EP1985810B1 - Amortisseur pour aubes de turbomachine - Google Patents

Amortisseur pour aubes de turbomachine Download PDF

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Publication number
EP1985810B1
EP1985810B1 EP08155206A EP08155206A EP1985810B1 EP 1985810 B1 EP1985810 B1 EP 1985810B1 EP 08155206 A EP08155206 A EP 08155206A EP 08155206 A EP08155206 A EP 08155206A EP 1985810 B1 EP1985810 B1 EP 1985810B1
Authority
EP
European Patent Office
Prior art keywords
damper
weight
rotor
rim
spring
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
EP08155206A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1985810A1 (fr
Inventor
Eric Lefebvre
Mathieu Caucheteux
Goran Durdevic
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 Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP1985810A1 publication Critical patent/EP1985810A1/fr
Application granted granted Critical
Publication of EP1985810B1 publication Critical patent/EP1985810B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • 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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion 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
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/38—Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/601—Fabrics
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Definitions

  • the present invention relates to the field of turbomachines comprising at least one rotor disk provided with blades on the rim, and relates to a dynamic damper mounted under the platform of the blades. It is more particularly axial compressors.
  • a turbomachine concerned by the invention is an axial compressor or an axial turbine of the type comprising at least one rotor disc with recesses dug on its rim for blades which extend radially relative to the axis of the machine.
  • the blades themselves include a foot, a blade and in between a platform. The foot is embedded in the disk housing, the blade is swept by the engine gas flow and the platform forms a portion of the radially inner surface of the gas stream.
  • Dynamic damping aims at modifying the dynamic behavior of the blades of the turbomachine by adding a mass under the platforms of the blades. The forces thus generated in operation make it possible to reduce the dynamic stresses in the blade root by changing the natural frequencies of vibration.
  • dampers are known among which there are glue dampers and reported dampers: glued dampers are directly fixed by gluing. on the inner surface of the platforms, that is to say the surface facing the axis of the machine. This solution has no mounting problem. It requires, however, that the weights are accurately positioned before gluing and a sufficiently strong glue to prevent loss of shock in operation.
  • the dampers reported are arranged between the blades, in operation they are centrifuged and stopped radially by the blade platforms. This system requires an appropriate environment, accessible so as to allow both the mounting and the maintenance in place of the dampers. Unlike the previous solution we do not encounter cases with loss of damper because there is no bonding. Problems of wear can appear however due to the friction of the parts with each other.
  • EP 1291492 describes a damper for turbomachine blades arranged to be housed between two adjacent blades under the face of the platforms turned towards the rim of the rotor disc.
  • the damper comprises a weight, a sole and a spring.
  • a damper for turbomachine blades which can be housed between the underside of the platforms of two adjacent blades of a turbomachine and the rim of the rotor disk on which the blades are mounted, comprising a flyweight, a sole and a spring, the spring connecting the weight to the sole is characterized in that at least the flyweight is made of composite material and that the sole is shaped to bear on said rim.
  • the solution of the invention by the spring function makes it possible to design a damper whose shape makes it possible to put it in place in the inaccessible spaces and to ensure a maintenance by limiting the friction reducing the risk of wear.
  • the flyweight comprises a portion of surface of contact with the platforms, said surface portion forming, when the spring is at rest, an angle less than 90 ° with the sole, said angle being determined by the angle that forms the inner face of the platforms with the rim.
  • the damper thus has a form deformable wedge easily manipulated.
  • the spring is a blade secured to one end of the weight and the sole at its opposite end.
  • the weight is made of composite material, the latter material allows a wide choice of density of the weight while offering a great flexibility of form. More particularly, the material is an impregnated textile.
  • the portion of the spring damper can be distinguished from the feeder portion in the choice of materials used and their structure.
  • the flyweight may include at least one density insert distinct from the density of the impregnated material.
  • the insert is determined according to the target density for the damper. It may be a metal insert for example if the density is to be increased or a foam material if on the contrary the density must be reduced.
  • the damper comprises on at least one free end of the sole or the weight of a blade portion forming a stop or a fixing hook.
  • the mass of the damper is adjusted so as to be interchangeable without requiring rebalancing of the rotor on which it is mounted.
  • the adjustment of the mass is done simply by removal of material in the area of the center of gravity of the weight.
  • the Applicant also intends to protect a turbomachine rotor comprising a rim with individual cells and blades having a foot housed in the cells, a blade and a platform between the foot and the blade. It is characterized in that dampers as defined above are housed in the spaces between the rim and two platforms of two adjacent blades. In order to take advantage of such a structure the springs of the dampers are pre-stressed during assembly.
  • a damper 1 according to the invention. It comprises a flyweight 11, a spring 12 and a sole 13.
  • the flyweight is shaped to the environment in which the damper is intended to be mounted.
  • the weight is elongated for mounting in the free space between two adjacent blades of a gas turbine engine compressor, under the platforms of the two blades.
  • the weight has two surfaces 11A and 11B of contact with the platforms, and two side surfaces 11C and 11D.
  • the weight 11 is extended at one end by a spring 12 shaped curved blade about an axis perpendicular to the longitudinal direction of the weight.
  • the leaf spring 12 is connected to a flat plate-shaped sole.
  • the flyweight forms in the example shown an angle with the plane of the sole when the spring is at rest, unconstrained.
  • the ends of the weight and the sole opposite the spring each comprise a hook-shaped folded blade, 14 and 15 respectively.
  • the Figures 3 and 4 show the damper in place in a turbomachine rotor.
  • it is a compressor rotor 2, known per se, seen, on the figure 3 from downstream in the direction of gas flow.
  • This rotor 2 is composed of a disc 3 and a plurality of blades 4 at its periphery.
  • the rim 31 is provided with substantially axial cells 31 'distributed around its circumference. In this example the cells are section dovetail.
  • the blades 4 have a foot 41, a platform 42 and a blade 43.
  • the foot in its lower portion 41 ' has a dovetail section, complementary to that of the cells.
  • the cells thus have surfaces forming radial retaining surfaces of the blades against the centrifugal forces.
  • Foot also includes a stub 41 "under the platform 42.
  • This stilt is provided with a hook 41 '''facing downstream.This hook cooperates with a not shown ring which cooperates with the downstream face of the rim to lock the blades
  • the locking can also be ensured by wedges arranged under the blade between the foot and the bottom of the cell.
  • Figures 3 and 4 the platforms 42 are inclined relative to the surface of the rim. This is a compressor where the platforms define the section reduction of the air stream in compression.
  • the damper 1 in place between two adjacent blades, is disposed in the space defined under the two platforms 42 between the rim 31 and the two stilts 41 ''.
  • the spring 12 is arranged to be under tension so that the weight 11 remains pressed against the platforms 42 permanently.
  • the sole by reaction is supported and pressed against the rim 31.
  • the two hook blades 14 and 15 are made to engage one 14 under the radial rib 42 ', the other 15 against the downstream edge of the rim 31.
  • the damper is visible only by the two hook blades 14 and 15 which thus fulfill the keying function. We can check at a glance either their absence or a wrong assembly. It is understood that the surfaces 11A, 11B, 11C and 11D, coming into contact against the vanes are shaped accordingly.
  • the damper is preferably made of composite material.
  • the manufacturing technique comprises making a stack of several layers of fabrics impregnated with an organic resin in a mold; then the polymerization of the resin in an autoclave.
  • the material can be obtained from a preformed texture of resin-injected woven fibers using a process such as that described in US Pat. FR 2759096 in the name of the plaintiff.
  • the texture can be of type 2D (D for dimension) 3D or that known under the designation 2.5D.
  • the fibers may be based on a single material or different materials, for example a mixture of carbon fibers with glass fibers and fibers known as Kevlar ®.
  • the entire damper can be made in one piece or in several separate elements that are assembled.
  • the materials may differ.
  • the fibers forming the reinforcement of the spring element and or sole may be different from the element forming the flyweight. The choice is conditioned by the desired properties of one element with respect to the other.
  • one or more inserts 116 in the fibrous structure of the weight 110 of the damper 100 as a function of the density that it is desired to obtain.
  • a metal insert makes it possible to increase the density
  • an insert with foam structure, in the form of foam makes it possible to reduce the density of the weight.
  • the structure of the damper, spring 112 and sole 113 is not different from the damper 10
  • the figure 9 shows another embodiment of shock absorber 200 in which the surface in contact with the platforms has been reduced to areas, such as 211B1 and 211B2, of reduced extent and located along the weight. This is to locate the effort on the platforms of the blades to improve the effectiveness of the damper. These areas can be obtained by machining the surface of the weight.
  • the figure 10 shows another alternative embodiment of the damper according to the invention.
  • the damper 300 comprises an additional weight 317 fixed on the spring 312 forward relative to the weight 311. This solution allows when necessary to distribute the dynamic damping forces along the blade platform.
  • the damper 300 may be made in one piece as the previous embodiments or in several elements attached to each other.
  • the structure of the damper makes it possible to ensure a very precise mass calibration.
  • the weight of the weight is adjusted by removal of material by digging a cavity around the center of gravity in the axis of inertia of the weight as seen on the figure 11 .
  • the sole is pierced at 13 'and the cavity 19, which is seen in transparency, is hollowed out along the axis of inertia J.
  • This adjustment makes it possible to produce identical dampers in mass with a precision of up to 0 5g.
  • it provides a surplus of material manufacturing around the center of gravity. All the dampers thus produced are interchangeable with each other. This makes it possible to limit the differences in distribution of the masses likely to generate unbalance in the rotor.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP08155206A 2007-04-27 2008-04-25 Amortisseur pour aubes de turbomachine Active EP1985810B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0703106A FR2915510B1 (fr) 2007-04-27 2007-04-27 Amortisseur pour aubes de turbomachines

Publications (2)

Publication Number Publication Date
EP1985810A1 EP1985810A1 (fr) 2008-10-29
EP1985810B1 true EP1985810B1 (fr) 2010-06-09

Family

ID=38826493

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08155206A Active EP1985810B1 (fr) 2007-04-27 2008-04-25 Amortisseur pour aubes de turbomachine

Country Status (8)

Country Link
US (1) US8137071B2 (zh)
EP (1) EP1985810B1 (zh)
JP (1) JP5362252B2 (zh)
CN (1) CN101294501B (zh)
CA (1) CA2629803C (zh)
DE (1) DE602008001458D1 (zh)
FR (1) FR2915510B1 (zh)
RU (1) RU2493370C2 (zh)

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US11808170B2 (en) 2019-05-29 2023-11-07 Safran Aircraft Engines Turbomachine assembly having a damper
US11808169B2 (en) 2019-05-29 2023-11-07 Safran Aircraft Engines Assembly for a turbomachine

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FR2881174B1 (fr) * 2005-01-27 2010-08-20 Snecma Moteurs Dispositif de positionnement d'une aube et disque aubage comportant un tel dispositif

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11808170B2 (en) 2019-05-29 2023-11-07 Safran Aircraft Engines Turbomachine assembly having a damper
US11808169B2 (en) 2019-05-29 2023-11-07 Safran Aircraft Engines Assembly for a turbomachine

Also Published As

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JP2008274945A (ja) 2008-11-13
RU2008116554A (ru) 2009-10-27
FR2915510A1 (fr) 2008-10-31
FR2915510B1 (fr) 2009-11-06
CN101294501A (zh) 2008-10-29
JP5362252B2 (ja) 2013-12-11
EP1985810A1 (fr) 2008-10-29
CA2629803A1 (fr) 2008-10-27
CA2629803C (fr) 2014-12-30
RU2493370C2 (ru) 2013-09-20
US8137071B2 (en) 2012-03-20
CN101294501B (zh) 2013-05-01
DE602008001458D1 (de) 2010-07-22
US20090010762A1 (en) 2009-01-08

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