent/RU2651697C2/en
Priority to US14/168,530 priority patent/US9739150B2/en
Priority to CN201410116548.2A priority patent/CN103967840B/en
Publication of EP2762681A1 publication Critical patent/EP2762681A1/en
Application granted granted Critical
Publication of EP2762681B1 publication Critical patent/EP2762681B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/3046—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses the rotor having ribs around the circumference
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/38—Arrangement of components angled, e.g. sweep angle

Definitions

  • the invention relates to an axial compressor bladed drum. More particularly, the invention relates to a drum on which the rotor blades are fixed by engagement with positive contact material. The invention also relates to a turbomachine provided with such a drum.
  • An axial turbomachine compressor advantageously has several compression stages. Each compression stage comprises an annular row of rotor vanes and an annular row of stator vanes.
  • a compressor rotor can be formed of a drum with an axially symmetrical wall, which allows for a lightweight and economical monoblock element.
  • a drum has a generally thin annular wall, on which the rotor blades are directly fixed.
  • the blades can be welded into openings in the drum wall.
  • the blade roots can also be inserted in axial grooves formed on the drum.
  • the drum may be provided with annular cavities inside which fixing surfaces are provided.
  • the rotor blades have corresponding attachment surfaces that allow them to be anchored in the cells.
  • the document EP 2 075 417 A1 discloses an axial turbomachine compressor rotor drum.
  • the drum has a symmetrical wall and annular cells. These are open radially outward and have a narrowing in the same direction. Blades are fixed inside these annular cells. They have for this purpose feet having profiles complementary to the cells and are inserted therein. They are thus retained radially.
  • the existence of the cell requires a large mass of material that weighs down the drum. This material also represents a cost.
  • an annular cell forms a discontinuity of material in the wall of the drum since it extends radially at height of the wall of the drum. It reduces its rigidity, which results in an increase in deformations during operation of the turbomachine.
  • the document EP 1 406 019 A1 also discloses a turbomachine rotor drum having a machined groove and blade retention surfaces, in accordance with the preambles of claims 1 and 3.
  • the document EP 0422433 A1 discloses a turbomachine rotor disk having a bearing rib projecting from the outer radial surface of the disk and having blade retention surfaces.
  • the invention aims to solve at least one of the problems raised by the prior art.
  • the invention also aims to facilitate the machining of the mounting surfaces of the drum.
  • the invention also aims to lighten an axial compressor bladed drum.
  • the invention also aims to stiffen an axial compressor bladed drum.
  • the invention relates to an axial turbomachine rotor drum according to claims 1 and 3.
  • the drum may be free of disks or annular disks.
  • the profile of each of the two retention surfaces forms an average angle of between 30 ° and 60 ° with the axis of rotation and / or the profiles of said surfaces form between them an average angle between 60 ° and 120 °.
  • the wall forms the drum structure, preferably from its front end to its rear end.
  • the wall of the drum has one or more annular ribs upstream and downstream, respectively, of the two retention surfaces, said ribs being configured to cooperate by abrasion with annular layers of abradable material, the wall extending substantially rectilinearly along the two retention surfaces, between said upstream and downstream ribs.
  • the two retention surfaces are generally radially raised relative to the adjacent wall.
  • the radial height of the retention surfaces represents between 1% and 10% of the average radius of the wall of the drum where they are arranged, preferably between 1% and 5%, more preferably between 1% and 3%.
  • This feature of the invention aims to reduce the radial size of the fastening surfaces and the fastening lugs and the annular body or collars.
  • a segment of the two annular retention surfaces comprises a blade mounting notch on only one of the two surfaces, so as to allow the blades to be fitted by an engagement movement with the retention surface. without notch, followed by a tilt penetrating the platform into the notch.
  • the two flanges are implanted on the wall, at a distance from one another, said distance being preferably greater than 10 mm.
  • the annular body may generally have a trapezoid profile whose parallel sides generally extend along the axis of rotation of the rotor, the smallest of these sides being arranged inwardly.
  • the annular body comprises a radially outwardly open annular groove configured to receive a preferably toric seal intended to be pressed against the platforms of the blades under the effect of the centrifugal force during the rotation. drum.
  • the drum comprises the row of blades, said blades each comprising a platform provided with two bearing surfaces configured to cooperate with the retaining surfaces on the wall.
  • the platform of the blades comprises a cavity open towards the wall of the drum and forming the bearing surfaces, the bottom of the cavity forming a radial bearing surface directed towards the inside of the drum.
  • the two contact surfaces of the blade platforms are situated essentially at the right of the leading and trailing edges, respectively, of the blades.
  • the subject of the invention is a turbomachine comprising a turbine or compressor rotor, preferably a low-pressure rotor, which is remarkable in that the rotor comprises a drum according to the invention, and preferably in that the drum comprises several sets of retention surfaces. each game corresponding to a row of blades.
  • the invention makes it possible to simplify the machining of a turbomachine drum.
  • the clearance around the retention surfaces is increased, which simplifies the corresponding manufacturing or metrology operations.
  • the invention allows positioning on the same side of the wall functional elements such as retention surfaces and wipers.
  • the volume to be machined inside is reduced.
  • This configuration provides a smooth interior surface, which facilitates the integration of interior supports to resume cutting efforts.
  • the invention makes it possible to stiffen the drum.
  • the profile of its wall has continuity of curvature and limits the changes of radii.
  • the variations in thickness of the profile are limited, which improves the longevity of the drum.
  • the invention also makes it possible to improve the fastening stability of the vanes on the rotor. Indeed, it comes into contact with surfaces that can more easily be extended or removed from each other, without increasing the amount of material needed to obtain the drum, or without weighing it down.
  • inner and outer refer to a positioning relative to the axis of rotation of the turbomachine.
  • the figure 1 illustrates an axial turbomachine. It is in this case a double-flow turbojet engine.
  • the turbojet engine 2 comprises a first compression level, called a low-pressure compressor 4, a second compression level, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10.
  • a first compression level called a low-pressure compressor 4
  • a second compression level called a high-pressure compressor 6
  • a combustion chamber 8 and one or more levels of turbines 10.
  • Reducing means can increase the speed of rotation transmitted to the compressors.
  • the different turbine stages can each be connected to the compressor stages via concentric shafts.
  • the compressor comprises several rows of rotor blades associated with rows of stator vanes. The rotation of the rotor 12 around its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until it reaches the combustion chamber 10.
  • a commonly designated fan inlet fan 16 is coupled to the rotor 12 and generates a flow of air which is divided into a primary flow 18 passing through the various levels mentioned above of the turbomachine, and a secondary flow 20 passing through an annular duct (partially shown) along the machine to then join the primary flow at the turbine outlet.
  • the primary 18 and secondary 20 streams are annular flows, they are channeled by the casing of the turbomachine.
  • the casing has cylindrical walls or ferrules which can be internal and external.
  • the figure 2 is a sectional view of a low-pressure compressor 4 of an axial turbomachine 2 such as that of the figure 1 . It is possible to observe a portion of the fan 16 and the separation nozzle 22 of the primary flow 18 and the secondary flow 20.
  • the rotor 12 comprises several rows of rotor blades 24, in the specific case of the figure 2 three rows are planned.
  • the low-pressure compressor 4 comprises a plurality of rectifiers, for example 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 24 for straightening the air flow, so as to convert the speed of the flow into pressure.
  • the rotor vanes 24 extend substantially radially from the rotor 12. They are regularly spaced from each other, and have the same angular orientation in the flow. Advantageously, these rotor vanes 24 are identical. Optionally, the spacing between the vanes may vary locally, as can their angular orientation. Some blades may be different from the rest of the blades in the row.
  • the rotor 12 comprises a drum 28.
  • the drum 28 has a wall 30 with a profile of revolution about the axis of rotation 14.
  • the profile of revolution of the wall may have a generally continuous curvature. It radially follows the section variation of the inner surface of the primary flow.
  • the wall 30 is essentially thin. Its thickness is generally constant. Its thickness is less than 10.00 mm, preferably less than 5.00 mm, more preferably less than 2.00 mm.
  • the wall 30 forms a hollow body which delimits a hollow space, having a cylinder or ogive shape.
  • the drum 28 and / or the rotor blades 24 are made of metal materials, preferably titanium. They are each from matter.
  • the drum 28 comprises annular ribs 32 or wipers. They form annular lamellae which extend radially. They are intended to cooperate by abrasion with annular layers of abradable material so as to ensure a seal. Generally, a single layer of abradable cooperates with two ribs 32.
  • the rotor 12 can deform. It may, for example, expand or increase in diameter under the effect of centrifugal force. These deformations can be observed on the wall 30.
  • the rotor 12 has annular retention surfaces.
  • the rotor vanes 24 comprise corresponding retention surfaces which cooperate with the retaining surfaces of the drum, making it possible to fasten the rotor blades thereon.
  • the rotor blades 24 have lower platforms 34 arranged opposite the rotor 12. The attachment surfaces are arranged between the rotor 12 and the lower platforms 34.
  • the figure 3 represents a drum according to a first embodiment of the invention.
  • the drum 28 comprises on its outer surface an annular body 36.
  • the latter has a general trapezoidal profile whose parallel edges are substantially parallel to the axis of rotation 14, the two other inclined sides extending essentially radially.
  • the inclined sides of the trapezoidal profile generate by rotation about the axis of rotation 14 a set of two annular retention surfaces 38.
  • the drum 28 may have several sets of such retention surfaces. Each set of retention surfaces 38 is separated from the other sets by ribs 32.
  • the radial thickness of the annular body 36 is greater than 5.00 mm, preferably greater than 10.00 mm, more preferably greater than 20.00 mm.
  • the annular body 36 forms an outer ring which makes it possible to reinforce and stiffen the drum 28. It makes it possible to reduce the deformations of the drum 28 related to the centrifugal force.
  • the annular body 36 makes it possible to replace the inner annular reinforcements of the drum or "leeks".
  • a drum is generally machined by turning from a drum-shaped machining blank whose walls encompass the finished drum. The crude must embrace the surfaces radially retentions and leeks. The set requires to perform important machining. Since the annular body 36 is located on the same side as the retention surfaces 38, the machining stock can be thinned and the corresponding machining reduced.
  • the rotor blade 24 comprises attachment lugs 40 extending radially and axially beneath its lower platform 28.
  • the attachment lugs 40 are inclined towards each other.
  • the corresponding retention surfaces 42 are implanted on the inner surfaces of the fastening tabs 40.
  • the corresponding retention surfaces 42 are opposite one another.
  • the retention surfaces 38 and the corresponding retention surfaces 42 are complementary. They marry on most of their expanses. They can be frustoconical. They are configured to cooperate by engagement of material so as to fix the rotor blade 24 on the drum 28. They form a dovetail type fastener.
  • the flared section of the corresponding retention surfaces 42, together with the narrowed section defined by the retaining surfaces 38 of the drum allow radial retention of the vane 24 towards the drum 28.
  • the revolution profiles of the retention surfaces 38 and 42 are inclined relative to the perpendicular 44 to the axis of rotation 14 by an angle ⁇ , which is between 10 ° and 80 °, preferably between 30 ° and 60 ° included.
  • the profiles of the retention surfaces 38 and 42 are inclined relative to each other by an angle ⁇ .
  • the angle ⁇ is between 60 ° and 120 °. The greater the angle ⁇ , the less the centrifugal force tends to move the fastening tabs 40 during operation of the turbomachine.
  • the retention surfaces 38 are substantially in radial elevation with respect to the wall 30 of the drum 28.
  • the wipers 32 are axially spaced therefrom.
  • the drum 28 is free axially surface capable of forming an obstacle to the retention surfaces 38 to more than 5.00 mm, preferably to more than 15.00 mm, more preferably to more than 30.00 mm.
  • the retention surfaces 38 are therefore easily accessible for machining, for example to achieve a blank and a finish.
  • the wall 30 of the drum 28 can extend substantially rectilinearly at the retention surfaces 38, preferably between the ribs 32 arranged upstream and downstream. This feature makes it possible to preserve the rigidity of the drum 28. In particular, it is more resistant to axial compression. One consequence is that its wall 30 can be thinned.
  • the profile of the inner surface of the wall 30 may be generally straight or substantially curved. This aspect reduces the stress concentrations and improves the life of the drum.
  • the annular body 36 has an annular groove open radially outwardly.
  • the rotor 12 comprises an O-ring 48 housed inside this annular groove.
  • the inner radius of the O-ring 48 is less than or equal to the radius of the bottom of the groove, the radii being measured from the axis of rotation 14.
  • the O-ring 48 is essentially elastic. Under the effect of the centrifugal force that appears during the operation of the turbomachine, the O-ring 48 is pressed against the inner surface of the lower platform 34 of the rotor blade 24. It thus ensures a seal between the upstream and downstream sides. of dawn 24.
  • the annular body 36 comprises radial bearing surfaces 50 arranged upstream and downstream. They can be essentially cylindrical and are oriented radially outwards.
  • the rotor blade 24 has corresponding bearing surfaces 52 which are able to cooperate with the bearing surfaces 50 of the drum.
  • the bearing surfaces 52 are arranged facing the bearing surfaces 50 of the drum.
  • these surfaces 50 and 52 are spaced apart from each other. Centrifugal force keeps them at bay. They are able to come into contact with one another or at least to be adjacent in the event of a change in the operating condition of the turbomachine.
  • These surfaces 50 and 52 make it possible to reduce or block the downstream upstream tilting of the vanes 24 with respect to the drum 28, this phenomenon being known by the term "rocking".
  • the figure 4 represents the annular body 36 of the drum 28 seen radially from the outside.
  • a rotor blade 24 is mounted therein by means of its fixing lugs 40.
  • the annular body 36 has at least one axial notch 53 at one of the retention surfaces, in order to be able to fit the rotor blades 24.
  • a latch (not shown) or several locks can close the notch 53 and can serve to tangentially block the blades 24.
  • the locks can overlap the annular body 36 or cross axially.
  • the figure 5 illustrates a section of the drum according to the first embodiment of the invention, the section being taken along the axis 5-5 traced on the figure 4 .
  • a segment or section of the two annular retention surfaces may comprise a single mounting notch 53 of the vanes on only one of the two retention surfaces 38, so as to allow the vanes 24 to be mounted by a movement of engagement with the retention surface without notch, vis-à-vis the notch 53, followed by a tilt partially penetrating the bracket 40 of the platform 34 in the notch 53.
  • the blade 24 can then be slid in the circumferential direction of the drum, so that its fixing lugs 40 are no longer at the level of the notch (s) 53.
  • the figure 6 represents a rotor according to a second embodiment of the invention. This figure 6 resumes the numbering of the preceding figures for identical or similar elements, however the number is incremented by 100. Furthermore, reference is made in particular to the description of the preceding figures for their similar or equivalent elements. Specific numbers are used for the specific elements of this embodiment.
  • the drum 128 comprises two annular flanges 154.
  • the flanges 154 are inclined, preferably relative to one another. They move away from each other to the outside. Their profiles have an average length and width. The length is greater than three times the average width, preferably greater than five times.
  • the junctions of the collars 154 to the wall 130 may be distant from each other. the other.
  • the axial distance between the retention surfaces measured at the junction with the outer surface of the wall 130 is greater than the average length of the profile of the flanges 154, preferably greater than 1.5 times, more preferably greater than twice.
  • the wall 130 may be locally thickened between the flanges 154 so as to strengthen it.
  • This configuration makes it possible to axially separate the retention surfaces 138 from each other without making the drum 128 heavier.
  • the stability of the blade 124 on the drum is improved.
  • the inclination angles of the profiles of the retention surfaces 138 and 142 can be chosen with greater freedom.
  • the collars 154 define between them an annular space 156.
  • One of them may have a thickening so as to receive an annular groove and an O-ring capable of sealing against the platform of the rotor blade 124.
  • the collars 154 help to stiffen the drum in the manner of strapping.

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  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
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Description

Domaine techniqueTechnical area

L'invention a trait à un tambour aubagé de compresseur axial. Plus particulièrement, l'invention a trait à un tambour sur lequel les aubes rotoriques sont fixées par engagement à contact positif de matière. L'invention a également trait à une turbomachine munie d'un tel tambour.The invention relates to an axial compressor bladed drum. More particularly, the invention relates to a drum on which the rotor blades are fixed by engagement with positive contact material. The invention also relates to a turbomachine provided with such a drum.

Technique antérieurePrior art

Un compresseur de turbomachine axiale présente avantageusement plusieurs étages de compression. Chaque étage de compression comprend une rangée annulaire d'aubes rotoriques et une rangée annulaire d'aubes statoriques. Un rotor de compresseur peut être formé d'un tambour avec une paroi symétrique axialement, ce qui permet de réaliser un élément monobloc léger et économique.An axial turbomachine compressor advantageously has several compression stages. Each compression stage comprises an annular row of rotor vanes and an annular row of stator vanes. A compressor rotor can be formed of a drum with an axially symmetrical wall, which allows for a lightweight and economical monoblock element.

Un tambour présente une paroi annulaire généralement fine, sur laquelle sont fixées directement les aubes rotoriques. Pour cela plusieurs solutions sont possibles. Les aubes peuvent êtres soudées dans des ouvertures ménagées dans la paroi du tambour. Les pieds des aubes peuvent aussi être insérés dans des gorges axiales formées sur le tambour.A drum has a generally thin annular wall, on which the rotor blades are directly fixed. For this, several solutions are possible. The blades can be welded into openings in the drum wall. The blade roots can also be inserted in axial grooves formed on the drum.

Suivant une alternative, le tambour peut être muni d'alvéoles annulaires à l'intérieur desquelles sont prévues des surfaces de fixation. Les aubes rotoriques présentent des surfaces de fixation correspondantes qui permettent de les ancrer dans les alvéoles.According to an alternative, the drum may be provided with annular cavities inside which fixing surfaces are provided. The rotor blades have corresponding attachment surfaces that allow them to be anchored in the cells.

Le document EP 2 075 417 A1 divulgue un tambour de rotor de compresseur de turbomachine axiale. Le tambour comporte une paroi symétrique et des alvéoles annulaires. Celle-ci sont ouvertes radialement vers l'extérieur et présentent un rétrécissement dans cette même direction. Des aubes sont fixées à l'intérieur de ces alvéoles annulaires. Elles présentent à cet effet des pieds présentant des profils complémentaires aux alvéoles et y sont insérés. Elles y sont ainsi retenues radialement. L'existence de l'alvéole nécessite une masse importante de matière qui alourdit le tambour. Cette matière représente également un coût. De plus, une alvéole annulaire forme une discontinuité de matière dans la paroi du tambour puisqu'elle s'étend radialement à hauteur de la paroi du tambour. Elle en réduit la rigidité, ce qui se traduit par une augmentation des déformations lors du fonctionnement de la turbomachine. En raison de la force centrifuge, les pieds des aubes sont tirés vers l'extérieur. En raison de leurs formes et de leurs configurations, ils tendent à écarter les bords intérieurs des alvéoles annulaires, ce qui déforme encore le tambour. Chaque alvéole annulaire présente des surfaces de fixation qui doivent être usinées. En raison du caractère fermé des alvéoles, les surfaces de fixation sont peu accessibles, ce qui en complique l'usinage. Le document EP 1 406 019 A1 divulgue également un tambour de rotor de turbomachine présentant une gorge usinée et des surfaces de rétention d'aubes, conformément aux préambules des revendications 1 et 3. En outre, le document EP 0422433 A1 divulgue un disque de rotor de turbomachine ayant une nervure portante faisant saillie de la surface radiale externe du disque et présentant des surfaces de rétention d'aubes.The document EP 2 075 417 A1 discloses an axial turbomachine compressor rotor drum. The drum has a symmetrical wall and annular cells. These are open radially outward and have a narrowing in the same direction. Blades are fixed inside these annular cells. They have for this purpose feet having profiles complementary to the cells and are inserted therein. They are thus retained radially. The existence of the cell requires a large mass of material that weighs down the drum. This material also represents a cost. In addition, an annular cell forms a discontinuity of material in the wall of the drum since it extends radially at height of the wall of the drum. It reduces its rigidity, which results in an increase in deformations during operation of the turbomachine. Due to the centrifugal force, the blade roots are pulled out. Because of their shapes and configurations, they tend to spread the inner edges of the annular cells, which further deforms the drum. Each annular recess has attachment surfaces that must be machined. Due to the closed nature of the cells, the attachment surfaces are not very accessible, which complicates the machining. The document EP 1 406 019 A1 also discloses a turbomachine rotor drum having a machined groove and blade retention surfaces, in accordance with the preambles of claims 1 and 3. In addition, the document EP 0422433 A1 discloses a turbomachine rotor disk having a bearing rib projecting from the outer radial surface of the disk and having blade retention surfaces.

Résumé de l'inventionSummary of the invention Problème techniqueTechnical problem

L'invention a pour objectif de résoudre au moins un des problèmes soulevés par l'art antérieur. L'invention a également pour objectif de faciliter l'usinage des surfaces de fixation du tambour. L'invention a également pour objectif d'alléger un tambour aubagé de compresseur axial. L'invention a également pour objectif de rigidifier un tambour aubagé de compresseur axial.The invention aims to solve at least one of the problems raised by the prior art. The invention also aims to facilitate the machining of the mounting surfaces of the drum. The invention also aims to lighten an axial compressor bladed drum. The invention also aims to stiffen an axial compressor bladed drum.

Solution techniqueTechnical solution

L'invention a trait à un tambour de rotor de turbomachine axiale selon les revendications 1 et 3.The invention relates to an axial turbomachine rotor drum according to claims 1 and 3.

Le tambour peut être libre de disques ou de disques annulaires.The drum may be free of disks or annular disks.

Selon un mode avantageux de l'invention, le profil de chacune des deux surfaces de rétention forme un angle moyen compris entre 30° et 60° avec l'axe de rotation et/ou les profils desdits surfaces forment entre eux un angle moyen compris entre 60° et 120°.According to an advantageous embodiment of the invention, the profile of each of the two retention surfaces forms an average angle of between 30 ° and 60 ° with the axis of rotation and / or the profiles of said surfaces form between them an average angle between 60 ° and 120 °.

Selon un mode avantageux de l'invention, la paroi forme la structure du tambour, préférentiellement depuis son extrémité avant jusqu'à son extrémité arrière.According to an advantageous embodiment of the invention, the wall forms the drum structure, preferably from its front end to its rear end.

Selon un mode avantageux de l'invention, la paroi du tambour présente une ou plusieurs nervures annulaires en amont et en aval, respectivement, des deux surfaces de rétention, lesdites nervures étant configurées pour coopérer par abrasion avec des couches annulaires de matériau abradable, la paroi s'étendant de manière essentiellement rectiligne le long des deux surfaces de rétention, entre lesdites nervures amont et aval.According to an advantageous embodiment of the invention, the wall of the drum has one or more annular ribs upstream and downstream, respectively, of the two retention surfaces, said ribs being configured to cooperate by abrasion with annular layers of abradable material, the wall extending substantially rectilinearly along the two retention surfaces, between said upstream and downstream ribs.

Selon un mode avantageux de l'invention, les deux surfaces de rétention sont généralement radialement surélevées par rapport à la paroi adjacente.According to an advantageous embodiment of the invention, the two retention surfaces are generally radially raised relative to the adjacent wall.

La hauteur radiale des surfaces de rétention représente entre 1% et 10% du rayon moyen de la paroi du tambour là où elles sont disposées, préférentiellement entre 1% et 5%, plus préférentiellement entre 1% et 3%. Cette particularité de l'invention vise à réduire l'encombrement radial des surfaces de fixation et des pattes de fixation et du corps annulaire ou des collerettes associés.The radial height of the retention surfaces represents between 1% and 10% of the average radius of the wall of the drum where they are arranged, preferably between 1% and 5%, more preferably between 1% and 3%. This feature of the invention aims to reduce the radial size of the fastening surfaces and the fastening lugs and the annular body or collars.

Selon un mode avantageux de l'invention, un segment des deux surfaces annulaires de rétention comprend une encoche de montage des aubes sur une seule des deux surfaces, de manière à permettre le montage des aubes par un mouvement d'engagement avec la surface de rétention sans encoche, suivi d'un basculement faisant pénétrer la plateforme dans l'encoche.According to an advantageous embodiment of the invention, a segment of the two annular retention surfaces comprises a blade mounting notch on only one of the two surfaces, so as to allow the blades to be fitted by an engagement movement with the retention surface. without notch, followed by a tilt penetrating the platform into the notch.

Selon un mode avantageux de l'invention, les deux collerettes sont implantées sur la paroi, à distance l'une de l'autre, ladite distance étant préférentiellement supérieure à 10mm.According to an advantageous embodiment of the invention, the two flanges are implanted on the wall, at a distance from one another, said distance being preferably greater than 10 mm.

Le corps annulaire peut présenter généralement un profil de trapèze dont les côtés parallèles s'étendent généralement selon l'axe de rotation du rotor, le plus petit de ces côtés étant disposé vers l'intérieur.The annular body may generally have a trapezoid profile whose parallel sides generally extend along the axis of rotation of the rotor, the smallest of these sides being arranged inwardly.

Selon un mode avantageux de l'invention, le corps annulaire comprend une gorge annulaire ouverte radialement vers l'extérieur configurée pour recevoir un joint préférentiellement torique destiné à être plaqué contre les plateformes des aubes sous l'effet de la force centrifuge lors de la rotation du tambour.According to an advantageous embodiment of the invention, the annular body comprises a radially outwardly open annular groove configured to receive a preferably toric seal intended to be pressed against the platforms of the blades under the effect of the centrifugal force during the rotation. drum.

Selon un mode avantageux de l'invention, le tambour comprend la rangée d'aubes, lesdites aubes comprenant, chacune, une plateforme pourvue des deux surfaces d'appui configurées pour coopérer avec les surfaces de rétention sur la paroi.According to an advantageous embodiment of the invention, the drum comprises the row of blades, said blades each comprising a platform provided with two bearing surfaces configured to cooperate with the retaining surfaces on the wall.

Selon un mode avantageux de l'invention, la plateforme des aubes comprend une cavité ouverte vers la paroi du tambour et formant les surfaces d'appui, le fond de la cavité formant une surface d'appui radial dirigée vers l'intérieur du tambour.According to an advantageous embodiment of the invention, the platform of the blades comprises a cavity open towards the wall of the drum and forming the bearing surfaces, the bottom of the cavity forming a radial bearing surface directed towards the inside of the drum.

Selon un mode avantageux de l'invention, les deux surfaces de contact des plateformes des aubes sont situées essentiellement au droit des bords d'attaque et de fuite, respectivement, des aubes.According to an advantageous embodiment of the invention, the two contact surfaces of the blade platforms are situated essentially at the right of the leading and trailing edges, respectively, of the blades.

L'invention a pour objet une turbomachine comprenant un rotor de turbine ou de compresseur, préférentiellement basse pression, remarquable en ce que le rotor comprend un tambour conforme à l'invention, et préférentiellement en ce que le tambour comprend plusieurs jeux de surfaces de rétention, chaque jeu correspondant à une rangée d'aubes.The subject of the invention is a turbomachine comprising a turbine or compressor rotor, preferably a low-pressure rotor, which is remarkable in that the rotor comprises a drum according to the invention, and preferably in that the drum comprises several sets of retention surfaces. each game corresponding to a row of blades.

Avantages apportésBenefits brought

L'invention permet de simplifier l'usinage d'un tambour de turbomachine. Le dégagement autour des surfaces de rétention est augmenté, ce qui simplifie les opérations de fabrication ou de métrologie correspondantes.The invention makes it possible to simplify the machining of a turbomachine drum. The clearance around the retention surfaces is increased, which simplifies the corresponding manufacturing or metrology operations.

L'invention permet de positionner d'un même côté de la paroi les éléments fonctionnels comme les surfaces de rétention et les léchettes. Lorsque le tambour est usiné à partir d'un brut épais, le volume à usiner à l'intérieur est réduit. Cette configuration offre une surface intérieure lisse, qui facilite l'intégration de supports intérieurs pour reprendre les efforts de coupe.The invention allows positioning on the same side of the wall functional elements such as retention surfaces and wipers. When the drum is machined from a thick stock, the volume to be machined inside is reduced. This configuration provides a smooth interior surface, which facilitates the integration of interior supports to resume cutting efforts.

L'invention permet de rigidifier le tambour. Le profil de sa paroi présente une continuité de courbure et limite les changements de rayons. Les variations d'épaisseurs du profil sont limitées, ce qui améliore la longévité du tambour.The invention makes it possible to stiffen the drum. The profile of its wall has continuity of curvature and limits the changes of radii. The variations in thickness of the profile are limited, which improves the longevity of the drum.

L'invention permet également d'améliorer la stabilité de fixation des aubes sur le rotor. En effet, elle viennent en contact de surfaces qui peuvent plus facilement être étendues ou éloignées les unes des autres, et ce sans augmenter la quantité de matière nécessaire pour obtenir le tambour, ou sans l'alourdir.The invention also makes it possible to improve the fastening stability of the vanes on the rotor. Indeed, it comes into contact with surfaces that can more easily be extended or removed from each other, without increasing the amount of material needed to obtain the drum, or without weighing it down.

Brève description des dessinsBrief description of the drawings

  • La figure 1 représente une turbomachine axiale selon l'invention.The figure 1 represents an axial turbomachine according to the invention.
  • La figure 2 est une vue en coupe d'un compresseur de turbomachine selon l'invention.The figure 2 is a sectional view of a turbomachine compressor according to the invention.
  • La figure 3 illustre un tambour selon un premier mode de réalisation de l'invention.The figure 3 illustrates a drum according to a first embodiment of the invention.
  • La figure 4 illustre un tambour selon le premier mode de réalisation de l'invention vu radialement depuis le dessus.The figure 4 illustrates a drum according to the first embodiment of the invention seen radially from above.
  • La figure 5 illustre le tambour selon le premier mode de réalisation de l'invention suivant l'axe 5-5 tracé sur la figure 4.The figure 5 illustrates the drum according to the first embodiment of the invention along the axis 5-5 drawn on the figure 4 .
  • La figure 6 illustre un tambour selon un deuxième mode de réalisation de l'invention.The figure 6 illustrates a drum according to a second embodiment of the invention.
Description des modes de réalisationDescription of the embodiments

Dans la description qui va suivre, les termes intérieur et extérieur renvoient à un positionnement par rapport à l'axe de rotation de la turbomachine.In the following description, the terms inner and outer refer to a positioning relative to the axis of rotation of the turbomachine.

La figure 1 illustre une turbomachine axiale. Il s'agit dans ce cas précis d'un turboréacteur double-flux. Le turboréacteur 2 comprend un premier niveau de compression, dit compresseur basse-pression 4, un deuxième niveau de compression, dit compresseur haute-pression 6, une chambre de combustion 8 et un ou plusieurs niveaux de turbines 10. En fonctionnement, la puissance mécanique de la turbine 10 transmise via l'arbre central jusqu'au rotor 12 met en mouvement les deux compresseurs 4 et 6. Des moyens de démultiplication peuvent augmenter la vitesse de rotation transmise aux compresseurs. Ou encore, les différents étages de turbines peuvent chacun être reliés aux étages de compresseur via des arbres concentriques. Le compresseur comporte plusieurs rangées d'aubes rotoriques associées à des rangées d'aubes statoriques. La rotation du rotor 12 autour de son axe de rotation 14 permet ainsi de générer un débit d'air et de comprimer progressivement ce dernier jusqu'à l'entrée de la chambre de combustion 10.The figure 1 illustrates an axial turbomachine. It is in this case a double-flow turbojet engine. The turbojet engine 2 comprises a first compression level, called a low-pressure compressor 4, a second compression level, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10. In operation, the mechanical power the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6. Reducing means can increase the speed of rotation transmitted to the compressors. Or, the different turbine stages can each be connected to the compressor stages via concentric shafts. The compressor comprises several rows of rotor blades associated with rows of stator vanes. The rotation of the rotor 12 around its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until it reaches the combustion chamber 10.

Un ventilateur d'entrée communément désigné fan 16 est couplé au rotor 12 et génère un flux d'air qui se divise en un flux primaire 18 traversant les différents niveaux sus mentionnés de la turbomachine, et un flux secondaire 20 traversant un conduit annulaire (partiellement représenté) le long de la machine pour ensuite rejoindre le flux primaire en sortie de turbine. Les flux primaire 18 et secondaire 20 sont des flux annulaires, ils sont canalisés par le carter de la turbomachine. A cet effet, le carter présente des parois cylindriques ou viroles qui peuvent être internes et externes.A commonly designated fan inlet fan 16 is coupled to the rotor 12 and generates a flow of air which is divided into a primary flow 18 passing through the various levels mentioned above of the turbomachine, and a secondary flow 20 passing through an annular duct (partially shown) along the machine to then join the primary flow at the turbine outlet. The primary 18 and secondary 20 streams are annular flows, they are channeled by the casing of the turbomachine. For this purpose, the casing has cylindrical walls or ferrules which can be internal and external.

La figure 2 est une vue en coupe d'un compresseur basse-pression 4 d'une turbomachine axiale 2 telle que celle de la figure 1. On peut y observer une partie du fan 16 et le bec de séparation 22 du flux primaire 18 et du flux secondaire 20. Le rotor 12 comprend plusieurs rangées d'aubes rotoriques 24, dans le cas précis de la figure 2, trois rangées sont prévues.The figure 2 is a sectional view of a low-pressure compressor 4 of an axial turbomachine 2 such as that of the figure 1 . It is possible to observe a portion of the fan 16 and the separation nozzle 22 of the primary flow 18 and the secondary flow 20. The rotor 12 comprises several rows of rotor blades 24, in the specific case of the figure 2 three rows are planned.

Le compresseur basse pression 4 comprend plusieurs redresseurs, par exemple quatre, qui contiennent, chacun, une rangée d'aubes statoriques 26. Les redresseurs sont associés au fan 16 ou à une rangée d'aubes rotoriques 24 pour redresser le flux d'air, de sorte à convertir la vitesse du flux en pression.The low-pressure compressor 4 comprises a plurality of rectifiers, for example 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 24 for straightening the air flow, so as to convert the speed of the flow into pressure.

Les aubes rotoriques 24 s'étendent essentiellement radialement depuis le rotor 12. Elles sont régulièrement espacés les unes des autres, et présentent une même orientation angulaire dans le flux. Avantageusemsent, ces aubes rotoriques 24 sont identiques. Eventuellement, l'espacement entre les aubes peut varier localement, tout comme leur orientation angulaire. Certaines aubes peuvent être différentes du reste des aubes de la rangée.The rotor vanes 24 extend substantially radially from the rotor 12. They are regularly spaced from each other, and have the same angular orientation in the flow. Advantageously, these rotor vanes 24 are identical. Optionally, the spacing between the vanes may vary locally, as can their angular orientation. Some blades may be different from the rest of the blades in the row.

Le rotor 12 comprend un tambour 28. Le tambour 28 comporte une paroi 30 avec un profil de révolution autour de l'axe de rotation 14. Le profil de révolution de la paroi peut présenter une courbure généralement continue. Il suit radialement la variation de section de la surface intérieur du flux primaire. La paroi 30 est essentiellement fine. Son épaisseur est généralement constante. Son épaisseur est inférieure à 10,00 mm, préférentiellement inférieure à 5,00 mm, plus préférentiellement inférieure à 2,00 mm. La paroi 30 forme un corps creux qui délimite un espace creux, ayant une forme de cylindre ou d'ogive. Le tambour 28 et/ou les aubes rotoriques 24 sont réalisés en matériaux métalliques, préférentiellement en titane. Ils sont chacun venus de matière.The rotor 12 comprises a drum 28. The drum 28 has a wall 30 with a profile of revolution about the axis of rotation 14. The profile of revolution of the wall may have a generally continuous curvature. It radially follows the section variation of the inner surface of the primary flow. The wall 30 is essentially thin. Its thickness is generally constant. Its thickness is less than 10.00 mm, preferably less than 5.00 mm, more preferably less than 2.00 mm. The wall 30 forms a hollow body which delimits a hollow space, having a cylinder or ogive shape. The drum 28 and / or the rotor blades 24 are made of metal materials, preferably titanium. They are each from matter.

Le tambour 28 comprend des nervures annulaires 32 ou léchettes. Elles forment des lamelles annulaires qui s'étendent radialement. Elles sont destinées à coopérer par abrasion avec des couches annulaires de matériau abradable de sorte à assurer une étanchéité. Généralement, une même couche d'abradable coopère avec deux nervures 32. Lors du fonctionnement du compresseur, le rotor 12 peut se déformer. Il peut, par exemple, se dilater ou augmenter de diamètre sous l'effet de la force centrifuge. Ces déformations peuvent s'observer sur la paroi 30.The drum 28 comprises annular ribs 32 or wipers. They form annular lamellae which extend radially. They are intended to cooperate by abrasion with annular layers of abradable material so as to ensure a seal. Generally, a single layer of abradable cooperates with two ribs 32. During operation of the compressor, the rotor 12 can deform. It may, for example, expand or increase in diameter under the effect of centrifugal force. These deformations can be observed on the wall 30.

Le rotor 12 comporte des surfaces de rétention annulaires. Les aubes rotoriques 24 comprennent des surfaces de rétention correspondantes qui coopèrent avec les surfaces de rétention du tambour, permettant d'y fixer les aubes rotoriques. Les aubes rotoriques 24 présentent des plateformes inférieures 34, disposées en regard du rotor 12. Les surfaces de fixation sont disposées entre le rotor 12 et les plateformes inférieures 34.The rotor 12 has annular retention surfaces. The rotor vanes 24 comprise corresponding retention surfaces which cooperate with the retaining surfaces of the drum, making it possible to fasten the rotor blades thereon. The rotor blades 24 have lower platforms 34 arranged opposite the rotor 12. The attachment surfaces are arranged between the rotor 12 and the lower platforms 34.

La figure 3 représente un tambour selon un premier mode de réalisation de l'invention.The figure 3 represents a drum according to a first embodiment of the invention.

Le tambour 28 comprend sur sa surface extérieure un corps annulaire 36. Ce dernier présente un profil général de trapèze dont les bords parallèles sont sensiblement parallèles à l'axe de rotation 14, les deux autres côtés inclinés s'étendant essentiellement radialement. Les côtés inclinés du profil du trapèze génèrent par rotation autour de l'axe de rotation 14 un jeu de deux surfaces annulaires de rétention 38. Le tambour 28 peut présenter plusieurs jeux de telles surfaces de rétention. Chaque jeu de surfaces de rétention 38 est séparé des autres jeux par des nervures 32.The drum 28 comprises on its outer surface an annular body 36. The latter has a general trapezoidal profile whose parallel edges are substantially parallel to the axis of rotation 14, the two other inclined sides extending essentially radially. The inclined sides of the trapezoidal profile generate by rotation about the axis of rotation 14 a set of two annular retention surfaces 38. The drum 28 may have several sets of such retention surfaces. Each set of retention surfaces 38 is separated from the other sets by ribs 32.

L'épaisseur radiale du corps annulaire 36 est supérieure à 5,00 mm, préférentiellement supérieure à 10,00 mm, plus préférentiellement supérieure à 20,00 mm. Le corps annulaire 36 forme une couronne extérieure qui permet de renforcer et rigidifier le tambour 28. Il permet de réduire les déformations du tambour 28 liées à la force centrifuge. Le corps annulaire 36 permet de remplacer les renforts annulaires intérieurs du tambour ou « poireaux ». Un tambour est généralement usiné par tournage à partir d'un brut d'usinage en forme de tambour dont les parois englobent le tambour fini. Le brut doit englober radialement les surfaces de rétentions extérieures et les poireaux intérieurs. L'ensemble impose de réaliser des usinages importants. Puisque le corps annulaire 36 est situé du même côté que les surfaces de rétention 38, le brut d'usinage peut être aminci et les usinages correspondants réduits.The radial thickness of the annular body 36 is greater than 5.00 mm, preferably greater than 10.00 mm, more preferably greater than 20.00 mm. The annular body 36 forms an outer ring which makes it possible to reinforce and stiffen the drum 28. It makes it possible to reduce the deformations of the drum 28 related to the centrifugal force. The annular body 36 makes it possible to replace the inner annular reinforcements of the drum or "leeks". A drum is generally machined by turning from a drum-shaped machining blank whose walls encompass the finished drum. The crude must embrace the surfaces radially retentions and leeks. The set requires to perform important machining. Since the annular body 36 is located on the same side as the retention surfaces 38, the machining stock can be thinned and the corresponding machining reduced.

L'aube rotorique 24 comprend des pattes de fixation 40 s'étendant radialement et axialement sous sa plateforme inférieure 28. Les pattes de fixation 40 sont inclinées l'une vers l'autre. Les surfaces de rétention correspondantes 42 sont implantées sur les surfaces intérieures des pattes de fixation 40. Les surfaces de rétention correspondantes 42 sont en regard l'une de l'autre.The rotor blade 24 comprises attachment lugs 40 extending radially and axially beneath its lower platform 28. The attachment lugs 40 are inclined towards each other. The corresponding retention surfaces 42 are implanted on the inner surfaces of the fastening tabs 40. The corresponding retention surfaces 42 are opposite one another.

Les surfaces de rétention 38 et les surfaces de rétention correspondantes 42 sont complémentaires. Elles s'épousent sur la majorité de leurs étendues. Elles peuvent être tronconiques. Elles sont configurées pour coopérer par engagement de matière de sorte à fixer l'aube rotorique 24 sur le tambour 28. Elles forment une fixation de type queue d'aronde. La section évasée des surfaces de rétention correspondantes 42, conjuguée à la section étrécie définie par les surfaces de rétention 38 du tambour permettent une rétention radiale de l'aube 24 vers le tambour 28.The retention surfaces 38 and the corresponding retention surfaces 42 are complementary. They marry on most of their expanses. They can be frustoconical. They are configured to cooperate by engagement of material so as to fix the rotor blade 24 on the drum 28. They form a dovetail type fastener. The flared section of the corresponding retention surfaces 42, together with the narrowed section defined by the retaining surfaces 38 of the drum allow radial retention of the vane 24 towards the drum 28.

Les profils de révolution des surfaces de rétention 38 et 42 sont inclinés par rapport à la perpendiculaire 44 à l'axe de rotation 14 d'un angle β, qui est compris entre 10° et 80°, préférentiellement compris entre 30° et 60° inclus.The revolution profiles of the retention surfaces 38 and 42 are inclined relative to the perpendicular 44 to the axis of rotation 14 by an angle β, which is between 10 ° and 80 °, preferably between 30 ° and 60 ° included.

Les profils des surfaces de rétention 38 et 42 sont inclinés l'un par rapport à l'autre d'un angle α. L'angle α est compris entre 60° et 120°. Plus l'angle α est grand, moins la force centrifuge tend à écarter les pattes de fixation 40 lors du fonctionnement de la turbomachine.The profiles of the retention surfaces 38 and 42 are inclined relative to each other by an angle α. The angle α is between 60 ° and 120 °. The greater the angle α, the less the centrifugal force tends to move the fastening tabs 40 during operation of the turbomachine.

Les surfaces de rétention 38 sont sensiblement en élévation radiale par rapport à la paroi 30 du tambour 28. Les léchettes 32 en sont à distance axialement. Le tambour 28 est libre axialement de surface pouvant former un obstacle aux surfaces de rétention 38 à plus de 5,00 mm, préférentiellement à plus de 15,00 mm, plus préférentiellement à plus de 30,00 mm. Les surfaces de rétention 38 sont donc facilement accessibles pour les usiner, par exemple pour réaliser une ébauche et une finition.The retention surfaces 38 are substantially in radial elevation with respect to the wall 30 of the drum 28. The wipers 32 are axially spaced therefrom. The drum 28 is free axially surface capable of forming an obstacle to the retention surfaces 38 to more than 5.00 mm, preferably to more than 15.00 mm, more preferably to more than 30.00 mm. The retention surfaces 38 are therefore easily accessible for machining, for example to achieve a blank and a finish.

La paroi 30 du tambour 28 peut s'étendre de manière sensiblement rectiligne au niveau des surfaces de rétention 38, préférentiellement entre les nervures disposées 32 en amont et en aval. Cette particularité permet de préserver la rigidité du tambour 28. Il est en particulier plus résistant à une compression axiale. Une conséquence est que sa paroi 30 peut être amincie. Le profil de la surface intérieure de la paroi 30 peut y être généralement droite ou être sensiblement courbe. Cet aspect réduit les concentrations de contraintes et améliore la durée de vie du tambour.The wall 30 of the drum 28 can extend substantially rectilinearly at the retention surfaces 38, preferably between the ribs 32 arranged upstream and downstream. This feature makes it possible to preserve the rigidity of the drum 28. In particular, it is more resistant to axial compression. One consequence is that its wall 30 can be thinned. The profile of the inner surface of the wall 30 may be generally straight or substantially curved. This aspect reduces the stress concentrations and improves the life of the drum.

Le corps annulaire 36 présente une gorge annulaire ouverte radialement vers l'extérieur. Le rotor 12 comprend un joint torique 48 logé à l'intérieur de cette gorge annulaire. Le rayon intérieur du joint torique 48 est inférieur ou égal au rayon du fond de la gorge, les rayons étant mesurés depuis l'axe de rotation 14. Le joint torique 48 est essentiellement élastique. Sous l'effet de la force centrifuge qui apparaît lors du fonctionnement de la turbomachine, le joint torique 48 est plaqué contre la surface intérieure de la plateforme inférieure 34 de l'aube rotorique 24. Il assure ainsi une étanchéité entre les côtés amont et aval de l'aube 24.The annular body 36 has an annular groove open radially outwardly. The rotor 12 comprises an O-ring 48 housed inside this annular groove. The inner radius of the O-ring 48 is less than or equal to the radius of the bottom of the groove, the radii being measured from the axis of rotation 14. The O-ring 48 is essentially elastic. Under the effect of the centrifugal force that appears during the operation of the turbomachine, the O-ring 48 is pressed against the inner surface of the lower platform 34 of the rotor blade 24. It thus ensures a seal between the upstream and downstream sides. of dawn 24.

Le corps annulaire 36 comprend des surfaces d'appui radial 50 disposées en amont et en aval. Elles peuvent être essentiellement cylindriques et sont orientées radialement vers l'extérieur. L'aube rotorique 24 présente des surfaces d'appui correspondantes 52 qui sont aptes à coopérer avec les surfaces d'appui 50 du tambour. Les surfaces d'appui 52 sont disposées en regard des surfaces d'appui 50 du tambour. Lors du fonctionnement de la turbomachine, ces surfaces 50 et 52 sont distantes l'une de l'autre. La force centrifuge les maintient à distance. Elles sont aptes à venir en contact l'une de l'autre ou du moins à être adjacentes en cas de changement de condition de fonctionnement de la turbomachine. Ces surfaces 50 et 52 permettent de réduire ou bloquer le basculement amont aval des aubes 24 par rapport au tambour 28, ce phénomène étant connu sous le terme « rocking ».The annular body 36 comprises radial bearing surfaces 50 arranged upstream and downstream. They can be essentially cylindrical and are oriented radially outwards. The rotor blade 24 has corresponding bearing surfaces 52 which are able to cooperate with the bearing surfaces 50 of the drum. The bearing surfaces 52 are arranged facing the bearing surfaces 50 of the drum. During operation of the turbomachine, these surfaces 50 and 52 are spaced apart from each other. Centrifugal force keeps them at bay. They are able to come into contact with one another or at least to be adjacent in the event of a change in the operating condition of the turbomachine. These surfaces 50 and 52 make it possible to reduce or block the downstream upstream tilting of the vanes 24 with respect to the drum 28, this phenomenon being known by the term "rocking".

La figure 4 represente le corps annulaire 36 du tambour 28 vu radialement depuis l'extérieur. Une aube rotorique 24 y est montée à l'aide de ses pattes de fixation 40.The figure 4 represents the annular body 36 of the drum 28 seen radially from the outside. A rotor blade 24 is mounted therein by means of its fixing lugs 40.

Le corps annulaire 36 présente au moins une encoche axiale 53 au niveau d'une des surfaces de rétention, afin de pouvoir y chausser les aubes rotoriques 24. Un verrou (non représenté) ou plusieurs verrous peuvent refermer la ou les encoches 53 et peuvent servir à bloquer tangentiellement les aubes 24. Les verrous peuvent chevaucher le corps annulaire 36 ou le traverser axialement. Certaines aubes rotoriques 24, en particulier leurs plateformes 34 ou leurs pattes de fixation 40, peuvent être adaptées en conséquence.The annular body 36 has at least one axial notch 53 at one of the retention surfaces, in order to be able to fit the rotor blades 24. A latch (not shown) or several locks can close the notch 53 and can serve to tangentially block the blades 24. The locks can overlap the annular body 36 or cross axially. Some rotor blades 24, in particular their platforms 34 or their fixing lugs 40, can be adapted accordingly.

La figure 5 illustre une coupe du tambour selon le premier mode de réalisation de l'invention, la coupe étant réalisée suivant l'axe 5-5 tracé sur la figure 4.The figure 5 illustrates a section of the drum according to the first embodiment of the invention, the section being taken along the axis 5-5 traced on the figure 4 .

Un segment ou tronçon des deux surfaces annulaires de rétention peut comprendre une seule encoche de montage 53 des aubes sur une seule des deux surfaces de rétention 38, de manière à permettre le montage des aubes 24 par un mouvement d'engagement avec la surface de rétention sans encoche, en vis-à-vis de l'encoche 53, suivi d'un basculement faisant pénétrer partiellement la patte de fixation 40 de la plateforme 34 dans l'encoche 53. L'aube 24 peut ensuite être coulissée selon la direction circonférentielle du tambour, de sorte que ses pattes de fixation 40 ne soient plus au niveau de la ou des encoches 53.A segment or section of the two annular retention surfaces may comprise a single mounting notch 53 of the vanes on only one of the two retention surfaces 38, so as to allow the vanes 24 to be mounted by a movement of engagement with the retention surface without notch, vis-à-vis the notch 53, followed by a tilt partially penetrating the bracket 40 of the platform 34 in the notch 53. The blade 24 can then be slid in the circumferential direction of the drum, so that its fixing lugs 40 are no longer at the level of the notch (s) 53.

La figure 6 représente un rotor selon un deuxième mode de réalisation de l'invention. Cette figure 6 reprend la numérotation des figures précédentes pour les éléments identiques ou similaires, la numération étant toutefois incrémentée de 100. Il est par ailleurs notamment fait référence à la description des figures précédentes pour leurs éléments similaires ou équivalents. Des numéros spécifiques sont utilisés pour les éléments spécifiques à ce mode de réalisation.The figure 6 represents a rotor according to a second embodiment of the invention. This figure 6 resumes the numbering of the preceding figures for identical or similar elements, however the number is incremented by 100. Furthermore, reference is made in particular to the description of the preceding figures for their similar or equivalent elements. Specific numbers are used for the specific elements of this embodiment.

Le tambour 128 comprend deux collerettes annulaires 154. Les collerettes 154 sont inclinées, préférentiellement l'une par rapport à l'autre. Elles s'écartent l'une de l'autre vers l'extérieur. Leurs profils présentent une longueur et une largeur moyenne. La longueur est supérieure au triple de la largeur moyenne, préférentiellement supérieure au quintuple. Les jonctions des collerettes 154 à la paroi 130 peuvent être distantes l'une de l'autre. La distance axiale entre les surfaces de rétention mesurée à la jonction avec la surface extérieure de la paroi 130 est supérieure à la longueur moyenne du profil des collerettes 154, préférentiellement supérieure à 1,5 fois, plus préférentiellement supérieure à deux fois. La paroi 130 peut être localement épaissie entre les collerettes 154 de sorte à la renforcer.The drum 128 comprises two annular flanges 154. The flanges 154 are inclined, preferably relative to one another. They move away from each other to the outside. Their profiles have an average length and width. The length is greater than three times the average width, preferably greater than five times. The junctions of the collars 154 to the wall 130 may be distant from each other. the other. The axial distance between the retention surfaces measured at the junction with the outer surface of the wall 130 is greater than the average length of the profile of the flanges 154, preferably greater than 1.5 times, more preferably greater than twice. The wall 130 may be locally thickened between the flanges 154 so as to strengthen it.

Cette configuration permet d'écarter axialement les surfaces de rétention 138 l'une de l'autre sans alourdir le tambour 128. La stabilité de l'aube 124 sur le tambour est améliorée. Ainsi, les angles d'inclinaison des profils des surfaces de rétention 138 et 142 peuvent être choisis avec une plus grande liberté.This configuration makes it possible to axially separate the retention surfaces 138 from each other without making the drum 128 heavier. The stability of the blade 124 on the drum is improved. Thus, the inclination angles of the profiles of the retention surfaces 138 and 142 can be chosen with greater freedom.

Les collerettes 154 définissent entre elle une espace annulaire 156. L'une d'elle peut présenter un épaississement de sorte à recevoir une gorge annulaire et un joint torique apte à assurer une étanchéité contre la plateforme de l'aube rotorique 124. Les collerettes 154 contribuent à rigidifier le tambour à la manière de cerclages.The collars 154 define between them an annular space 156. One of them may have a thickening so as to receive an annular groove and an O-ring capable of sealing against the platform of the rotor blade 124. The collars 154 help to stiffen the drum in the manner of strapping.

Claims (15)

  1. Drum (28, 128) of an axial turbomachine rotor, comprising
    a wall (30, 130) of revolution about the axis of rotation (14, 114) of the rotor, forming a hollow body and comprising on its outer surface two annular retaining surfaces (38, 138) for a row of blades;
    wherein the two retaining surfaces (38, 138) of the drum wall (28, 128) generally diverge from one another to form a profile which is wider the further it is radially outwards from the outer surface of the wall;
    characterized in that the retaining surfaces (138) are formed by two annular flanges (154) projecting from the outer surface of the wall (130), the said flanges (154) being inclined opposite to one another relative to a direction perpendicular to the axis of rotation (114).
  2. Drum (128) in accordance with Claim 1, characterized in that the two flanges (154) are located on the wall (130), separated from one another, the said separation being preferably greater than 10 mm.
  3. Drum (28, 128) of an axial turbomachine rotor, comprising
    a wall (30, 130) of revolution about the axis of rotation (14, 114) of the rotor, forming a hollow body and comprising on its outer surface two annular retaining surfaces (38, 138) for a row of blades;
    wherein the two retaining surfaces (38, 138) of the drum wall (28, 128) generally diverge from one another to form a profile which is wider the further it is radially outwards from the outer surface of the wall;
    characterized in that the drum is essentially free of material inside the wall and in that the drum comprises at least one annular body (36) on the outer surface of the wall (30) and forming the retaining surfaces (38).
  4. Drum (28) in accordance with Claim 3, characterized in that the annular body (36) comprises an annular groove opening radially outwards designed to hold a seal preferably in the shape of a toroid (48) designed to be pressed against the platforms (34) of the blades (24) by centrifugal force during rotation of the drum.
  5. Drum (28, 128) in accordance with one of Claims 3 to 4, characterized in that the annular body generally shows a trapezoid profile whose parallel sides extend generally according to the rotation axis of the rotor, the shortest of these sides being arranged toward the interior.
  6. Drum (28, 128) in accordance with one of Claims 1 to 5, characterized in that the profile of each of the two retaining surfaces (38, 138) forms an average angle of between 30° and 60° with the axis of rotation (14, 114), and/or the profiles of the said surfaces form a mean angle between them of between 60° and 120°.
  7. Drum (28, 128) in accordance with one of Claims 1 to 6, characterized in that the wall (30, 130) defines the structure of the drum, preferably from its front end to its rear end.
  8. Drum (28, 128) in accordance with one of Claims 1 to 7, characterized in that the wall (30, 130) of the drum (28, 128) has one or more annular ribs (32, 132) upstream and downstream respectively of the two retaining surfaces (38, 138), the said ribs (32, 132) being configured to mate with annular abradable layers of material, the wall (30, 130) extending substantially in a straight line along the two retaining surfaces (38, 138) between the said upstream and downstream ribs (32, 132).
  9. Drum (28, 128) in accordance with one of Claims 1 to 8, characterized in that the two retaining surfaces (38, 138) are generally raised radially relative to the adjacent wall (30, 130).
  10. Drum (28, 128) in accordance with one of Claims 1 to 9, characterized in that the wall (30, 130) and the retaining surfaces (38, 138) are made in one piece, preferably substantially formed integrally.
  11. Drum (28, 128) in accordance with one of Claims 1 to 10, characterized in that a segment of the two annular retaining surfaces (38, 138) includes a notch (53) for mounting the blades (24, 124) on one of the two surfaces (38, 138), so as to allow the blades to be assembled by a locking movement of the unnotched retaining surface, followed by tilting the platform (34, 134) to slide into the notch.
  12. Drum (28, 128) in accordance with one of Claims 1 to 11, characterized in that it comprises the blade row (24, 124), the said blades each comprising a platform (34, 134) provided with two corresponding retaining surfaces (42, 142) designed to mate with the retaining surfaces (38, 138) of the wall (30, 130).
  13. Drum (28, 128) in accordance with Claim 12, characterized in that the platform (34, 134) of the blades (24, 124) comprises a cavity open towards the wall (30, 130) of the drum and forming corresponding retaining surfaces (42, 142), the bottom of the cavity forming a radial abutment surface (52, 152) directed towards the inside of the drum.
  14. Drum (28, 128) in accordance with one of Claims 12 and 13, characterized in that the two corresponding retaining surfaces (42, 142) of the blades (24, 124) are substantially situated in line with the leading and trailing edges, respectively, of the said blades.
  15. Turbomachine (2) comprising a turbine rotor (12) or compressor (4,6), preferably low-pressure, characterized in that the rotor comprises a drum (28, 128) according to one of Claims 1 to 14, and preferably wherein the drum comprises a plurality of sets of retaining surfaces (38, 138), each set corresponding to a blade row (24, 124).
EP13153799.5A 2013-02-04 2013-02-04 Rotor drum of an axial turbomachine and corresponding turbomachine Active EP2762681B1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP13153799.5A EP2762681B1 (en) 2013-02-04 2013-02-04 Rotor drum of an axial turbomachine and corresponding turbomachine
CA2841344A CA2841344A1 (en) 2013-02-04 2014-01-24 Attaching the blades of an axial turbocompressor to the compressor drum
RU2014103113A RU2651697C2 (en) 2013-02-04 2014-01-30 Rotor drum of axial turbomachine and corresponding turbomachine
US14/168,530 US9739150B2 (en) 2013-02-04 2014-01-30 Attaching the blades of an axial turbocompressor to the compressor drum
CN201410116548.2A CN103967840B (en) 2013-02-04 2014-02-07 The blade of axial flow turbine compressor is connected to compressor drum

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13153799.5A EP2762681B1 (en) 2013-02-04 2013-02-04 Rotor drum of an axial turbomachine and corresponding turbomachine

Publications (2)

Publication Number Publication Date
EP2762681A1 EP2762681A1 (en) 2014-08-06
EP2762681B1 true EP2762681B1 (en) 2017-09-06

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EP13153799.5A Active EP2762681B1 (en) 2013-02-04 2013-02-04 Rotor drum of an axial turbomachine and corresponding turbomachine

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US (1) US9739150B2 (en)
EP (1) EP2762681B1 (en)
CN (1) CN103967840B (en)
CA (1) CA2841344A1 (en)
RU (1) RU2651697C2 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3027071B1 (en) 2014-10-13 2019-08-23 Safran Aircraft Engines METHOD OF INTERVENTION ON A ROTOR AND ASSOCIATED CLINKER
FR3039225B1 (en) * 2015-07-20 2017-07-21 Snecma TURBOMACHINE, SUCH AS A TURBO AIRCRAFT
CN110005637B (en) * 2018-01-04 2021-03-26 中国航发商用航空发动机有限责任公司 Axial-flow type aircraft engine rotor
US11085315B2 (en) * 2019-07-09 2021-08-10 General Electric Company Turbine engine with a seal
IT201900014736A1 (en) 2019-08-13 2021-02-13 Ge Avio Srl Integral sealing elements for blades held in a rotatable annular outer drum rotor in a turbomachinery.

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DE1957614C3 (en) * 1969-11-15 1974-03-14 Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Blade ring for high-speed gas turbine engines
GB2001398A (en) * 1977-07-22 1979-01-31 Rolls Royce Bladed Rotor for Gas Turbine Engine
DE3839672A1 (en) * 1988-11-24 1990-05-31 Mtu Muenchen Gmbh SHOVEL FOOT FASTENING FOR A FIBER TECHNICAL ROTOR SHOVEL
DE3934207A1 (en) * 1989-10-13 1991-04-25 Mtu Muenchen Gmbh ARRANGEMENT FOR FASTENING TURBO BLADES
DE4442157A1 (en) * 1994-11-26 1996-05-30 Abb Management Ag Method and device for influencing the radial clearance of the blades in compressors with axial flow
US6409472B1 (en) 1999-08-09 2002-06-25 United Technologies Corporation Stator assembly for a rotary machine and clip member for a stator assembly
FR2845436B1 (en) * 2002-10-02 2004-12-31 Snecma Moteurs DRUM FORMING PARTICULARLY A TURBOMACHINE ROTOR, COMPRESSOR AND TURBOMOTOR COMPRISING SUCH A DRUM
RU2270937C1 (en) * 2004-08-10 2006-02-27 Акционерное общество открытого типа Авиамоторный научно-технический комплекс "Союз" Gas-turbine engine axial-flow compressor (versions)
EP2075417B1 (en) 2007-12-27 2016-04-06 Techspace Aero Platform for a bladed wheel of a turbomachine, bladed wheel and compressor or turbomachine comprising such a bladed wheel
EP2400160B1 (en) * 2010-06-23 2014-01-01 Techspace Aero S.A. Lightened rotor of axial compressor

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Also Published As

Publication number Publication date
RU2014103113A (en) 2015-08-10
CN103967840A (en) 2014-08-06
CA2841344A1 (en) 2014-08-04
EP2762681A1 (en) 2014-08-06
RU2651697C2 (en) 2018-04-23
US20140219803A1 (en) 2014-08-07
US9739150B2 (en) 2017-08-22
CN103967840B (en) 2018-12-18

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