EP2861849B1 - Aube, moteur à turbine et procédé associé d'assemblage d'une aube - Google Patents

Aube, moteur à turbine et procédé associé d'assemblage d'une aube Download PDF

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Publication number
EP2861849B1
EP2861849B1 EP13807627.8A EP13807627A EP2861849B1 EP 2861849 B1 EP2861849 B1 EP 2861849B1 EP 13807627 A EP13807627 A EP 13807627A EP 2861849 B1 EP2861849 B1 EP 2861849B1
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EP
European Patent Office
Prior art keywords
shroud
airfoil
fitting
recited
adhesively bonded
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
EP13807627.8A
Other languages
German (de)
English (en)
Other versions
EP2861849A4 (fr
EP2861849A1 (fr
Inventor
Nicholas D. Stilin
Jeremy L. Fox
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.)
RTX Corp
Original Assignee
United Technologies Corp
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
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Publication of EP2861849A1 publication Critical patent/EP2861849A1/fr
Publication of EP2861849A4 publication Critical patent/EP2861849A4/fr
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Publication of EP2861849B1 publication Critical patent/EP2861849B1/fr
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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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • 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
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
    • Y10T156/10—Methods of surface bonding and/or assembly therefor

Definitions

  • This disclosure relates to improvements in shrouded airfoils.
  • Airfoils such as airfoils in gas turbine engines, may include a shroud at an inner diameter, outer diameter or both.
  • the airfoils are circumferentially arranged such that inner diameter shrouds bound an inner diameter of a gas path and outer diameter shrouds bound an outer diameter of the gas path.
  • the airfoils are secured to static structures, such as cases, using fittings at the inner and outer diameters.
  • the fittings and shrouds are integrally formed in a forging process from a suitable metallic alloy or are integrally formed by machining from a single monolithic piece of a suitable metallic alloy.
  • An airfoil having the features of the preamble of claim 1 is disclosed in WO 96/04468 A1 .
  • a stator element comprising an array of fixed blades mounted on a ring is disclosed in US 5083900 A .
  • the present invention provides, in an exemplary aspect an airfoil as set forth in claim 1.
  • the at least one shroud may comprise a polymeric material.
  • the at least one fitting may be metallic and the at least one shroud be polymeric.
  • a further non-limiting embodiment of any of the foregoing examples comprises of a seal member attached at an edge of the at least one shroud.
  • the edge of the at least one shroud may include a slot, and the seal member be located in the slot.
  • the seal member may be adhesively bonded to the edge of the at least one shroud.
  • the at least one shroud may include a plurality of distinct shroud pieces that, when assembled together, circumscribe the at least one fitting.
  • the at least one shroud may include a shroud body extending between first and second broadsides, perimeter edges and interior edges that define an elongated, arcuate opening extending between the first and second broadsides.
  • the invention also provides a turbine engine as set forth in claim 9.
  • the invention also provides a method of assembling an airfoil according to claim 10.
  • FIG. 1 schematically illustrates a gas turbine engine 20.
  • the gas turbine engine 20 disclosed herein is a two-spool turbofan that generally includes a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28 that are arranged along a central axis A.
  • the illustrated example is a turbofan gas turbine engine and the examples herein are described with reference to an airfoil in the engine 20, it is to be understood that this disclosure is not limited to gas turbine engines or turbine engine airfoils.
  • the teachings herein can be applied to other types of shrouded airfoils and turbine engines, including single- or three-spool architectures.
  • the fan section 22 of the gas turbine engine 20 includes a plurality of rotatable blades 30 and a plurality of static, structural exit guide vanes 32.
  • the vanes 32 are circumferentially arranged around the central axis A between an outer structure 34 and an inner structure 36, such as cases.
  • Figure 2 shows an example of one of the vanes 32, which is considered to be an airfoil.
  • the vane 32 includes an airfoil body 40 that extends between a leading edge 42 and the trailing edge 44, a suction side 46 and a pressure side 48, and a first end 50 and a second end 52. Relative to the central axis A, the first end 50 is an outer diameter end of the vane 32 and the second end 52 is an inner diameter end of the vane 32.
  • the vane 32 further includes a first fitting 54a located at the first end 50 and a second fitting 54b located at the second end 52.
  • Each of the fittings 54a/54b is or includes a metallic material and includes one or more mounting lugs 56 for securing the vane 32 to the respective structures 34/36 in a known manner, such as by using fasteners.
  • the vane 32 further includes a first shroud 58a that is adhesively bonded to the first fitting 54a and a second shroud 58b that is adhesively bonded to the second fitting 54b.
  • first shroud 58a that is adhesively bonded to the first fitting 54a
  • second shroud 58b that is adhesively bonded to the second fitting 54b.
  • the vane 32 is shrouded at both the first end 50 and the second end 52. It is to be understood, however, that other types of airfoils may be shrouded at only one end, and that the examples herein are also applicable to such airfoils.
  • shrouds 58a/58b that are separate and distinct pieces from the airfoil body 40 and the respective fittings 54a/54b permits the shrouds 58a/58b to be made of different material than either the airfoil body 40 or the fittings 54a/54b.
  • FIGS 3 and 4 show isolated views, respectively, of the first fitting 54a and the second fitting 54b.
  • each of the fittings 54a/54b is a separate and distinct piece from the airfoil body 40.
  • each of the fittings 54a/54b includes a corresponding pocket 60 into which the airfoil body 40 is received.
  • the airfoil body 40 can be adhesively bonded to the respective fittings 54a/54b.
  • the fittings 54a/54b can be integral with the airfoil body 40.
  • Figures 5 and 6 show isolated views, respectively, of the shrouds 58a/58b adhesively bonded to the fittings 54a/54b.
  • Figure 7 shows a cross-section through an interface between the second fitting 54b and the second shroud 58b adhesively bonded to the second fitting 54b. It is to be understood that the interface between the first fitting 54a and the first shroud 58a is similar to the interface shown in Figure 7 .
  • the second shroud 58a is adhesively bonded to the second fitting 54b by an adhesive 70.
  • the adhesive 70 is an epoxy adhesive. In other examples, other types of adhesives can be used that are suitable for the expected operating temperature of the airfoil.
  • the second fitting 54b includes a flange F to which the second shroud 58a is adhesively bonded.
  • the flange F includes a rabbet 54b'.
  • the rabbet 54b' or ledge, supports the adhesive 70 for bonding the second shroud 58b thereto.
  • the second shroud 58b is adhesively bonded to the rabbet 54b'.
  • a method of assembling the vane 32 therefore includes providing the vane 32 as described, and adhesively bonding the shrouds 58a/58b to the fittings 54a/54b.
  • Figure 8 shows an isolated view of the first shroud 58a.
  • the first shroud 58a includes a shroud body 72 that extends between first and second broadsides 74a/74b, perimeter edges 76, which are axially and circumferentially facing surfaces, and interior edges 78 that define an elongated, arcuate opening 80 extending between the first and second broadsides 74a/74b.
  • the opening 80 is generally elongated in a direction parallel to the central axis A of the gas turbine engine 20.
  • the opening 80 also has the arcuate shape, which corresponds to the arcuate shape of the cross-section of the airfoil body 40.
  • the first shroud 58 also optionally includes a plurality of additional openings 82 that correspond to the mounting lugs 56 on the first fitting 54a. Depending on the geometry of the first shroud 58a and location of the mounting lugs 56, other examples may exclude the additional openings 82.
  • the second shroud 58b has similar features as the first shroud 58a with regard to including a shroud body, first and second broadsides, perimeter edges and interior edges that define an elongated, arcuate opening.
  • the contouring and size of the second shroud 58b may differ and the elongated, arcuate opening of the second shroud 58b may have a different geometry that corresponds to the cross-section of the airfoil body 40 at the inner diameter.
  • the additional optional openings may be positioned differently to align with the mounting lugs 56 on the second fitting 54b.
  • the first shroud 58a is a monolithic piece. That is, the first shroud 58a is a single piece of material that is free of joints or seams.
  • the airfoil body 40 extends through the elongated, arcuate opening 80 and into the corresponding first fitting 54a (or second fitting 54b for the elongated arcuate opening of the second shroud 58b).
  • Figure 9 shows a modified example of a first shroud 158a.
  • the first shroud 158a includes a plurality of separate and distinct pieces 190a/190b.
  • Each of the pieces 190a/190b includes a portion of the interior edges 78 such that, when assembled together, the pieces 190a/190b define the complete perimeter of the elongated, arcuate opening 80, which circumscribes the first fitting 54a similar to as shown in Figure 6 .
  • the pieces 190a/190b are initially separate and are then assembled around the first fitting 54a and adhesively bonded thereto to form the complete first shroud 158a.
  • the shroud 158a can be fitted onto an existing vane as a retrofit, for example.
  • the use of the separate pieces 190a/190b also facilitates removal of the shroud 158a for replacement with a new, similar shroud, should the shroud 158a require replacement.
  • Figure 10 shows a perspective, sectioned view through a portion of the second fitting 54b.
  • the second shroud 58b further includes a seal member 90 attached at one of the perimeter edges 76 of the second shroud 58b.
  • the second fitting 54b, the second shroud 58b and the seal member 90 are shown in full view in Figure 11 .
  • the first shroud 58a can likewise include a seal member 90.
  • the seal members 90 bear against a neighboring shroud 58a/58b to provide a gas path seal.
  • the seal member 90 is adhesively bonded to the second shroud 58b using an adhesive 90a.
  • the adhesive 90a can be an epoxy adhesive.
  • the adhesive 90a can be another type of adhesive that is suitable for the operating temperature of the airfoil.
  • the seal member 90 can be integrally formed with the second shroud 58b, such as in a co-molding or over-molding operation.
  • Figure 13 shows a portion of a modified first shroud 258a.
  • the first shroud 258a includes a slot S extending into one of the perimeter edges 76.
  • the seal member 90 includes a flange 90' that is received into the slot S to secure the seal member 90 and the first shroud 258a together.
  • the slot S can be sized in correspondence with the size of the flange 90' such that there is an interference fit or snap fit between the first shroud 258a and the seal member 90.
  • an adhesive can be used to secure the seal member 90 within the slot S.
  • the second shroud 58b can also include a slot for attaching the seal member 90.
  • the shrouds disclosed herein that are separate and distinct pieces from the airfoil body 40 and the respective fittings 54a/54b permits the shrouds to be made of different materials than either the airfoil body 40 or the fittings 54a/54b.
  • the shrouds are, or include, a polymeric material.
  • the polymeric material is a reinforced polymeric material that includes glass fibers, carbon fibers, or other reinforcement additives.
  • the airfoils disclosed herein provide a weight reduction because of the use of the polymeric material.
  • metallic shrouds that are integrally formed with fittings require significant raw material and machining to attain the final geometric configuration.
  • the shrouds disclosed herein can be formed to the required geometry and tolerances using known polymer forming processes, such as injection molding.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (10)

  1. Profil aérodynamique (32) comprenant :
    un corps de profil aérodynamique (40) s'étendant entre un bord d'attaque (42) et un bord de fuite (44), un intrados (46) et un extrados (48), ainsi qu'une première extrémité (50) et une seconde extrémité (52) ;
    au moins un raccord (54a, 54b) situé sur au moins l'une de la première extrémité (50) et de la seconde extrémité (52), l'au moins un raccord (54a, 54b) comportant au moins une patte de montage (56) ; et
    au moins une enveloppe (58a, 58b) liée de manière adhésive à au moins un raccord (54a, 54b) ;
    caractérisé en ce que :
    l'au moins un raccord (54a, 54b) comporte une bride (F), et l'au moins une enveloppe (58a, 58b) est liée de manière adhésive à la bride, et la bride (F) comporte une feuillure (54b'), et l'au moins une enveloppe (58a, 58b) est liée de manière adhésive à la feuillure (54b').
  2. Profil aérodynamique selon une quelconque revendication précédente, dans lequel l'au moins une enveloppe (58a, 58b) comprend un matériau polymère.
  3. Profil aérodynamique selon la revendication 1 ou 2, dans lequel l'au moins un raccord (54a, 54b) est métallique et l'au moins une enveloppe est polymère.
  4. Profil aérodynamique selon une quelconque revendication précédente, comprenant en outre un élément d'étanchéité (90) fixé sur un bord de l'au moins une enveloppe (58a, 58b ; 258a).
  5. Profil aérodynamique selon la revendication 4, dans lequel le bord de l'au moins une enveloppe (258a) comporte une fente (S), et l'élément d'étanchéité (90) est situé dans la fente (S).
  6. Profil aérodynamique selon la revendication 5, dans lequel l'élément d'étanchéité (90) est lié de manière adhésive au bord de l'au moins une enveloppe (58b).
  7. Profil aérodynamique selon une quelconque revendication précédente, dans lequel l'au moins une enveloppe (158a) comporte une pluralité de pièces d'enveloppe distinctes (190a, 190b) qui, lorsqu'elles sont assemblées, entourent l'au moins un raccord (54a, 54b).
  8. Profil aérodynamique selon une quelconque revendication précédente, dans lequel l'au moins une enveloppe (58a, 58b) comporte un corps d'enveloppe (72) s'étendant entre des premier et second côtés larges (74a, 74b), des bords périmétriques (76) et des bords intérieurs (78) qui définissent une ouverture arquée allongée (80) s'étendant entre les premier et second côtés larges (74a, 74b).
  9. Moteur à turbine (20), comprenant :
    une section de soufflante (22) ;
    une section de compresseur (24) en communication avec la section de soufflante (22) ;
    une chambre de combustion (26) en communication fluidique avec la section de compresseur (24) ; et
    une section de turbine (28) en communication fluidique avec la chambre de combustion (26) ;
    dans lequel la section de soufflante (22) comporte un profil aérodynamique selon l'une quelconque des revendications 1 à 8.
  10. Procédé d'assemblage d'un profil aérodynamique (32), le procédé comprenant :
    la fourniture d'un corps de profil aérodynamique (40) s'étendant entre un bord d'attaque (42) et un bord de fuite (44), un intrados (46) et un extrados (48), ainsi qu'une première extrémité (50) et une seconde extrémité (52), et au moins un raccord (54a, 54b) situé sur au moins l'une de la première extrémité (50) et de la seconde extrémité (52), l'au moins un raccord (54a, 54b) comportant au moins une patte de montage (56) ; et
    la liaison adhésive d'au moins une enveloppe (58a, 58b) à l'au moins un raccord (54a, 54b) ;
    caractérisé en ce que :
    l'au moins un raccord (54a, 54b) comporte une bride (F), et l'au moins une enveloppe (58a, 58b) est liée de manière adhésive à la bride, et la bride (F) comporte une feuillure (54b'), et l'au moins une enveloppe (58a, 58b) est liée de manière adhésive à la feuillure (54b').
EP13807627.8A 2012-06-19 2013-06-03 Aube, moteur à turbine et procédé associé d'assemblage d'une aube Active EP2861849B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/527,036 US20130333350A1 (en) 2012-06-19 2012-06-19 Airfoil including adhesively bonded shroud
PCT/US2013/043815 WO2013191877A1 (fr) 2012-06-19 2013-06-03 Surface portante comprenant un carénage à liaison adhésive

Publications (3)

Publication Number Publication Date
EP2861849A1 EP2861849A1 (fr) 2015-04-22
EP2861849A4 EP2861849A4 (fr) 2015-10-21
EP2861849B1 true EP2861849B1 (fr) 2019-12-11

Family

ID=49754653

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13807627.8A Active EP2861849B1 (fr) 2012-06-19 2013-06-03 Aube, moteur à turbine et procédé associé d'assemblage d'une aube

Country Status (3)

Country Link
US (1) US20130333350A1 (fr)
EP (1) EP2861849B1 (fr)
WO (1) WO2013191877A1 (fr)

Families Citing this family (7)

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Publication number Priority date Publication date Assignee Title
US8998575B2 (en) * 2011-11-14 2015-04-07 United Technologies Corporation Structural stator airfoil
WO2014055109A1 (fr) 2012-10-01 2014-04-10 United Technologies Corporation Joint d'étanchéité d'aube directrice
US9963984B2 (en) 2013-03-07 2018-05-08 United Technologies Corporation Structural guide vane for gas turbine engine
JP6167677B2 (ja) * 2013-06-06 2017-07-26 株式会社Ihi ファンにおける翼及びファン
FR3059706B1 (fr) 2016-12-02 2020-10-23 Safran Aircraft Engines Redresseur de flux pour turbomachine a fixation amovible
US10483659B1 (en) * 2018-11-19 2019-11-19 United Technologies Corporation Grounding clip for bonded vanes
DE102019135338A1 (de) * 2019-12-19 2021-06-24 Rolls-Royce Deutschland Ltd & Co Kg Vorrichtung eines Flugtriebwerkes mit einem radial äußeren Gehäusebereich und mit einem radial inneren Gehäuseteil

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US4832568A (en) * 1982-02-26 1989-05-23 General Electric Company Turbomachine airfoil mounting assembly
FR2654463A1 (fr) 1989-11-15 1991-05-17 Snecma Element de stator de turbomachine.
US5411370A (en) 1994-08-01 1995-05-02 United Technologies Corporation Vibration damping shroud for a turbomachine vane
US5562419A (en) * 1995-06-06 1996-10-08 General Electric Company Shrouded fan blisk
US6619917B2 (en) * 2000-12-19 2003-09-16 United Technologies Corporation Machined fan exit guide vane attachment pockets for use in a gas turbine
FR2856749B1 (fr) * 2003-06-30 2005-09-23 Snecma Moteurs Redresseur de compresseur de moteur aeronautique a aubes collees
FR2896548B1 (fr) * 2006-01-24 2011-05-27 Snecma Ensemble de redresseurs fixes sectorise pour un compresseur de turbomachine
US7980817B2 (en) * 2007-04-16 2011-07-19 United Technologies Corporation Gas turbine engine vane
FR2933130B1 (fr) * 2008-06-25 2012-02-24 Snecma Carter structural pour turbomachine
US20100080692A1 (en) * 2008-09-30 2010-04-01 Courtney James Tudor Fairing seal
EP2221454A1 (fr) * 2009-02-24 2010-08-25 Alstom Technology Ltd Aube carénée de turbine à gaz

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Also Published As

Publication number Publication date
EP2861849A4 (fr) 2015-10-21
EP2861849A1 (fr) 2015-04-22
US20130333350A1 (en) 2013-12-19
WO2013191877A1 (fr) 2013-12-27

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