EP2090747B1 - Bord d'attaque de pièce de turbomachine constitué de matériau superélastique - Google Patents

Bord d'attaque de pièce de turbomachine constitué de matériau superélastique Download PDF

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Publication number
EP2090747B1
EP2090747B1 EP09152682A EP09152682A EP2090747B1 EP 2090747 B1 EP2090747 B1 EP 2090747B1 EP 09152682 A EP09152682 A EP 09152682A EP 09152682 A EP09152682 A EP 09152682A EP 2090747 B1 EP2090747 B1 EP 2090747B1
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EP
European Patent Office
Prior art keywords
main portion
leading edge
sheet
deformation
turbomachine
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
EP09152682A
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German (de)
English (en)
French (fr)
Other versions
EP2090747A1 (fr
Inventor
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
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Filing date
Publication date
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Publication of EP2090747A1 publication Critical patent/EP2090747A1/fr
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Publication of EP2090747B1 publication Critical patent/EP2090747B1/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/20—Rotors
    • F05B2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05B2240/31—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor of changeable form or shape
    • F05B2240/311—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor of changeable form or shape flexible or elastic
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane
    • 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
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • 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
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/505—Shape memory behaviour
    • 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
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making

Definitions

  • the present invention relates to a turbomachine part comprising a main part and a leading edge.
  • upstream and downstream are defined relative to the direction of normal air flow along the room.
  • length and height refer to the largest dimension and the smallest dimension of the part perpendicular to the direction of air flow, respectively.
  • leading edge of a workpiece is meant that part of the workpiece which, in normal operation when it is subjected to a flow of air, is directly impacted by this flow.
  • the leading edge is the most upstream part of the room.
  • the blades are an example of parts that are subject to a flow of air.
  • the flow of air circulating around the fixed or moving parts of a turbomachine can carry foreign bodies (chippings, pieces of ice, ...) that can impact these parts at high speed and damage them. In particular, it is the leading edge of these parts which undergoes the impacts, and is therefore undesirably deformed.
  • This damage is particularly detrimental with respect to turbine blades, including OGV ( outletguide vanes ) and IGV ( inlet guide vanes ), which participate in creating the thrust developed by the turbomachine.
  • a collision with a foreign body can affect both the structural integrity of the blade (creation of internal or external cracks, and delamination in the case of composite parts), hence a risk of rupture of the part and severe damage to parts of the downstream turbomachine.
  • this collision almost systematically deforms the leading edge of the blade, which modifies its ideal aerodynamic profile and disrupts the flow of air around this blade, which leads to a decrease in performance. of the turbomachine.
  • the present invention aims to remedy these drawbacks, or at least to mitigate them.
  • EP 1,577,422 which relates to a turbomachine part comprising a main part 14 and a leading edge 16, this leading edge being constituted, on at least a part of the length of the part, of a material which is fixed on the main part and which is capable, below maximum deformation, of reversibly deforming superelastically in response to impact by a foreign body.
  • the object of the invention is to propose a part that can recover its initial shape after an impact by a foreign body, and whose mechanical performance is not affected by this impact.
  • the leading edge of the part is constituted, on at least a part of the length of the part, of a sheet of material which is fixed on the main part and which extends from the intrados on the extrados of the main part by providing a space between this sheet and the upstream end of the main part, the material being capable, below a maximum deformation ( ⁇ 2 ), of deforming reversible superelastic in response to an impact by a foreign body, without damaging the main part.
  • the leading edge of the part under the effect of an impact by a foreign body, deforms but without damaging the main part of the part, which is its structural part.
  • this leading edge is able to substantially return to its original shape before impact, even in case of impact of high energy.
  • the superelastic material is a shape memory alloy in the austenite phase.
  • the material is capable, above the maximum deformation ( ⁇ 2 ), of recovering, by heating above a transition temperature (T t ), its shape before deformation.
  • the leading edge even strongly deformed (that is to say above the deformation ⁇ 2 ) following an impact, is capable, by heating the material constituting the leading edge to above a transition temperature, to substantially resume its original shape before impact.
  • the invention also relates to a method of manufacturing a turbomachine part comprising a main part having a leading edge.
  • this method comprises: truncating the leading edge of the main part; fixing on this main part of a sheet of material which extends from the intrados to the extrados of the main part over at least part of its length so that the sheet reconstitutes the profile of the leading edge of the main part before the truncation of this leading edge, this material being capable, below a maximum deformation ( ⁇ 2 ), of reversibly deforming superelastically in response to impact by a foreign body, without damaging the main part.
  • ⁇ 2 maximum deformation
  • the piece having a leading edge is a blade.
  • this dawn is an OGV ("outlet guide vane") or an IGV ("guide guide vane”).
  • the invention applies to any turbomachine part having a leading edge and subjected to an air flow, such as for example an inlet housing arm.
  • the figure 1 represents a turbine engine blade section.
  • This blade 10 comprises an upstream end 20, a lower surface 30, an upper surface 50, and a downstream end 40.
  • the upstream end 20 is the portion of the blade which is first touched by the air flow during normal operation. the turbomachine, which is in this case the leading edge of the dawn 10.
  • the intrados 30 is the concave surface of the blade 10, namely the surface along which the flow of air circulating around the blade 10 generates an overpressure.
  • the extrados 50 is the convex surface of the blade 10, namely the surface along which the airflow generates a depression.
  • the blade 10 has substantially a curved plate shape that thickens from its downstream end 40 to its upstream end 20.
  • the figure 2 shows a blade 10 according to the invention.
  • This blade 10 comprises on the one hand a main part 15 having an upstream end 20, a lower surface 30, an upper surface 50, and a downstream end 40, on the other hand a sheet 60.
  • the main part 15 is identical to the dawn of the figure 1 .
  • the upstream end 20 of the main portion 15 is covered by the sheet 60.
  • the sheet 60 extends in length in the direction D in which extends the upstream end 20 of the main portion 15.
  • the sheet extends width in a plane that is perpendicular to this direction D (this direction D is perpendicular to the plane of the figure 2 ). Thus, in this plane, the sheet extends from a first edge 61 to a second edge 62, each of these edges extending in the direction D.
  • the first edge 61 is fixed, over its entire length (this is in the direction D) on the extrados 50, near the upstream end 20, and the second edge 62 is fixed, throughout its length, on the intrados 30, near the upstream end 20.
  • the sheet 60 is substantially U-shaped in a plane perpendicular to the direction D.
  • these fasteners do not generate protuberances protruding from the surface of the workpiece, so as not to disturb the flow of air along the intrados 30 and the extrados 50.
  • these fasteners can for example by gluing, brazing, welding, or riveting.
  • the upstream end 20 of the main part is covered over its entire length (direction D) by the sheet 60.
  • the sheet 60 may cover the upstream end 20 only over part of its length.
  • the material in which the sheet 60 is manufactured is a superelastic material, that is, a material that is able to recover its original shape when the stress to which it had been subjected is removed (reversible deformation), and this for deformations well above the deformation corresponding to the usual elastic limit of alloys.
  • the elastic limit that is to say the stress up to which the deformation is elastic reversible (conventional elasticity)
  • the elastic limit is of the order of 0.1%.
  • For a superelastic material it is of the order of several percent.
  • the superelastic material of the sheet 60 is a shape memory alloy.
  • shape memory alloys the superelasticity is due to the reversible transformation of the austenite phase (face-centered cubic crystal lattice) into the martensite phase (tetragonal crystalline lattice) at a substantially constant temperature.
  • Shape memory alloys are for example copper-nickel alloys (Cu-Ni), copper-zinc-nickel (Cu-Zn-Ni) or nickel-titanium (Ni-Ti, Nitinol ®), optionally alloyed with d other elements (iron, niobium).
  • the figure 4 gives an example of a stress-strain curve (or ⁇ ( ⁇ )) of a shape memory alloy. Note that this curve has three regions: for deformation ⁇ less than the minimum deformation ⁇ 1 (region I), the material is linear elastic (classical elasticity); for a deformation ⁇ between ⁇ 1 and a maximum deformation ⁇ 2 greater than the minimum deformation ⁇ 1 (region II), the material is superelastic (it deforms a lot under a constraint that increases little); for a deformation ⁇ greater than the maximum deformation ⁇ 2 (region III), the deformation is not reversible. Region II is the range of superelastic deformations. The maximum deformation ⁇ 2 may for example vary between 3% and 10%.
  • the shape memory alloy which constitutes the sheet 60 is in austenite.
  • the energy of the impact by a foreign body causes the metallurgical transformation of this alloy into martensite, and causes the reversible superelastic deformation of the sheet 60 (that is to say that the deformation is in the deformation range [ ⁇ 1 ; ⁇ 2 ]).
  • the alloy After impact, the alloy returns to its initial shape (before impact).
  • the space 70 constitutes an empty cavity.
  • the cavity 70 is of sufficient size that the sheet 60 can deform without touching the upstream end 20 the main part 15, or if it touches it, without causing any damage to the mechanical integrity of the main part 15.
  • the retreating distance of the sheet 60 depends on the energy and shape of the impact projectile, the thickness of the sheet, and the size of the part.
  • the recoil distance is for example between 0.1 mm and 2 mm (millimeters).
  • the sheet has for example a thickness of between 0.1 and 0.5 mm.
  • the upstream end 20 of the main portion 15 may be truncated to form an upstream face 25 which is substantially flat.
  • This embodiment is illustrated on the figure 3 .
  • the sheet 60 can thus be fixed on the main part 15 so that it reconstructs the profile of the upstream end 20 (leading edge) of the main part 15 before the truncation of this upstream end 20.
  • a part 10 whose leading edge consists of a sheet 60 of superelastic material, the shape and the volume of the part 10 being substantially identical to the initial shape and volume of the main part 15 before truncation of its end upstream 20. In this way, the aerodynamic characteristics of the part 10 are preserved.
  • the space 70 may be filled with a filling material whose rigidity is substantially less than the stiffness E 0 of the material of the main part 15.
  • This filling material for example a solid foam
  • the blade 10 can withstand impacts of larger energy foreign bodies (that is to say until the impacts that generate in the sheet 60 stresses ⁇ less than ⁇ 1 ) while practically deforming.
  • the material of the sheet 60 will not enter the superelastic domain II (domain of deformations greater than the minimum deformation ⁇ 1 and less than the maximum deformation ⁇ 2 ) than for significant energy impacts.
  • the sheet 60 will retain longer its ability to deform superelastically. Indeed, it is known that the shape memory alloys age beyond a given number of superelastic deformation cycles, this aging resulting in a degradation of the ability of such alloys to return to their original shape after deformation.
  • the austenite-martensite transformation temperatures of the shape memory alloy constituting the sheet 60 must be less than the temperature operating range of the part 10, the sheet 60 forms the leading edge. Indeed, in the opposite case, the superelastic effect (which is solely due to the application of a mechanical stress), is disturbed, and the sheet 60 does not return to its original shape before impact. In this temperature operating range, the sheet 60 is in the austenite phase. In a turbomachine, this temperature range is typically -50 ° C to 130 ° C for so-called "cold" parts, especially upstream of the combustion chamber.
  • the leading edge may consist of any superelastic material which, subjected to deformations greater than the maximum deformation ⁇ 2 , is able to recover its initial shape (before deformation) by heating above a transition temperature T t .

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP09152682A 2008-02-14 2009-02-12 Bord d'attaque de pièce de turbomachine constitué de matériau superélastique Active EP2090747B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0850935A FR2927652B1 (fr) 2008-02-14 2008-02-14 Bord d'attaque de piece de turbomachine constitue de materiau superelastique

Publications (2)

Publication Number Publication Date
EP2090747A1 EP2090747A1 (fr) 2009-08-19
EP2090747B1 true EP2090747B1 (fr) 2011-09-21

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EP09152682A Active EP2090747B1 (fr) 2008-02-14 2009-02-12 Bord d'attaque de pièce de turbomachine constitué de matériau superélastique

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US (1) US20090208342A1 (ja)
EP (1) EP2090747B1 (ja)
JP (1) JP5172735B2 (ja)
CA (1) CA2653565A1 (ja)
FR (1) FR2927652B1 (ja)
RU (1) RU2486347C2 (ja)

Cited By (1)

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CN107420349A (zh) * 2017-09-14 2017-12-01 西安交通大学 一种预旋条件下低流动损失的离心压缩机进口导叶结构

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DE102010036042B3 (de) * 2010-08-31 2012-02-16 Lufthansa Technik Ag Verfahren zum Rekonturieren einer Kompressor- oder Turbinenschaufel für eine Gasturbine
US20130167552A1 (en) * 2012-01-04 2013-07-04 General Electric Company Exhaust strut and turbomachine incorprating same
USD748054S1 (en) * 2013-02-19 2016-01-26 Tnp Co., Ltd. Wind turbine blade
EP2971522B1 (en) 2013-03-14 2018-07-18 Rolls-Royce Corporation Airfoil with leading edge reinforcement
FR3014943B1 (fr) * 2013-12-18 2019-03-29 Safran Aircraft Engines Piece de turbomachine a surface non-axisymetrique
US20170130585A1 (en) * 2015-11-09 2017-05-11 General Electric Company Airfoil with energy absorbing edge guard
BE1023295B1 (fr) * 2016-01-21 2017-01-26 Safran Aero Boosters S.A. Aube statorique
BE1023299B1 (fr) * 2016-01-21 2017-01-26 Safran Aero Boosters S.A. Aube statorique
CN114961873B (zh) * 2021-02-25 2024-05-31 中国航发商用航空发动机有限责任公司 可恢复变形的叶片及包含其的涡扇发动机
US11988103B2 (en) * 2021-10-27 2024-05-21 General Electric Company Airfoils for a fan section of a turbine engine
US20230160307A1 (en) * 2021-11-23 2023-05-25 General Electric Company Morphable rotor blades and turbine engine systems including the same

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Publication number Priority date Publication date Assignee Title
CN107420349A (zh) * 2017-09-14 2017-12-01 西安交通大学 一种预旋条件下低流动损失的离心压缩机进口导叶结构

Also Published As

Publication number Publication date
EP2090747A1 (fr) 2009-08-19
RU2009105144A (ru) 2010-08-20
FR2927652B1 (fr) 2010-03-26
JP2009191847A (ja) 2009-08-27
RU2486347C2 (ru) 2013-06-27
CA2653565A1 (fr) 2009-08-14
FR2927652A1 (fr) 2009-08-21
JP5172735B2 (ja) 2013-03-27
US20090208342A1 (en) 2009-08-20

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