EP1939402A2 - Aube de soufflante en matériau composite pour un moteur à turbine à gaz - Google Patents

Aube de soufflante en matériau composite pour un moteur à turbine à gaz Download PDF

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Publication number
EP1939402A2
EP1939402A2 EP07024380A EP07024380A EP1939402A2 EP 1939402 A2 EP1939402 A2 EP 1939402A2 EP 07024380 A EP07024380 A EP 07024380A EP 07024380 A EP07024380 A EP 07024380A EP 1939402 A2 EP1939402 A2 EP 1939402A2
Authority
EP
European Patent Office
Prior art keywords
fiber composite
composite material
fan blade
enveloping
blade
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.)
Withdrawn
Application number
EP07024380A
Other languages
German (de)
English (en)
Other versions
EP1939402A3 (fr
Inventor
Karl Schreiber
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1939402A2 publication Critical patent/EP1939402A2/fr
Publication of EP1939402A3 publication Critical patent/EP1939402A3/fr
Withdrawn legal-status Critical Current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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor

Definitions

  • the invention relates to a fan blade for a gas turbine engine, which comprises an existing fiber composite material support structure and a metallic shell structure.
  • the fan blades of a fan gas turbine engine are exposed to centrifugal forces, gas pressure and excited by the flowing medium vibrations of the airfoil, but also by impinging foreign body, considerable loads that are transmitted to the blade end held in recesses of the rotor disk.
  • the supporting structure consisting of a fiber composite material is surrounded by a metallic enveloping structure.
  • the invention has for its object to develop from a support structure and a Hüll Quilt existing fan blades that can be produced with little effort and have a long life.
  • the core of the invention is the sheathing of the fiber composite existing support structure with the existing sheet metal envelope structure only in the region of the airfoil, while the blade root consists only of fiber composite material.
  • the enveloping structure is flush with the fiber composite structure of the blade root. It is important that the edge of the envelope structure for voltage reduction in the transition region to the blade root is busy and / or having recesses at regular intervals. With the envelope confined to the airfoil, the tensile forces acting on it are not transferred to the blade root. The high bending load at the transition between the blade root and the blade leaf can not lead to detachment of the enveloping structure from the supporting structure.
  • the blade is produced on the basis of a prefabricated support structure made of fiber composite material which is encased in the airfoil region with the enveloping structure by welding a first cover plate to a leading edge molding and then gluing the support structure thereto. Thereafter, the second cover plate is glued to the still free surface of the support structure and connected by welding to the leading edge molding and the trailing edge of the first cover plate.
  • the second cover sheet is welded to the guide edge molding at a location remote from the support structure, so that the fiber composite material can not be destroyed by the welding heat.
  • the fan blade 1 consists of a support structure 2 not shown in detail from a fiber composite material, here a plurality of superimposed carbon fiber layers with infiltrated plastic in the fiber fabric, and a supporting structure 2 in the region of the airfoil 3 surrounding enveloping structure 4.
  • the envelope structure 4 comprises a metallic leading edge molding 5 and a pressure-side cover plate 6 and a suction-side cover plate 7, which in the present embodiment consist of a titanium alloy.
  • the two cover plates 6, 7 are connected via welds 8, 9 with the leading edge molding 5 and at the opposite ends (not shown) with each other.
  • the enveloping structure 4 delimited on the airfoil, the tensile forces acting on it are not transmitted to the blade root 11. At the blade root 11 thus act only low shear stresses, so that the risk of occurrence of delaminations is significantly reduced. Especially in the transition region between the blade 3 and the blade root 11 large forces are applied by the bending stress occurring there, which can lead to a delamination between the sheet metal casing and the fiber composite material with completely enveloped support structure.
  • the busy training of the enveloping structure 4 (beveled edge 12) at the transition to the blade root 11 is important because at this point only a small voltage overshoot will occur.
  • the supporting structure 2 made of fiber composite material can be produced separately in a tool and the enveloping structure subsequently connected to the supporting structure 2 using a selected ductile adhesive.
  • the possibility of selecting a particularly suitable adhesive independent of the infiltration material also contributes to avoiding delaminations.
  • the leading edge molding 5 is first connected via the weld 8 with the pressure-side cover plate 6 and then the prefabricated in a tool support structure 2 means a special adhesive with the pressure-side cover plate 6 and the leading edge molding 5 is connected.
  • the leading edge molding 5 has a radially extending recess 13, in which the front edge of the suction-side cover plate 7 inserted flush and at its leading edge with the leading edge molding 5, and indeed away from the fiber composite material, is welded (weld 9).
  • the suction-side cover plate 7 was previously bonded to the fiber composite material of the support structure 2 by means of a ductile special adhesive.
  • the opposite ends (not shown) of the two cover sheets 7, 8 can be welded to the edges remote from the fiber composite material so that the welding heat does not act on the fiber composite material.
  • the enveloping structure 4 for the airfoil 3 and to introduce it into a mold and to carry out the infiltration of the synthetic resin after the fiber material has been inserted.
  • the welding of the support structure can be done in this case without regard to the later introduced fiber composite material.
  • the connection between the support structure and enveloping structure with a particularly suitable adhesive is not possible. In this case, the adhesive connection is effected by the infiltrated synthetic resin.
  • Another advantageous effect of the proposed fan blade design is to increase the frictional action between the blade root and the rotor disk because of the combination of the hard metallic rotor disk material with the soft fiber composite material of the blade root. As a result, the wear of the blade root is reduced and thus the life of the fan blade in combination with the effects of the above-mentioned features is further increased overall.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Composite Materials (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Laminated Bodies (AREA)
EP07024380A 2006-12-21 2007-12-17 Aube de soufflante en matériau composite pour un moteur à turbine à gaz Withdrawn EP1939402A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102006061916A DE102006061916A1 (de) 2006-12-21 2006-12-21 Fanschaufel für ein Gasturbinentriebwerk

Publications (2)

Publication Number Publication Date
EP1939402A2 true EP1939402A2 (fr) 2008-07-02
EP1939402A3 EP1939402A3 (fr) 2010-05-05

Family

ID=39203238

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07024380A Withdrawn EP1939402A3 (fr) 2006-12-21 2007-12-17 Aube de soufflante en matériau composite pour un moteur à turbine à gaz

Country Status (3)

Country Link
US (1) US8251664B2 (fr)
EP (1) EP1939402A3 (fr)
DE (1) DE102006061916A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2189627A1 (fr) * 2008-11-25 2010-05-26 Rolls-Royce Deutschland Ltd & Co KG Procédé de fabrication des composantes hybrides pour moteurs de turbine à gaz
WO2014007685A1 (fr) * 2012-07-03 2014-01-09 Gkn Aerospace Sweden Ab Structure de support pour un moteur de turbine à gaz
EP2693061A3 (fr) * 2012-07-30 2014-04-30 Rolls-Royce Deutschland Ltd & Co KG Aube de compresseur d'une turbine à gaz et son procédé de fabrication
CN104603398A (zh) * 2012-09-12 2015-05-06 联合工艺公司 具有蜂窝填料的中空风扇叶片

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2943102B1 (fr) * 2009-03-12 2014-05-02 Snecma Aube en materiau composite comportant un dispositif d'amortissement.
US8585368B2 (en) * 2009-04-16 2013-11-19 United Technologies Corporation Hybrid structure airfoil
US20120021243A1 (en) * 2010-07-23 2012-01-26 General Electric Company Components with bonded edges
CH705171A1 (de) * 2011-06-21 2012-12-31 Alstom Technology Ltd Turbinenschaufel mit einem Schaufelblatt aus Verbundwerkstoff und Verfahren zum Herstellen davon.
US9121294B2 (en) * 2011-12-20 2015-09-01 General Electric Company Fan blade with composite core and wavy wall trailing edge cladding
EP2679776A1 (fr) 2012-06-28 2014-01-01 Alstom Technology Ltd Système de refroidissement et procédé pour turbine à flux axial
DE102012015137A1 (de) * 2012-07-30 2014-02-13 Rolls-Royce Deutschland Ltd & Co Kg Niedermodulige Gasturbinenverdichterschaufel
EP2746428B1 (fr) 2012-12-20 2017-09-13 General Electric Technology GmbH Revêtement de composants de turbine
US10519788B2 (en) * 2013-05-29 2019-12-31 General Electric Company Composite airfoil metal patch
FR3012515B1 (fr) * 2013-10-31 2018-02-09 Safran Aube composite de turbomachine
JP6645986B2 (ja) 2014-05-05 2020-02-14 ホートン， インコーポレイテッド 複合ファン
FR3041684B1 (fr) * 2015-09-28 2021-12-10 Snecma Aube comprenant un bouclier de bord d'attaque et procede de fabrication de l'aube
US11542820B2 (en) * 2017-12-06 2023-01-03 General Electric Company Turbomachinery blade and method of fabricating
US11073027B2 (en) 2018-05-17 2021-07-27 Raytheon Technologies Corporation Mold tool and methods for airfoil bonding
US11136888B2 (en) * 2018-10-18 2021-10-05 Raytheon Technologies Corporation Rotor assembly with active damping for gas turbine engines
CN110439623B (zh) * 2019-08-14 2024-05-14 上海两擎机电科技合伙企业(有限合伙) 飞机发动机风扇叶片用金属包边、加工工装及加工方法

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1450006A1 (fr) * 2003-02-22 2004-08-25 Rolls-Royce Deutschland Ltd & Co KG Aube de compresseur pour un moteur d'avion

Family Cites Families (16)

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US1862579A (en) * 1930-02-11 1932-06-14 Parsons Elastic fluid turbine
GB1088032A (en) * 1964-06-12 1967-10-18 English Electric Co Ltd Turbine blades
US3762835A (en) * 1971-07-02 1973-10-02 Gen Electric Foreign object damage protection for compressor blades and other structures and related methods
US3752600A (en) * 1971-12-09 1973-08-14 United Aircraft Corp Root pads for composite blades
US3799701A (en) * 1972-02-28 1974-03-26 United Aircraft Corp Composite fan blade and method of construction
FR2195255A5 (fr) * 1972-08-04 1974-03-01 Snecma
GB2171151B (en) * 1985-02-20 1988-05-18 Rolls Royce Rotors for gas turbine engines
DE4411679C1 (de) * 1994-04-05 1994-12-01 Mtu Muenchen Gmbh Schaufelblatt in Faserverbundbauweise mit Schutzprofil
FR2732406B1 (fr) * 1995-03-29 1997-08-29 Snecma Aube de turbomachine en materiau composite
US5655883A (en) 1995-09-25 1997-08-12 General Electric Company Hybrid blade for a gas turbine
US5881972A (en) * 1997-03-05 1999-03-16 United Technologies Corporation Electroformed sheath and airfoiled component construction
GB9915637D0 (en) * 1999-07-06 1999-09-01 Rolls Royce Plc A rotor seal
GB0100695D0 (en) * 2001-01-11 2001-02-21 Rolls Royce Plc a turbomachine blade
US6843928B2 (en) 2001-10-12 2005-01-18 General Electric Company Method for removing metal cladding from airfoil substrate
FR2831207B1 (fr) * 2001-10-24 2004-06-04 Snecma Moteurs Plates-formes pour aubes d'un ensemble rotatif
US7189064B2 (en) * 2004-05-14 2007-03-13 General Electric Company Friction stir welded hollow airfoils and method therefor

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1450006A1 (fr) * 2003-02-22 2004-08-25 Rolls-Royce Deutschland Ltd & Co KG Aube de compresseur pour un moteur d'avion

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2189627A1 (fr) * 2008-11-25 2010-05-26 Rolls-Royce Deutschland Ltd & Co KG Procédé de fabrication des composantes hybrides pour moteurs de turbine à gaz
US9126361B2 (en) 2008-11-25 2015-09-08 Rolls-Royce Deutschland Ltd & Co Kg Method for the manufacture of hybrid components for aircraft gas turbines
WO2014007685A1 (fr) * 2012-07-03 2014-01-09 Gkn Aerospace Sweden Ab Structure de support pour un moteur de turbine à gaz
US9822652B2 (en) 2012-07-03 2017-11-21 Gkn Aerospace Sweden Ab Supporting structure for a gas turbine engine
EP2693061A3 (fr) * 2012-07-30 2014-04-30 Rolls-Royce Deutschland Ltd & Co KG Aube de compresseur d'une turbine à gaz et son procédé de fabrication
US9828860B2 (en) 2012-07-30 2017-11-28 Rolls-Royce Deutschland Ltd & Co Kg Compressor blade of a gas turbine as well as method for manufacturing said blade
CN104603398A (zh) * 2012-09-12 2015-05-06 联合工艺公司 具有蜂窝填料的中空风扇叶片
CN104603398B (zh) * 2012-09-12 2017-03-08 联合工艺公司 具有蜂窝填料的中空风扇叶片

Also Published As

Publication number Publication date
EP1939402A3 (fr) 2010-05-05
DE102006061916A1 (de) 2008-06-26
US8251664B2 (en) 2012-08-28
US20080152506A1 (en) 2008-06-26

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