EP3315721A1 - Verstärkung der vorderkante einer laufradschaufel einer strömungsmaschine - Google Patents

Verstärkung der vorderkante einer laufradschaufel einer strömungsmaschine Download PDF

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Publication number
EP3315721A1
EP3315721A1 EP17197595.6A EP17197595A EP3315721A1 EP 3315721 A1 EP3315721 A1 EP 3315721A1 EP 17197595 A EP17197595 A EP 17197595A EP 3315721 A1 EP3315721 A1 EP 3315721A1
Authority
EP
European Patent Office
Prior art keywords
point
blade
fin
edge
radially outer
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.)
Granted
Application number
EP17197595.6A
Other languages
English (en)
French (fr)
Other versions
EP3315721B1 (de
Inventor
Jean-Louis Romero
Jean-François FREROT
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
Safran Aircraft Engines 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 Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP3315721A1 publication Critical patent/EP3315721A1/de
Application granted granted Critical
Publication of EP3315721B1 publication Critical patent/EP3315721B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/288—Protective coatings for 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
    • F01D5/14—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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/388—Blades characterised by construction
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/711—Shape curved convex
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/174—Titanium alloys, e.g. TiAl

Definitions

  • the present invention relates to a turbomachine blade, and more particularly to a leading edge reinforcement of this blade.
  • these include a Leading edge reinforcement whose role is to protect the leading edge from deterioration during an impact with a FOD and to distribute the impact force a large area of the dawn.
  • a reinforcement of the blade leading edge conventionally comprises an extrados vane at least partially covering the aerodynamic surface of the upper surface of the vane and a vane fin at least partially covering the aerodynamic surface of the lower surface of the vane. dawn, these two fins being joined by a leading edge of the reinforcement.
  • the blade When the blade is movable relative to the axis of the turbomachine, it turns its surface intrados forward, that is to say that the air comes into contact with the surface of the lower surface thus creating an overpressure on the underside surface and a depression on its extrados surface.
  • the detachment of the extrados blade causes damage to the inner layer of abradable.
  • the extrados vane protrudes from the upper surface of the blade and penetrates into the abradable inner layer which creates a groove in the abradable inner layer. It is then necessary to immobilize the turbomachine to replace both the blade whose leading edge reinforcement has taken off and the inner layer of abradable. Such immobilization generates a significant cost resulting from the lack of exploitation of the turbomachine that it is important to reduce or even eliminate.
  • the invention aims in particular to provide a simple, effective and economical solution to this problem.
  • the invention proposes, firstly, a turbomachine blade extending along a longitudinal axis, comprising an aerodynamic surface which extends in a first direction between a leading edge and a trailing edge, and in a second direction substantially perpendicular to the first direction between a foot and a top of the blade, and a leading edge reinforcement comprising a fin partly covering the aerodynamic surface of the blade, characterized in that, the fin has a radially outer edge arranged in the vicinity of the apex of the blade and extending between the leading edge and the trailing edge, this radially outer edge comprising an upstream point flush with the top of the blade at the edge attack and a downstream point separated from the top of the dawn.
  • the upstream point is located at the upstream end of the upper edge, that is to say at the leading edge of the blade and the downstream point is located at the downstream end of the radially outer edge of the fin.
  • downstream point is spaced radially inwardly of the blade tip.
  • the aerodynamic surface is an extrados surface
  • the fin is an extrados fin, the extrados portion of the reinforcement being more particularly subject to detachment, increased separation in particular by the centrifugal force for a movable blade.
  • the radially outer edge of the fin comprises an intermediate point located between the upstream point and the downstream point and defining with the upstream point a first portion of the radially outer edge, flush with the top of the blade and, with the downstream point a second portion of the radially outer edge progressively diverging from the apex of the blade towards the vanishing point.
  • the separation into two portions offers a good compromise between limiting penetration of the fin in the abradable inner layer in case of separation of the fin, and good distribution of forces in case of impact of a FOD on the reinforcement leading edge.
  • the intermediate point may be arranged longitudinally at an equal distance from the upstream point and the downstream point.
  • the second portion of the radially outer edge of the extrados vane is curved convex. This particular shape makes it easier to manufacture the reinforcement and also to limit the creation of disturbances in the flow of the air flow.
  • This distance also offers a good compromise between limiting penetration of the fin in the abradable inner layer in case of separation of the fin, and good distribution of forces in case of impact of an FOD on the edge reinforcement. attack.
  • the reinforcement comprises a vane fin partly covering an aerodynamic surface of intrados of the blade.
  • This underside fin also helps protect the aerodynamic surface of intrados of the blade against the FOD.
  • the leading edge reinforcement is made of a metallic material.
  • the invention proposes, secondly, an assembly comprising a central disc on which are mounted a plurality of blades as previously described, said vanes being evenly distributed around the periphery of the central disc, and extending substantially radially to the disc central.
  • the invention proposes, thirdly, a turbomachine comprising an assembly as previously described.
  • a turbomachine 2 having an assembly 4 comprising a central disc 6 rotating about a longitudinal axis A of the turbomachine 2, and on which is mounted a plurality of blades 8.
  • the blades 8 are regularly distributed around the periphery 6a of the disc 6 central, and extending substantially radially to the disc 6 central.
  • the assembly 4 is the fan of the turbomachine 2
  • the blades 8 are the fan blades.
  • the turbomachine 2 also comprises, upstream to downstream, and downstream of the blower, a low pressure compressor 10, a high pressure compressor 12, a combustion chamber 14, a high pressure turbine 16, a low pressure turbine 18 , and an exhaust casing.
  • the turbomachine 2 comprises hooking means 22, in this case two, each carried by an intermediate blower housing 24 carrying an internal layer 24a abradable (visible on the figure 4 ), and a turbine casing 26.
  • radial (e) is understood to mean any direction substantially perpendicular to the axis A of the turbomachine 2, upstream the side by which the air reaches a part of the turbomachine 2, and downstream the side by which the air moves away from said part of the turbomachine 2.
  • the air flow direction is represented in FIG. figure 2 by the arrow F.
  • blade 8 is meant here both the blades 8 movable (for example the rotor blades) and the blades (for example the stator vanes) of the turbomachines 2.
  • Dawn 8 illustrated in perspective on the figure 2 and in section on the figure 3 comprises an aerodynamic surface 28 of an upper surface and an aerofoil surface 30 which extends in a first direction between a leading edge 8a and a trailing edge 8b of the blade 8.
  • the blade 8 of a fan being twisted, the first direction moves in an XY plane following the section taken in a radial direction along the Z axis which forms with the X and Y axes an orthonormal reference on the figure 2 .
  • the aerodynamic surface 28 of the upper surface and the aerodynamic surface 30 of the undersides extend between a foot 8c and an apex 8d of the blade 8.
  • the blade 8 also comprises a leading edge reinforcement 32 comprising an extrados fin 32a partly covering the aerodynamic surface 28 of the extrados of the substantially radial blade 8, and a fin 29b of a lower surface covering part of the airfoil. aerodynamic surface of the underside of the blade 8.
  • These two fins 32a, 32b have, as visible in FIG. figure 3 , a section that is refined from upstream to downstream.
  • the two fins 32a, 32b are joined by a leading edge 32c which covers the leading edge 8a of the blade 8 and has, in section, a thickness greater than the maximum thickness of the fins 32a, 32b.
  • the reinforcement 32 of edge 8a of attack of the blade 8 extends substantially from the foot 8c of the blade 8, to its top 8d.
  • the leading edge reinforcement 32 is preferably made of a highly resistant metallic material, such as, for example, a titanium alloy.
  • the detail view of the figure 4 highlights a particularity of the fin 32a of extrados of the leading edge reinforcement 32.
  • the extrados vane 32a has a radially outer (also upper) edge 34 arranged in the vicinity of the blade crown 8d and which extends from the leading edge 8a to the edge 8b ( figure 2 ) leak.
  • This radially outer edge 34 comprises an upstream point 34a which is flush with the apex 8d of the blade 8 at the leading edge 8a and a downstream point 34b which is spaced from the apex 8d of the blade 8.
  • the term "superior" according to the orientation of the figure 4 .
  • the radially outer edge 34 is disposed radially outwardly with respect to the axis A of the turbomachine 2.
  • upstream point 34a is arranged on the side of the leading edge 8a of the blade 8 and the downstream point 34b is arranged on the side of the trailing edge 8b of the blade 8 in the direction of air flow.
  • F figure 2
  • the upper radially outer edge 34 of the extrados fin 32a comprises an intermediate point 34c situated between the upstream point 34a and the downstream point 34b and defining, with the upstream point 34a, a first portion 36 of the radially outer edge flush with the top 8d of the blade 8 and, with the point 34b downstream, a second portion 38 of the upper edge progressively diverging from the top 8d of the blade 8.
  • the connection of the first portion 36 of the radially outer edge 34 with the second portion 38 of the upper edge is substantially tangential.
  • the intermediate point 34c is arranged equidistant from the upstream point 34a and the downstream point 34b, in an axial direction parallel to the longitudinal axis A.
  • intermediate point 34c could be closer to point 34a upstream or point 34b downstream.
  • a fictitious extreme point 34e corresponding to the symmetry of the point 34a upstream with respect to a median axis M substantially perpendicular to the axis A of the turbomachine 2, and passing at least through the center of the top of the fin 32a of extrados .
  • This 34th point fictitious extreme corresponds to an extreme point of the fin 32a extrados before optimization of the latter.
  • this point 34th extreme makes it possible to define the progressive spacing of the point 34b downstream from the vertex 8d of the blade 8.
  • the spacing of the second portion 38 of the radially outer edge 34 of the extrados fin 32a is preferably convexly curved.
  • the second portion 38 has a substantially curved shape that moves away from the top 8d of the blade 8 in the direction of the foot 8c ( figure 2 ) of the latter, and this upstream downstream.
  • the second portion 38 of the radially outer edge 34 of the extrados vane 32a could be rectilinear or, conversely, comprise an alternation of bumps and depressions.
  • the distance L, the tangent T and the angle ⁇ are illustrated on the figure 5 .
  • the lower surface fin 32b also comprises an upper edge having an upstream point flush with the apex 8d of the blade 8 and a downstream point remote from the upstream point and spaced from the vertex 8d of the blade 8, that is to say radially distant internally.
  • the upper edge of the lower surface fin 32b may also comprise an intermediate point situated between the point of attack and the vanishing point and defining with the point of attack a first portion of the upper edge, flush with the top 8d of the dawn 8 and, with the vanishing point, a second portion of the upper edge progressively diverging from the apex 8d of the blade 8 towards the foot 8c.
  • the shapes and dimensions of the portions of the vane fin 32b are reduced with respect to the shapes and dimensions of the portions 36, 38 of the upper edge 34 of the extrados vane 32a.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Architecture (AREA)
  • Composite Materials (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP17197595.6A 2016-10-28 2017-10-20 Verstärkung der vorderkante einer laufradschaufel einer strömungsmaschine Active EP3315721B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1660479A FR3058181B1 (fr) 2016-10-28 2016-10-28 Renfort de bord d'attaque d'une aube de turbomachine

Publications (2)

Publication Number Publication Date
EP3315721A1 true EP3315721A1 (de) 2018-05-02
EP3315721B1 EP3315721B1 (de) 2022-03-02

Family

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Family Applications (1)

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EP17197595.6A Active EP3315721B1 (de) 2016-10-28 2017-10-20 Verstärkung der vorderkante einer laufradschaufel einer strömungsmaschine

Country Status (4)

Country Link
US (1) US10316669B2 (de)
EP (1) EP3315721B1 (de)
CN (1) CN108005730B (de)
FR (1) FR3058181B1 (de)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108454829A (zh) * 2018-05-30 2018-08-28 安徽卓尔航空科技有限公司 一种螺旋桨叶片
FR3085300B1 (fr) * 2018-08-31 2022-01-21 Safran Aircraft Engines Aube en materiau composite a film anti-erosion renforce et procede de protection associe
US10760428B2 (en) 2018-10-16 2020-09-01 General Electric Company Frangible gas turbine engine airfoil
US10746045B2 (en) 2018-10-16 2020-08-18 General Electric Company Frangible gas turbine engine airfoil including a retaining member
US11111815B2 (en) 2018-10-16 2021-09-07 General Electric Company Frangible gas turbine engine airfoil with fusion cavities
US11434781B2 (en) 2018-10-16 2022-09-06 General Electric Company Frangible gas turbine engine airfoil including an internal cavity
US10837286B2 (en) 2018-10-16 2020-11-17 General Electric Company Frangible gas turbine engine airfoil with chord reduction
US11149558B2 (en) 2018-10-16 2021-10-19 General Electric Company Frangible gas turbine engine airfoil with layup change
FR3103215B1 (fr) 2019-11-20 2021-10-15 Safran Aircraft Engines Aube de soufflante rotative de turbomachine, soufflante et turbomachine munies de celle-ci
FR3115079B1 (fr) * 2020-10-12 2022-10-14 Safran Aircraft Engines Aube en materiau composite comprenant un bouclier de bord d’attaque, turbomachine comprenant l’aube

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2298653A (en) * 1995-03-10 1996-09-11 United Technologies Corp Electroformed sheath
EP2540974A2 (de) * 2011-06-28 2013-01-02 United Technologies Corporation Lüfterschaufel mit Umhüllung

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1304678A (de) * 1971-06-30 1973-01-24
JP4390026B2 (ja) * 1999-07-27 2009-12-24 株式会社Ｉｈｉ 複合材翼
US7736130B2 (en) * 2007-07-23 2010-06-15 General Electric Company Airfoil and method for protecting airfoil leading edge
FR2987867B1 (fr) * 2012-03-09 2016-05-06 Snecma Aube de turbomachine comportant un insert de protection de la tete de l'aube

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2298653A (en) * 1995-03-10 1996-09-11 United Technologies Corp Electroformed sheath
EP2540974A2 (de) * 2011-06-28 2013-01-02 United Technologies Corporation Lüfterschaufel mit Umhüllung

Also Published As

Publication number Publication date
FR3058181B1 (fr) 2018-11-09
CN108005730A (zh) 2018-05-08
EP3315721B1 (de) 2022-03-02
CN108005730B (zh) 2022-07-08
US10316669B2 (en) 2019-06-11
FR3058181A1 (fr) 2018-05-04
US20180119551A1 (en) 2018-05-03

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