US20070048142A1 - Assembly and method for the mounting of the foot of a blade of a turbine, blower, compressor, and turbine comprising such an assembly - Google Patents

Assembly and method for the mounting of the foot of a blade of a turbine, blower, compressor, and turbine comprising such an assembly Download PDF

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Publication number
US20070048142A1
US20070048142A1 US11/509,582 US50958206A US2007048142A1 US 20070048142 A1 US20070048142 A1 US 20070048142A1 US 50958206 A US50958206 A US 50958206A US 2007048142 A1 US2007048142 A1 US 2007048142A1
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US
United States
Prior art keywords
foot
blade
film
mounting
aperture
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.)
Abandoned
Application number
US11/509,582
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English (en)
Inventor
Bruno Dambrine
Stephane Deyber
Jean-Noel Mahieu
Claude Mons
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
Assigned to SNECMA reassignment SNECMA ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: DAMBRINE, BRUNO, DEYBER, STEPHANE, MAHIEU, JEAN-NOEL, MONS, CLAUDE
Publication of US20070048142A1 publication Critical patent/US20070048142A1/en
Abandoned legal-status Critical Current

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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
    • F01D5/30—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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F05D2300/432—PTFE [PolyTetraFluorEthylene]
    • 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
    • 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
    • F05D2300/611—Coating

Definitions

  • the invention relates to a method for the mounting of the foot of a blade of a turbine, made of metal, fixed or movable, in the aperture of a support made of metal, and to the assembly for such a mounting.
  • the present invention is not limited to situations in which the support of the foot of the blade comprises a rotor disk of a fan, but equally encompasses other situations of the mounting of movable blades, for example on the rotor disk of a low-pressure compressor, or even in the intake area of a high-pressure compressor.
  • the level of local stresses is very high due to the friction coefficient at the interface between the walls in contact with the foot of the blade and the aperture, derived from metal-on-metal contact.
  • a surface coating is deposited on the foot of the blade, in the form of a metallic alloy which is resistant to fretting, particularly by plasma projection, or use can be made of a protection element formed from one or more metallic foils (or tinsels), possibly themselves coated, surrounding the foot of the blade, these protection elements possibly being associated with lubricating varnishes.
  • the friction coefficient can be reduced to a value generally greater than 0.2. During operation, however, this value regularly increases up to about 0.5, or even beyond if the wear is complete.
  • One object of the invention is to provide another method of mounting a turbine blade, fixed or movable, made of metal, in the aperture of a support made of metal, in order to improve both the resistance to contact pressure between these components, while still allowing for very simple and rapid implementation of this procedure, both during initial mounting as well as when repairing the mounting of the blade foot.
  • this object is achieved by a method of mounting the foot of a turbine blade made of metal, fixed or movable, characterised in that it comprises the following steps:
  • the film replaces the wear-resistant metallic coating of the prior art.
  • This type of film is already being used for the mounting of the feet of blades made of composite material, using a film of the type derived from resistant fibre fabric impregnated with resin.
  • the removal in whole or in part of the film is carried out in an essentially simple manner, by straightforward peeling with the aid of a scalpel.
  • the application and fixing of the new replacement film are themselves also carried out much more simply and rapidly than for a metallic cladding, without the need for technologically complex equipment and without the risk of damaging the support.
  • the method according to the invention can be used both during the initial mounting as well as when carrying out a repair to the mounting between the foot of a blade and its aperture when this mounting has been initially carried out in accordance with the invention or if recourse has been made to a wear-resistant metallic coating.
  • the film is provided beforehand with bonding agent, on the surface or throughout its substance.
  • the bonding agent is thermo-polymerisable, and in the course of step b) the assembly comprising at least the foot of the blade, the support, and the film, is placed in an autoclave brought to a temperature which will allow the bonding agent to take, over a predetermined minimum period of time.
  • step a) the foot of the blade is clad with a metallic foil, said wear-resistant film then being arranged between the foil and the aperture.
  • the invention also relates to an assembly for the mounting of the foot of a turbine blade, fixed or movable, made of metal, in the aperture of a support made of metal, which is reliable, simple, and economical to put in place and to repair.
  • this assembly comprises, between the foot and the aperture, at least one non-metallic film comprising polyamide, coated or impregnated with a polymer bonding agent.
  • the film is arranged in such a manner that the bonding agent adheres to the foot of the blade.
  • the film may adhere to the surface of the support aperture.
  • the film comprises fibre glass, polytetrafluoroethylene, in particular Teflon (registered trademark), and/or polyamide, notably in the form of fibres, in particular of Kevlar or Nomex (registered trademarks).
  • the non-metallic film advantageously comprises a material made of synthetic fibres.
  • synthetic fibres there are, in fact, numerous types of synthetic fibres in existence which exhibit high wear resistance, as well as a low friction coefficient.
  • the bonding agent is thermo-polymerisable, which allows for the moment to be monitored at which this bonding agent takes, by placing the assembly in an autoclave brought to a minimum temperature for a predetermined period of time.
  • the bonding agent is of the resin type, and comprises a phenol or polyurethane resin.
  • the assembly according to the present invention encompasses the situation in which the foot of the blade is lodged directly in the aperture, but likewise the situation in which the assembly additionally comprises at least one metallic foil mounted on the foot of the blade, said non-metallic film then being arranged between the foil and the aperture.
  • the foot of the blade is made of titanium, of aluminium or of steel or of one of their alloys.
  • the blade support is made of titanium, of aluminium or of steel or of one of their alloys.
  • the present invention likewise relates to a turbine blower, comprising assemblies for the mounting of the foot of a blade according to one of the definitions given heretofore, characterised in that the blades are movable and the support is formed by the disk of the rotor.
  • the present invention also relates to a turbine compressor comprising assemblies for the mounting of the foot of a blade according to one of the definitions given heretofore, characterised in that the blades are movable and the support is formed by disk of the rotor.
  • the present invention also relates to a turbine compressor comprising assemblies for the mounting of the foot of a blade according to one of the definitions given heretofore, characterised in that the blades are movable and the support is formed by a flange.
  • Such compressors are, in particular, turbine compressors of the low-pressure type, but the invention can also relate to blades located at the intake of a high-pressure compressor, at the level of which the temperature attained does not prejudice the mechanical properties of any of the constituents of the wear resistance layer, namely the film and the bonding agent.
  • the present invention likewise relates to a turbine equipped with assemblies for the mounting of the foot of a blade according to one of the definitions given heretofore.
  • FIG. 1 represents a partial transverse sectional view of a fan, showing the mounting of the foot of a blade in the rotor, the blade being subjected to the centrifugal forces of rotation, and
  • FIG. 2 represents a view similar to that of FIG. 1 , according to a variant embodiment of the present invention.
  • FIG. 1 represents the mounting on the disk 10 of a blower or rotor of a blade 12 , of which the foot 121 is located in one of the multiple apertures 101 of the disk 10 .
  • each aperture 101 has a shape which is approximately complementary to the shape of the foot 121 of the blade 12 to form a mounting of the dovetail type.
  • the apertures 101 are distributed radially and equidistantly over the entire length of the circumference of the disk 10 , being open towards the outside.
  • the Figures show an enlarged portion of the transverse section of the disk 10 , i.e. a section orthogonal to the axis of rotation of the fan, each foot 121 of a blade 12 having a symmetrical contour with two lateral walls 122 , diverging in relation to one another from the body of the blade 12 in the direction of the free end of the foot 121 of the blade 12 , as far as a base wall 124 approximately parallel to the axis of rotation and the periphery of the disk 10 and orthogonal to the principal orthogonal direction of the corresponding blade 12 .
  • the apertures 101 have a similar shape to the lateral walls 102 , inclined outwards from the circumference, in the direction of the interior portion of the disk 10 as far as a base wall 104 .
  • the dimensions of the foot 121 of the blade 12 and of the blade 101 are such that, when the rotor 10 is at rest, the foot 121 is retained in the aperture 101 , the base wall 124 of the foot 121 then being able to touch the base wall 104 of the aperture 101 .
  • a contact area exists, referred to as the bearing surface and subject to substantial forces, designated by the reference number 14 , between the lateral wall 122 of the foot 121 and the lateral wall 102 of the aperture 101 , as well as an area without contact, designated by the reference number 16 , which is not subject to any mechanical contact stress during the rotation of the rotor formed from the disk 10 .
  • the deterioration caused by fatigue and wear on the contact surfaces of the lateral walls 102 and 122 due to the relative movement between the foot 121 of the blade 12 and the aperture 101 of the rotor 10 is reduced by the use of a non-metallic film 20 , which covers the whole outer surface of the foot 121 .
  • a film 20 which is advantageously formed from a wear-resistant fabric, such as a fabric from the CHEMFAB family of products from Saint-Gobain, manufactured based on glass fibres and/or aramide fibres, such as those known under the registered trademarks Nomex or Kevlar.
  • a wear-resistant fabric such as a fabric from the CHEMFAB family of products from Saint-Gobain, manufactured based on glass fibres and/or aramide fibres, such as those known under the registered trademarks Nomex or Kevlar.
  • This film 20 adheres to the outer surface of the foot 121 with a bonding agent coating or impregnating the film 20 , at least on the face of the film 20 before adhering, this bonding agent being preferably of the resin type, and advantageously a phenol or polyurethane resin.
  • This film 20 has a first face coated with a layer of polytetrafluoroethylene for the lubricant, and a second face intended to be adhesively bonded, which has a good attachment and holding surface, the thickness of this film being of the order of some tenths of millimetres.
  • the adhesive is applied in a regular manner to the second face of the film, and this second face of the film 20 pre-treated with adhesive is then arranged on the lateral walls 122 and the base wall 124 of the foot 121 of each blade 12 .
  • the assembly formed by the foot of the blade 121 , the resin, and the film 20 are placed under pressure during the adhesive bonding, i.e. the polymerisation of the resin.
  • the pressure used is of the order of 7 to 14 MPa. This allows for good adhesion of the adhesive to be guaranteed over the whole of the surface, as well as the evacuation of the solvents.
  • polymerisation is carried out, which in this embodiment is carried out at 170° C. for a period of one hour.
  • a crushed film 20 is obtained, which adheres perfectly over the whole surface of the foot 121 of the blade 12 , in such a way as to guarantee its presence in the area 14 after mounting, as shown in FIG. 1 .
  • the film 20 comprises on the surface opposite to that which is going to adhere to the foot 121 , a layer of polytetrafluoroethylene (PTFE), which forms a lubricating surface which reduces the friction coefficient with the surface of the lateral walls 102 of the aperture 101 to a very significant degree, this friction coefficient possibly being as low as 0.1.
  • PTFE polytetrafluoroethylene
  • the foot 121 of the blade can be cleaned in order to remove the excess resin by blasting with glass beads.
  • protection against wear by way of a non-metallic film 20 allows for easier non-destructive tests of the foot 121 of the blade.
  • recourse can be made to the technique of Foucault currents, which allows for the detection of defects (in particular micro-cracks or fissures) of small size (from about 0.1 mm).
  • the film 20 is a technical fabric formed from a fibre glass and/or polyamide fibre material, advantageously comprising polytetrafluoroethylene.
  • the preceding arrangement makes provision for the placing of a film 20 over the whole surface of the foot 121 of each blade. It will be understood that this solution is easier and quicker, but in reality, in order to achieve the object of the invention, it is sufficient for the film 20 to cover the lateral walls 122 of the foot 121 in the contact area, i.e. the bearing surface 14 .
  • This technique can likewise be applied, according to a variant, by adhesively bonding the non-metallic film 20 to the wall of the aperture 101 (not shown in the Figure).
  • the method according to the invention can readily be used during the initial mounting, but equally for carrying out a repair of the mounting between the foot 121 of a blade 12 and its aperture 101 , whether this mounting was initially carried out in accordance with the invention or by having had recourse beforehand to a metallic wear-resistant coating.
  • the film 20 can be applied as a repair on the old metallic coating after a prior treatment consisting of blasting and cleaning said coating or after the complete removal of this old metallic coating.
  • the foil 22 is a cambered sheet with a U-shaped cross-section, the arms of which are divided into two parts so as to form an obtuse angle facing into the interior of the U. This shape approximates that of the foot 121 of the blade 121 in such a way that the end sections of the arms of the U of the foil cover the area 14 of contact between the foot 121 and the aperture 101 .
  • the film 20 can be made to cover only the whole of the surface of the wall of the aperture 101 , or at the same time all the outer surface of the foil 22 and all the surface of the wall of the aperture 101 , or only an area comprising at least the area 14 of one, the other, or both of these surfaces.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US11/509,582 2005-08-26 2006-08-25 Assembly and method for the mounting of the foot of a blade of a turbine, blower, compressor, and turbine comprising such an assembly Abandoned US20070048142A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0508768A FR2890126B1 (fr) 2005-08-26 2005-08-26 Ensemble et procede pour le montage du pied d'une aube de turbomachine, soufflante, compresseur et turbomachine comportant un tel ensemble
FR0508768 2005-08-26

Publications (1)

Publication Number Publication Date
US20070048142A1 true US20070048142A1 (en) 2007-03-01

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US11/509,582 Abandoned US20070048142A1 (en) 2005-08-26 2006-08-25 Assembly and method for the mounting of the foot of a blade of a turbine, blower, compressor, and turbine comprising such an assembly

Country Status (7)

Country Link
US (1) US20070048142A1 (fr)
EP (1) EP1777371A1 (fr)
JP (1) JP2007064220A (fr)
CN (1) CN1920259A (fr)
CA (1) CA2557109A1 (fr)
FR (1) FR2890126B1 (fr)
RU (1) RU2006130731A (fr)

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US20080318467A1 (en) * 2007-06-19 2008-12-25 Denomme Gary M Relay receptacle shorting plug
EP2011601A1 (fr) * 2007-03-10 2009-01-07 MTU Aero Engines GmbH Procédé et dispositif de traitement de composants d'une turbine à gaz ainsi que matière première composite et son utilisation dans des procédés de traitement ou de liaison de composants d'une turbine à gaz
US20090038739A1 (en) * 2007-08-09 2009-02-12 United Technologies Corporation Replacement of a lubricant layer bonded to a part of a gas turbine engine
GB2452515A (en) * 2007-09-06 2009-03-11 Siemens Ag Seal coating for rotor blade and/or disc slot
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EP2388439A3 (fr) * 2010-05-20 2014-04-30 United Technologies Corporation Composant à profil d'aube ayant une couche électrochimique isolante
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EP2371521B1 (fr) * 2010-04-02 2014-07-02 Techspace Aero S.A. Procédé de fabrication d'un redresseur
JP5725849B2 (ja) * 2010-12-27 2015-05-27 三菱日立パワーシステムズ株式会社 固定治具
FR2975428B1 (fr) * 2011-05-17 2015-11-20 Snecma Roue a aubes de turbomachine
JP6085096B2 (ja) * 2012-04-05 2017-02-22 三菱日立パワーシステムズ株式会社 燃料ガス圧縮機の動翼取り外し方法
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JP6778147B2 (ja) * 2017-05-31 2020-10-28 三菱重工業株式会社 複合材料翼及び複合材料翼の製造方法
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Cited By (52)

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Publication number Priority date Publication date Assignee Title
EP2011601A1 (fr) * 2007-03-10 2009-01-07 MTU Aero Engines GmbH Procédé et dispositif de traitement de composants d'une turbine à gaz ainsi que matière première composite et son utilisation dans des procédés de traitement ou de liaison de composants d'une turbine à gaz
US20080318467A1 (en) * 2007-06-19 2008-12-25 Denomme Gary M Relay receptacle shorting plug
US20090038739A1 (en) * 2007-08-09 2009-02-12 United Technologies Corporation Replacement of a lubricant layer bonded to a part of a gas turbine engine
US8545183B2 (en) 2007-09-06 2013-10-01 Siemens Aktiengesellschaft Seal coating between rotor blade and rotor disk slot in gas turbine engine
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CN1920259A (zh) 2007-02-28
CA2557109A1 (fr) 2007-02-26
FR2890126B1 (fr) 2010-10-29
RU2006130731A (ru) 2008-02-27
FR2890126A1 (fr) 2007-03-02
EP1777371A1 (fr) 2007-04-25

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