(19)
(11)EP 2 434 105 B1

(12)EUROPEAN PATENT SPECIFICATION

(45)Mention of the grant of the patent:
29.04.2020 Bulletin 2020/18

(21)Application number: 11182794.5

(22)Date of filing:  26.09.2011
(51)International Patent Classification (IPC): 
F01D 21/04(2006.01)
F01D 25/24(2006.01)

(54)

Metallic backing for composite flange of a fan containment case

Metallischer Verstärkungsrahmen für einen Verbundstoffflansch eines Fangehäuses mit Berstschutz

Cadre de renforcement métallique pour une bride composite d'un carter de rétention de soufflante


(84)Designated Contracting States:
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

(30)Priority: 28.09.2010 US 892037

(43)Date of publication of application:
28.03.2012 Bulletin 2012/13

(73)Proprietor: United Technologies Corporation
Farmington, CT 06032 (US)

(72)Inventors:
  • Robertson, Jr., Thomas
    Glastonburyc, CT Connecticut 06033 (US)
  • Lussier, Darin S.
    Berlin, CT Connecticut 06037 (US)

(74)Representative: Dehns 
St. Bride's House 10 Salisbury Square
London EC4Y 8JD
London EC4Y 8JD (GB)


(56)References cited: : 
EP-A2- 2 290 197
GB-A- 2 406 627
US-A- 4 205 927
US-A1- 2005 252 195
US-A1- 2007 292 274
US-A1- 2010 000 227
WO-A1-2011/138571
JP-A- H09 242 957
US-A- 6 123 170
US-A1- 2007 086 854
US-A1- 2009 098 337
US-B2- 7 402 022
  
      
    Note: Within nine months from the publication of the mention of the grant of the European patent, any person may give notice to the European Patent Office of opposition to the European patent granted. Notice of opposition shall be filed in a written reasoned statement. It shall not be deemed to have been filed until the opposition fee has been paid. (Art. 99(1) European Patent Convention).


    Description

    BACKGROUND



    [0001] This disclosure generally pertains to an attachment flange for a composite fan case. Furthermore, this disclosure relates to a metallic attachment flange component for a composite fan case.

    [0002] A gas turbine engine can include a fan section including fan blades surrounded by a fan case supported within a nacelle. The function of the fan case is to contain any fractured and separated parts of the fan blades to prevent portions from leaving the fan nacelle. Metallic fan cases can be undesirably heavy to perform this containment function. A composite fan case constructed of non-metallic materials can reduce weight and provide the same capability as a metallic fan case. However, composite fan cases can require complicated configurations to provide the desired strength and durability. Moreover, composite material manufacturing and forming techniques are limited in the range of tolerances that can be reliably obtained.

    [0003] US 2007/0086854 discloses a fan containment case in accordance with the preamble of claim 1, and a method in accordance with the preamble of claim 10.

    [0004] A known fan containment case is also disclosed in US 2010/0000227.

    SUMMARY



    [0005] In accordance with the present invention, there is provided a fan containment case as set forth in claim 1 and a method of manufacturing a fan containment case as set forth in claim 10.

    [0006] A disclosed fan containment case includes a fan case fabricated from a plurality of non-metallic composite layers with an attachment flange formed of both a composite portion and a metallic backing.

    [0007] The metallic backing is mounted on a rearward facing surface of the composite portion of the attachment flange. The disclosed metallic backing includes a plurality of segments that combine to encircle the fan case on the attachment flange. The metallic backings are secured to the attachment flange with an adhesive and/or mechanical fasteners. The metallic backing provides a desired compression strength and durability along with the use of conventional machining processes to attain a desired total thickness of the attachment flange within desired tolerance limits.

    [0008] These and other features disclosed herein can be best understood from the following specification and drawings, the following of which is a brief description.

    BRIEF DESCRIPTION OF THE DRAWINGS



    [0009] 

    Figure 1 is a schematic view of an example gas turbine engine.

    Figure 2 is a perspective view of an example containment case.

    Figure 3 is a sectional view of the example containment case.

    Figure 4 is an enlarged view of an embodiment of an attachment flange of a fan containment case in accordance with the present invention.

    Figure 5 is an enlarged cross-section of a portion of an embodiment of the attachment flange.

    Figure 6 is a front view of an embodiment of a metallic backer segment.

    Figure 7 is a perspective view of the metallic backer segment.


    DETAILED DESCRIPTION



    [0010] Referring to Figure 1, a gas turbine engine is schematically indicated at 10 and includes a core 12 having a compressor section 14, a combustion section 16 and a turbine section 18. The example gas turbine engine 10 includes a fan section 20 that is disposed within a nacelle 22 and includes a plurality of blades 28. The compressor, combustion, turbine, and fan sections 14, 16 18 and 20 are arranged about an axis 15. The nacelle 22 defines an inlet 24 for incoming airflow. A fan containment case 26 is disposed proximate the blades 28 in the fan section 20.

    [0011] Referring to Figures 2 and 3, the example fan containment case 26 includes a generally cylindrically shaped fan case 30 that extends between an open front end 34 and an open rear end 36. The example fan case 30 is fabricated from a plurality of non-metallic composite layers 38 (Figure 4). The front end 34 includes an attachment flange 32 that is formed of the plurality of composite layers 38. A metallic backing 42 is secured to the attachment flange 32.

    [0012] The example metallic backing 42 is fabricated from an aluminum material and is mounted on an axially rearward facing surface of the attachment flange 32. The example metallic backing 42 consists of a plurality of segments 52 that combine to encircle the fan case 30 on the attachment flange 32. In the disclosed example, the metallic backing 42 includes four segments 52 disposed about the circumference of the fan case 30 and secured to the attachment flange 32.

    [0013] The attachment flange 32 includes openings 46 (best shown in Figure 4) that extend through the metallic backing 42 and the composite attachment flange 32. The openings 46 are provided for the fasteners (not shown) utilized for securing the containment case 26 within the nacelle 22. The rear end 36 of the fan case 26 does not include an attachment flange and is secured to the nacelle structure 22 using other attachment and securement methods. However, it is within the contemplation of this disclosure that an attachment flange 32 may be disposed on each of the front and rear ends 34, 36 in order to secure the fan case 30 within the nacelle structure 22.

    [0014] Referring to Figures 4 and 5 with continued reference to Figure 2, the metallic backings 42 are secured to the attachment flange 32 with an adhesive 56 and/or mechanical fasteners 54. The example mechanical fasteners 54 comprise rivets that extend through the metallic backing 42 and into the composite portion of the attachment flange 32. The metallic backing includes counter-bore holes 48 that receive the entire head of the rivet 54 such that the rivet head does not protrude from the metallic backing 42.

    [0015] Referring to Figures 4 and 5 with continued reference to Figure 2, the fan case 30 in accordance with the present invention includes the front end 34 that is defined by the attachment flange 32. The attachment flange 32 includes a radially upward extending composite portion 40. This radially upward extending composite portion 40 is formed from some or all of the plurality of layers 38 of the fan case 30. The composite portion 40 includes the composite material that is non-metallic and therefore is formed utilizing known composite manufacturing techniques.

    [0016] An embodiment of the composite portion 40 extends radially upward with a bend radius 58 that is determined according to the material properties of the composite layers 38 to provide the desired strength and formation of the attachment flange 32. Disposed between the metallic backing 42 and the composite portion 40 is a galvanic corrosion barrier 44. The combination of the metallic backing 42 with the composite portion 40 creates a galvanic corrosion condition encountered by responsive to direct contact between the two materials. The galvanic corrosion barrier 44 prevents degradation that may be caused by the galvanic incompatibility of the materials. The adhesive 56 is disposed between the galvanic barrier 44 and the metallic backing 42 to hold the metallic backing 42 in place during assembly and operation.

    [0017] The metallic backing 42 and the composite portion 40 define openings 46 for fasteners utilized to secure the containment case 26 within the nacelle 22. The metallic backing 42 includes a radius 60 that corresponds to the radius 58 of the composite portion 40. The radius 60 provides for the positioning of the metallic backing 42 further downwardly towards the outer surface of the fan case 30. Moreover, the radius 58 provides an increased area of compression contact in the radius to provide a desired increase in compression strength.

    [0018] Referring to Figures 6 and 7 with continued reference to Figure 2, the metallic backing 42 is shown and includes several features to maintain the desired structural integrity while reducing overall weight. The example metallic backing 42 is formed from an aluminum alloy to provide a desired strength to weight ratio. Each segment 52 of the metallic backing 42 may include scalloped portions 50. The scalloped portions 50 are areas where material is removed to reduce the overall weight of each of the metallic backing 42.

    [0019] Referring to Figure 4, with continued reference to Figures 6 and 7, the metallic backing 42 is secured to the attachment flange 32 by way of the adhesive 56 that is applied between the composite portion 40 and the metallic backing 42. The example adhesive 56 is applied to the front surface of the metallic backing 42 that will be placed in contact with the galvanic corrosion barrier 44 on the axially rearward facing surface of the composite portion 40.

    [0020] In addition to the adhesive 56, the mechanical fasteners 54 (Figure 2) are utilized to secure the metallic backing 42 to the composite portion 40 of the attachment flange 32. The example mechanical fasteners 54 are rivets secured through counter-bore holes 48 arranged at intervals along the length of each metallic backing 42. The counter-bore holes 48 allow for attachment of the rivets 54 without disrupting the rear axially facing surface of the metallic backing 42 during assembly and secondary machining.

    [0021] Metallic backing 42 is provided in segments 52 to allow for manufacturability and installation to the fan case 30. In the disclosed example, there are four segments 52 (Figure 2) of metallic backing 42 that are applied and attached to the attachment flange 32. Each segment 52 comprises a circumferential portion that combine to encircle the fan case 30 and form a semi-continuous mounting surface along the entire rearward facing surface of the attachment flange 32.

    [0022] The metallic backing 42 is metallic part and therefore is readily machinable by common manufacturing methods. Therefore, the metallic backing 42 provides a surface from which material can be removed to set a desired thickness 62 of the attachment flange 32. As appreciated, the desired thickness 62 of the attachment flange 32 is difficult to attain merely through the use of composite materials. Composite materials are not easy to machine compared to the metallic material comprising the metallic backing 42.

    [0023] The fan containment case 26 according to the present invention is fabricated by first producing the fan case 30 to include the attachment flange portion 40 that extends radially upward. The composite portion 40 of the attachment flange 32 includes the radius 58 that terminates at a first thickness 64. This first thickness 64 is formed within a desired tolerance range compatible with the composite material forming process. A second thickness 66 of the metallic backing 42 is provided such that sufficient material is provided in view of the tolerance range of the first thickness 64 defined by the composite material forming process. In other words, sufficient material is provided in the second thickness 66 of the metallic backing 42 such that a rear face 68 is machined to attain the desired total thickness 62 of the attachment flange 32. The metallic backing 42 because it is machinable by known and substantially standard conventional machining methods allows for the tailoring of the thickness 62 of the attachment flange 32 beyond the limits capable with only composite material fabrication techniques.

    [0024] The galvanic corrosion barrier 44 is attached to the composite portion 40 followed by attachment of the metallic backing 42 with the adhesive 56. Rivets 54 are then utilized to further attach the metallic backing 42 to the composite portion 40. The rivets 54 are attached within the counter-bore holes 48 such that the rivets 54 do not interfere with subsequent machining steps. Once the metallic backing 42 is attached to the composite portion 40, the back surface 68 is machined to obtain the desired total thickness 62 of the completed attachment flange 32. The machining operation can include any machining operation capable of removing material from the back surface 68 to obtain the total thickness within a desired tolerance range.

    [0025] Accordingly, the disclosed attachment flange 32 configuration including the metallic backing 42 provides for the tailoring of attachment flange dimensions to obtain desired dimensional repeatability. Moreover, the metallic backing 42 increases compression strength in the attachment flange 42 to facilitate increased durability while also improving manufacture and assembly.


    Claims

    1. A fan containment case (26) comprising:

    a plurality of non-metallic composite layers (38) defining a generally cylindrical case (30);

    an attachment flange (32) for securing the fan containment case (26) within a nacelle, the attachment flange (32) extending radially outward from the cylindrical case (30), the attachment flange (32) comprising a portion (40) of the plurality of composite layers (38) defining the cylindrical case (30), a first, axially forward facing surface for securing to a nacelle, and a second, axially rearward facing surface opposite the first surface; and

    a metallic backing (42) secured to the second surface of the attachment flange (32) to form a combined flange, characterised in that:
    the metallic backing (42) is secured to the attachment flange (32) with an adhesive (56) and/or mechanical fasteners (54), wherein the metallic backing (42) includes a thickness (66) and an axially rear face (68) that is machined after attachment to the attachment flange (32) to obtain a desired total thickness (62) of the combined flange without machining of the plurality of composite layers (38).


     
    2. The fan containment case as recited in claim 1, wherein the metallic backing (42) comprises at least two separate segments (52) secured to the attachment flange (32), wherein each of the at least two separate segments (52) comprise a circumferential portion that combine to encircle the cylindrical case (30) and form a semi-continuous mounting surface along the entire second surface of the attachment flange (32).
     
    3. The fan containment case as recited in claim 1 or 2, wherein the attachment flange (32) and the metallic backing (42) include a plurality of corresponding openings (48) for receiving the mechanical fasteners (54).
     
    4. The fan containment case as recited in claim 3, wherein the openings (48) are counter-bore holes (48).
     
    5. The fan containment case as recited in any preceding claim, wherein the mechanical fasteners (54) comprise a plurality of rivets (54).
     
    6. The fan containment case as recited in any preceding claim, including a galvanic corrosion barrier (44) secured between the metallic backing (42) and the attachment flange (32).
     
    7. The fan containment case as recited in any preceding claim, including a radius (58) between the attachment flange (32) and the outer surface of cylindrical case (30), the metallic backing (42) including a corresponding radius (60).
     
    8. A gas turbine engine fan section (20) comprising:

    a fan containment case (26) as recited in any preceding claim; and

    a plurality of fan blades (28) disposed within the generally cylindrical case (30).


     
    9. The gas turbine engine fan section as recited in claim 8 including a nacelle (22) disposed about the fan section (20) with the cylindrical case (30) supported by the nacelle (22).
     
    10. A method of manufacturing a fan containment case (26) comprising:

    forming a generally cylindrical case (30) with a plurality of non-metallic composite layers (38);

    forming an attachment flange (32) by extending at least a portion (40) of the plurality of composite layers (38) radially outward from the cylindrical case (30), the attachment flange (32) comprising a first, axially forward facing surface for securing to a nacelle, and a second, axially rearward facing surface opposite the first surface; and

    attaching a metallic backing (42) to the second surface of the attachment flange (32) to form a combined flange, characterised in that:

    the metallic backing (42) is attached to the formed portion of the attachment flange (32) with an adhesive (56) and/or mechanical fasteners (54); and

    machining an axially rear face (68) of the metallic backing (42) after attachment to the attachment flange (32) to obtain a desired total thickness (62) of the combined flange without machining of the plurality of composite layers (38).


     
    11. The method as recited in claim 10, wherein the mechanical fasteners (54) comprise a plurality of rivets (54).
     
    12. The method as recited in claim 10 or 11 including attaching a galvanic corrosion barrier (44) between the metallic backing (42) and the attachment flange (32).
     


    Ansprüche

    1. Fangehäuse (26) mit Berstschutz, umfassend:

    eine Vielzahl von nicht-metallischen Verbundstoffschichten (38), die ein allgemein zylindrisches Gehäuse (30) definiert;

    einen Befestigungsflansch (32) zum Sichern des Fangehäuses (26) mit Berstschutz innerhalb einer Triebwerksgondel, wobei sich der Befestigungsflansch (32) von dem zylindrischen Gehäuse (30) radial nach außen erstreckt, wobei der Befestigungsflansch (32) einen Abschnitt (40) der Vielzahl von Verbundstoffschichten (38), die das zylindrische Gehäuse (30) definiert, eine erste, axial nach vorne weisende Fläche zum Sichern an einer Triebwerksgondel und eine zweite, axial nach hinten weisende Fläche gegenüber der ersten Fläche umfasst; und

    einen metallischen Verstärkungsrahmen (42), der an der zweiten Fläche des Befestigungsflansches (32) gesichert ist, um einen kombinierten Flansch zu bilden, dadurch gekennzeichnet, dass:
    der metallische Verstärkungsrahmen (42) mit einem Klebstoff (56) und/oder mechanischen Befestigungselementen (54) an dem Befestigungsflansch (32) gesichert ist, wobei der metallische Verstärkungsrahmen (42) eine Dicke (66) und eine axial rückseitige Fläche (68), die nach der Befestigung an dem Befestigungsflansch (32) maschinell bearbeitet wird, beinhaltet, um eine gewünschte Gesamtdicke (62) des kombinierten Flansches zu erlangen, ohne die Vielzahl von Verbundstoffschichten (38) maschinell zu bearbeiten.


     
    2. Fangehäuse mit Berstschutz nach Anspruch 1, wobei der metallische Verstärkungsrahmen (42) mindestens zwei getrennte Segmente (52) umfasst, die an dem Befestigungsflansch (32) gesichert sind, wobei jedes der mindestens zwei getrennten Segmente (52) einen Umfangsabschnitt umfasst, der kombiniert wird, um das zylindrische Gehäuse (30) zu umschließen und eine semikontinuierliche Montagefläche entlang der gesamten zweiten Fläche des Befestigungsflansches (32) zu bilden.
     
    3. Fangehäuse mit Berstschutz nach Anspruch 1 oder 2, wobei der Befestigungsflansch (32) und der metallische Verstärkungsrahmen (42) eine Vielzahl von entsprechenden Öffnungen (48) zum Aufnehmen der mechanischen Befestigungselemente (54) beinhalten.
     
    4. Fangehäuse mit Berstschutz nach Anspruch 3, wobei die Öffnungen (48) Senkbohrungslöcher (48) sind.
     
    5. Fangehäuse mit Berstschutz nach einem der vorstehenden Ansprüche, wobei die mechanischen Befestigungselemente (54) eine Vielzahl von Nieten (54) umfassen.
     
    6. Fangehäuse mit Berstschutz nach einem der vorstehenden Ansprüche, beinhaltend eine galvanische Korrosionssperre (44), die zwischen dem metallischen Verstärkungsrahmen (42) und dem Befestigungsflansch (32) gesichert ist.
     
    7. Fangehäuse mit Berstschutz nach einem der vorstehenden Ansprüche, beinhaltend einen Radius (58) zwischen dem Befestigungsflansch (32) und der Außenfläche des zylindrischen Gehäuses (30), wobei der metallische Verstärkungsrahmen (42) einen entsprechenden Radius (60) beinhaltet.
     
    8. Fanbereich (20) eines Gasturbinentriebwerks, umfassend:

    ein Fangehäuse (26) mit Berstschutz nach einem der vorstehenden Ansprüche; und

    eine Vielzahl von Fanflügeln (28), die innerhalb des allgemein zylindrischen Gehäuses (30) angeordnet ist.


     
    9. Fanbereich eines Gasturbinentriebwerks nach Anspruch 8, beinhaltend eine Triebwerksgondel (22), die um den Fanbereich (20) herum angeordnet ist, wobei das zylindrische Gehäuse (30) durch die Triebwerksgondel (22) gelagert ist.
     
    10. Verfahren zum Herstellen eines Fangehäuses (26) mit Berstschutz, umfassend:

    Bilden eines allgemein zylindrischen Gehäuses (30) mit einer Vielzahl von nicht-metallischen Verbundstoffschichten (38) ;

    Bilden eines Befestigungsflansches (32) durch Verlängern mindestens eines Abschnitts (40) der Vielzahl von Verbundstoffschichten (38) radial nach außen von dem zylindrischen Gehäuse (30), wobei der Befestigungsflansch (32) eine erste, axial nach vorne weisende Fläche zum Sichern an einer Triebwerksgondel und eine zweite, axial nach hinten weisende Fläche gegenüber der ersten Fläche umfasst; und

    Befestigen eines metallischen Verstärkungsrahmens (42) an der zweiten Fläche des Befestigungsflansches (32), um einen kombinierten Flansch zu bilden, dadurch gekennzeichnet, dass:

    der metallische Verstärkungsrahmen (42) mit einem Klebstoff (56) und/oder mechanischen Befestigungselementen (54) an dem gebildeten Abschnitt des Befestigungsflansches (32) befestigt ist; und

    maschinelles Bearbeiten einer axial rückseitigen Fläche (68) des metallischen Verstärkungsrahmens (42) nach der Befestigung an dem Befestigungsflansch (32), um eine gewünschte Gesamtdicke (62) des kombinierten Flansches zu erlangen, ohne die Vielzahl von Verbundstoffschichten (38) maschinell zu bearbeiten.


     
    11. Verfahren nach Anspruch 10, wobei die mechanischen Befestigungselemente (54) eine Vielzahl von Nieten (54) umfassen.
     
    12. Verfahren nach Anspruch 10 oder 11, beinhaltend Befestigen einer galvanischen Korrosionssperre (44) zwischen dem metallischen Verstärkungsrahmen (42) und dem Befestigungsflansch (32) .
     


    Revendications

    1. Carter de rétention de soufflante (26) comprenant :

    une pluralité de couches composites non-métalliques (38) définissant un carter généralement cylindrique (30) ;

    une bride de fixation (32) pour le blocage du carter de rétention de soufflante (26) à l'intérieur d'une nacelle, la bride de fixation (32) s'étendant radialement vers l'extérieur depuis le carter cylindrique (30), la bride de fixation (32) comprenant une portion (40) de la pluralité de couches composites (38) définissant le carter cylindrique (30), une première surface tournée axialement vers l'avant pour le blocage sur une nacelle, et une deuxième surface tournée axialement vers l'arrière opposée à la première surface ; et

    un cadre de renforcement métallique (42) bloqué sur la deuxième surface de la bride de fixation (32) pour former une bride combinée, caractérisé en ce que :
    le cadre de renforcement métallique (42) est bloqué sur la bride de fixation (32) avec un adhésif (56) et/ou des éléments de fixation mécaniques (54), dans lequel le cadre de renforcement métallique (42) inclut une épaisseur (66) et une face axialement arrière (68) qui est usinée après fixation à la bride de fixation (32) pour obtenir une épaisseur totale souhaitée (62) de la bride combinée sans usinage de la pluralité de couches composites (38).


     
    2. Carter de rétention de soufflante selon la revendication 1, dans lequel le cadre de renforcement métallique (42) comprend au moins deux segments séparés (52) bloqués sur la bride de fixation (32), dans lequel chacun des au moins deux segments séparés (52) comprend une portion circonférentielle qui se combinent pour encercler le carter cylindrique (30) et former une surface de montage semi-continue le long de toute la deuxième surface de la bride de fixation (32).
     
    3. Carter de rétention de soufflante selon la revendication 1 ou 2, dans lequel la bride de fixation (32) et le cadre de renforcement métallique (42) incluent une pluralité d'ouvertures (48) correspondantes pour la réception des éléments de fixation mécaniques (54).
     
    4. Carter de rétention de soufflante selon la revendication 3, dans lequel les ouvertures (48) sont des trous lamés (48).
     
    5. Carter de rétention de soufflante selon une quelconque revendication précédente, dans lequel les éléments de fixation mécaniques (54) comprennent une pluralité de rivets (54).
     
    6. Carter de rétention de soufflante selon une quelconque revendication précédente, incluant une barrière de corrosion galvanique (44) bloquée entre le cadre de renforcement métallique (42) et la bride de fixation (32).
     
    7. Carter de rétention de soufflante selon une quelconque revendication précédente, incluant un rayon (58) entre la bride de fixation (32) et la surface extérieure du carter cylindrique (30), le cadre de renforcement métallique (42) incluant un rayon (60) correspondant.
     
    8. Section de soufflante de moteur à turbine à gaz (20) comprenant :

    un carter de rétention de soufflante (26) selon une quelconque revendication précédente ; et

    une pluralité de pales de soufflante (28) disposées à l'intérieur du carter généralement cylindrique(30).


     
    9. Section de soufflante de moteur à turbine à gaz selon la revendication 8 incluant une nacelle (22) disposée autour de la section de soufflante (20) avec le carter cylindrique (30) supporté par la nacelle (22).
     
    10. Procédé de fabrication d'un carter de rétention de soufflante (26) comprenant :

    la formation d'un carter généralement cylindrique (30) avec une pluralité de couches composites non-métalliques (38) ;

    la formation d'une bride de fixation (32) par extension d'au moins une portion (40) de la pluralité de couches composites (38) radialement vers l'extérieur depuis le carter cylindrique (30), la bride de fixation (32) comprenant une première surface tournée axialement vers l'avant pour le blocage sur une nacelle, et une deuxième surface tournée axialement vers l'arrière opposée à la première surface ; et

    la fixation d'un cadre de renforcement métallique (42) sur la deuxième surface de la bride de fixation (32) pour former une bride combinée, caractérisé en ce que :

    le cadre de renforcement métallique (42) est fixé sur la portion formée de la bride de fixation (32) avec un adhésif (56) et/ou des éléments de fixation mécaniques (54) ; et

    l'usinage d'une face axialement arrière (68) du cadre de renforcement métallique (42) après fixation à la bride de fixation (32) pour obtenir une épaisseur totale souhaitée (62) de la bride combinée sans usinage de la pluralité de couches composites (38).


     
    11. Procédé selon la revendication 10, dans lequel les éléments de fixation mécaniques (54) comprennent une pluralité de rivets (54).
     
    12. Procédé selon la revendication 10 ou 11, incluant la fixation d'une barrière de corrosion galvanique (44) entre le cadre de renforcement métallique (42) et la bride de fixation (32).
     




    Drawing














    Cited references

    REFERENCES CITED IN THE DESCRIPTION



    This list of references cited by the applicant is for the reader's convenience only. It does not form part of the European patent document. Even though great care has been taken in compiling the references, errors or omissions cannot be excluded and the EPO disclaims all liability in this regard.

    Patent documents cited in the description