EP2071125A1 - Einkristall-turbinenschaufel - Google Patents

Einkristall-turbinenschaufel Download PDF

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Publication number
EP2071125A1
EP2071125A1 EP08171584A EP08171584A EP2071125A1 EP 2071125 A1 EP2071125 A1 EP 2071125A1 EP 08171584 A EP08171584 A EP 08171584A EP 08171584 A EP08171584 A EP 08171584A EP 2071125 A1 EP2071125 A1 EP 2071125A1
Authority
EP
European Patent Office
Prior art keywords
blade
leading edge
face
point
theoretical
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
EP08171584A
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English (en)
French (fr)
Other versions
EP2071125B1 (de
Inventor
Patrick Joseph Marie Girard
Jean-Claude Marcel Auguste Hanny
Renaud Martet
Olivier Charles Henri Massy
Philippe Jean-Pierre Pabion
Stéphanie Dominique Roger
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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Publication date
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Publication of EP2071125A1 publication Critical patent/EP2071125A1/de
Application granted granted Critical
Publication of EP2071125B1 publication Critical patent/EP2071125B1/de
Active 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
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D27/00—Treating the metal in the mould while it is molten or ductile ; Pressure or vacuum casting
    • B22D27/04—Influencing the temperature of the metal, e.g. by heating or cooling the mould
    • B22D27/045—Directionally solidified castings
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/607—Monocrystallinity

Definitions

  • the present invention relates to turbomachine blades. It relates to the blades of turbomachines or turbine engine modules, such as compressor or turbine modules, made of foundry and in particular on the fattening of the connection zone between the blade and its heel or the blade and the plate. associated form.
  • the blades obtained by casting of superalloys based on nickel or cobalt are manufactured using the so-called lost wax technique. These blades have columnar or monocrystalline metallurgical structures obtained by a directed solidification process. This process is difficult to control, especially for hollow and highly three-dimensional parts.
  • a model wax or other equivalent material, which comprises an inner part forming a foundry core and the cavities of the blading.
  • a wax injection mold is used in which the core is placed and the wax is injected.
  • the wax model is then soaked several times in slips consisting of a suspension of ceramic particles to make a shell mold. We remove the wax and cook the carapace mold.
  • Blading is achieved by casting a molten metal which occupies the voids between the inner wall of the shell mold and the core. With a seed, or appropriate selector, and controlled cooling, the metal solidifies in a desired crystal structure.
  • the alloy may be directed solidification with columnar structure, directed solidification with monocrystalline structure or equiaxed solidification (EX). After solidification of the alloy, the carapace and the core are unchecked, it leaves the desired blading.
  • EX equiaxed solidification
  • Solidification is a time during which the metal undergoes significant thermal stresses, these stresses are often at the origin of the recrystallization of the metal.
  • these stresses are often at the origin of the recrystallization of the metal.
  • important areas of recrystallization well defined are observed. For example, when the blade comprises a heel, recrystallized zones are located on the blade, under the heel, approximately 10 mm under the pale-heel connection, as shown in FIG. figure 1 .
  • the recrystallization on these blades originates from excessive stresses imposed on the metal during solidification.
  • the root is defined by a height and a thickness in intrados and extrados.
  • the connection area extends all around the blade. Tests have shown the influence of the geometry of the root on recrystallization.
  • the figure 2a shows a root with a thickness of 2 mm and a height h of 5 mm.
  • the figure 2b shows a root with a thickness of 2 mm and a height 2h of 10 mm.
  • the Figure 2c shows a root with a thickness a 'of 3 mm and a height 2h of 10 mm. It has been possible to eliminate the recrystallization phenomenon only with a root of relatively large size facilitating the flow of the molten metal between the blade and the heel.
  • the root is not aerodynamically satisfactory: on the one hand it creates a nominal tangential step in the vein, generated by the truncation of the external vein radius, on the other hand its presence on the whole profile disrupts in a significant way the aerodynamic performance on the turbomachine.
  • the applicant has set the objective of developing a satisfactory root both with respect to the flowability of the molten metal in the shell mold, aerodynamic constraints to be respected and the mechanical strength of the part in use on the turbomachine.
  • the invention thus relates to the construction of a blade, with the establishment of a local thickening of the section of the blade, designated root, favorable with respect to the criteria reported above.
  • the thickening is applied to a particular surface of the blade, mainly at the leading edge, intrados and extrados, over a defined height.
  • the invention makes it possible to solve the problem of the flowability of the molten metal while ensuring both the aerodynamic performance and the mechanical strength. It consisted of defining a fattening of material, on a particular surface of the blade, mainly on the edge of attack, intrados and extrados and on a defined height, making it possible to respect the multi-disciplinary criteria.
  • the invention has the advantage of eliminating recrystallization, while respecting the aerodynamic criteria, and improves the life of the blade.
  • the invention applies to all blades of raw casting turbomachines, whether fixed or mobile, placed in a non-cylindrical vein.
  • the invention is explained for fattening at the leading edge between the blade and the upper vein, but can also be applied to fattening at the leading edge between the blade and the inferior vein if the conicity of the vein involves the need.
  • the section of said blade in the connection zone increases towards said heel, remaining lower than that which the blade presents in its lower part.
  • the line of points P2 located furthest upstream with respect to the direction of flow of the fluid in the connection zone is located in the extension of the leading edge BA of the blade on the skeleton S.
  • the blade end face out of the fillet of connection to the blade end face and the leading edge BA of the blade is rectilinear and forms an angle ⁇ with the line of points.
  • P2 at least equal to 75 ° and less than 90 °.
  • the curvature of the connection zone in at least one cutting plane perpendicular to the leading edge of the theoretical profile, at the corresponding point of the line of the points P2 is a function of the curvature of the leading edge and the distance separating in said cutting plane the point of the line of points P2 of the leading edge of the blade.
  • the curvature at a point is equal to the radius of the circle inscribed in the profile at the point.
  • the radius of curvature at said point of the line of the points P2 is equal to the corresponding radius of curvature on the theoretical profile BAv, plus one third of the length I1 as defined below.
  • the surface of the connection zone at P1 situated on the extrados FE on the one hand and the surface of the connection zone on P3 situated on the intrados FI, on the other hand, is tangent to the blade.
  • the surface of the connection zone has a profile C1 between the line of the points P2 and the point P1 located on the extrados FE which is deduced, at least in part, from that of the extrados surface FEv of the theoretical blade by a combination of geometric transformations of the translation, homothmatie and / or affinity type, with connecting parts providing continuity with the rest of the blade profile.
  • the surface of the connection zone has a profile C3 between the line of the points P2 and the point P3 situated on the intrados FI which is deduced, at least in part, from that of the intrados surface FIv of the theoretical blade by a combination of geometric transformations of the translation, homothmatie and / or affinity type, with connecting parts providing continuity with the rest of the blade profile.
  • the position of the point P3 located on the underside is determined so as to optimize the position of the center of gravity of the connection zone.
  • the center of gravity of the connection zone defined by the surface located upstream of the points P1 and P3 with respect to the direction of flow of the fluid lies on the axis of smaller inertia of the surface of the theoretical profile, preferably closer to the center of gravity of said section.
  • a blade 10 comprising a blade 11 and an end piece 20 (here a heel), shown schematically. It may be a platform in the case of the radially inner end; for the rest we will consider the case of a bead at the radially outer end of the blade.
  • the heel end of the blade 11 has the function of sealing the vein and comprises on its outer surface wipers of a seal, not shown.
  • the end piece 20 has a blade end face 21 facing the blade. This face forms a non-zero angle ⁇ with the axis ZZ of the blade. In the example shown, the angle ⁇ is about 50 °.
  • the blade 11 of the turbomachine has an intrados face FI and an extrados face FE extending between a leading edge BA and a trailing edge BF.
  • the blade 10 comprises a connection zone between the blade and the heel forming an extra thickness or a fattening 11E from a point P1 on the extrados face FE, and a point P3 on the intrados face FI.
  • This fattening is the excess of material with respect to the theoretical profile of the blade, that is to say that it would have without taking into account the technical problem solved by the invention, directly under the end surface 21 and which is represented by the dashed lines BAv, FIv and FEv on the Figures 3 and 4 .
  • Fattening is defined by the rules described below.
  • the point P1 is located upstream of the upper extrados CE line, the neck being the minimum distance separating two neighboring blades.
  • the connection zone, at P1 is tangential to the blade 11.
  • the profile C1 of the extrados of the connection zone 11E is substantially the same, at least in part, as that of the extrados area FEv of the theoretical blade, with connecting portions ensuring continuity with the rest of the profile of the blade.
  • This similarity is defined by the fact that the profile C1 is deduced from that of the FEv area by a combination of geometric transformations of the type translation, homothety and / or affinity.
  • the thickness of the connection zone 11E on the extrados must be minimal. This thickness is defined by the foundry experiment, it is imposed to minimize aerodynamic performance losses.
  • intrados material is defined by the rules described below.
  • the point P3 is located upstream of the CI intrados neckline.
  • the connection zone, at P3, is tangent to the blade 11.
  • the profile C3 of the intrados surface of the connection zone 11E is also similar to that of the intrados FIv zone of the theoretical blade and is deduced therefrom by a combination of geometric transformations of the same type as for the extrados.
  • the positioning of the point P3 is determined with a certain margin in order to optimize the position of the center of gravity of the connection zone 11E. Moving the point P3 to the point CI moves the center of gravity of the connection area to the point CI and vice versa.
  • the optimization of the position of the center of gravity of the connection zone allows the blade to keep its mechanical strength.
  • the center of gravity of the connection zone is advantageously on the axis of smaller inertia of the surface of the theoretical profile, preferably closer to the center of gravity of the surface of the theoretical profile.
  • the fattening of the connection area on the lower surface is determined, on the one hand, by a minimum thickness, specified by the foundry experiment, in order to meet flowability criteria, and on the other hand, by a maximum thickness resulting from the section / mass objective in order to respect the constraints of mechanical resistance.
  • the fattening is located mainly at the leading edge BA of the blade.
  • the leading edge BA is the line formed from the most upstream point on the profile of the blade and the trailing edge BF is the line of the points furthest downstream. Upstream and downstream are defined with respect to the flow of gas around the blade.
  • the line of points P2 of the connection zone which are also situated furthest upstream on the blade, is located in the extension of the line of the leading edge BA and the skeleton S of the blade.
  • the skeleton of the blade also called skeleton or middle line, is the set of equidistant points of extrados FE and intrados FI.
  • connection zone on which the line of points P2, which is preferably rectilinear, is positioned at the connection loops close to the end face 21 of the blade and with the leading edge, is defined by angles ⁇ and ⁇ .
  • the angle ⁇ corresponds to the angle between the end face of the blade and the line of points P2.
  • the angle ⁇ is the angle between the line of points P2 and the leading edge BA. These two angles are defined by the foundry experiment in order to respect the flowability criterion.
  • the angle ⁇ is in the range 75 ° to 90 °. As for the angle ⁇ , it is related to the angle ⁇ .
  • the connection between the zone 11E and the surface 21 is not secant but is progressive with a rounding.
  • the point of the line of the points P2 on the face 21 is at a distance I1 from the theoretical leading edge BAv.
  • the length I1 is determined so as to maintain the aerodynamic criteria of the blade. Its length is sufficient to preserve the mechanical strength of the heel.
  • the height I2 represents the height of the connection zone near the leading edge. This height is between a minimum value and a maximum value.
  • the minimum value must satisfy the flowability criterion, the minimum value is determined by the foundry experiment.
  • the maximum value aims to respect the objective of section / mass law to preserve the mechanical strength.
  • the figure 5 is a graph, with, for abscissa axis, the area of a section of the blade in a plane perpendicular to the leading edge of the theoretical profile, and for ordinate axis, the radius at the corresponding point of the leading edge , representing the law of evolution of the section / mass along the vein.
  • the GM mass gain is illustrated by the area between the curve portion representing the area of the cuts through the initial root R1 as it would have been achieved without the invention, that is, with a thickening on any the periphery of the blade and the RO root according to the invention.
  • the section of the blade which decreases as it approaches the heel, increases in the connection zone, but remains lower than the value it has in the lower part of the blade.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP08171584A 2007-12-14 2008-12-12 Einkristall-turbinenschaufel Active EP2071125B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0708751A FR2924958B1 (fr) 2007-12-14 2007-12-14 Aube de turbomachine realisee de fonderie avec un engraissement local de la section de la pale

Publications (2)

Publication Number Publication Date
EP2071125A1 true EP2071125A1 (de) 2009-06-17
EP2071125B1 EP2071125B1 (de) 2011-04-13

Family

ID=39719818

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08171584A Active EP2071125B1 (de) 2007-12-14 2008-12-12 Einkristall-turbinenschaufel

Country Status (7)

Country Link
US (1) US8128375B2 (de)
EP (1) EP2071125B1 (de)
JP (1) JP5462477B2 (de)
CA (1) CA2647154C (de)
DE (1) DE602008006153D1 (de)
FR (1) FR2924958B1 (de)
RU (1) RU2498082C2 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9163511B2 (en) 2012-08-09 2015-10-20 General Electric Company Steam turbine bucket tenon restoration through solid state bonding process

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5946707B2 (ja) * 2012-07-06 2016-07-06 三菱日立パワーシステムズ株式会社 軸流タービン動翼
FR2995235B1 (fr) * 2012-09-11 2016-12-09 Snecma Modele de fonderie
US9322282B2 (en) * 2012-11-30 2016-04-26 General Electric Company Fillet for use with a turbine rotor blade tip shroud
WO2014150342A1 (en) 2013-03-15 2014-09-25 United Technologies Corporation Cast component having corner radius to reduce recrystallization
JP6126745B2 (ja) * 2013-07-15 2017-05-10 ユナイテッド テクノロジーズ コーポレイションＵｎｉｔｅｄ Ｔｅｃｈｎｏｌｏｇｉｅｓ Ｃｏｒｐｏｒａｔｉｏｎ 可変フィレットを備えたタービンベーン
FR3017165B1 (fr) * 2014-02-05 2016-01-22 Snecma Pale pour une helice de turbomachine, notamment a soufflante non carenee, helice et turbomachine correspondantes
US9995166B2 (en) * 2014-11-21 2018-06-12 General Electric Company Turbomachine including a vane and method of assembling such turbomachine
FR3097262B1 (fr) * 2019-06-14 2023-03-31 Safran Aircraft Engines Pi Aji Aube de turbomachine avec talon optimise et procede d’optimisation d’un profil d’aube

Citations (4)

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Publication number Priority date Publication date Assignee Title
EP0441097A1 (de) 1990-02-07 1991-08-14 United Technologies Corporation Flügelprofil für die Verdichtungsstufe einer rotierenden Maschine
EP0833060A2 (de) 1996-09-30 1998-04-01 Kabushiki Kaisha Toshiba Schaufel für axiale Strömungsmaschine
EP1688586A1 (de) 2003-10-31 2006-08-09 Kabushiki Kaisha Toshiba Turbinenkaskadenkonstruktion
US20080099177A1 (en) * 2006-10-31 2008-05-01 General Electric Company Investment casting process and apparatus to facilitate superior grain structure in a DS turbine bucket with shroud

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SU1139185A1 (ru) * 1983-01-10 1997-01-27 Производственное Объединение Турбостроения "Ленинградский Металлический Завод" Рабочая лопатка турбомашины
RU2000443C1 (ru) * 1991-04-08 1993-09-07 Михаил Ефимович Дейч Соплова лопатка турбины
DE4344189C1 (de) * 1993-12-23 1995-08-03 Mtu Muenchen Gmbh Axial-Schaufelgitter mit gepfeilten Schaufelvorderkanten
RU2094170C1 (ru) * 1995-12-28 1997-10-27 Всероссийский научно-исследовательский институт авиационных материалов Способ получения охлаждаемой лопатки газотурбинного двигателя и охлаждаемая лопатка газотурбинного двигателя
US7175393B2 (en) * 2004-03-31 2007-02-13 Bharat Heavy Electricals Limited Transonic blade profiles
US7587818B2 (en) * 2004-12-23 2009-09-15 General Electric Company Repair of gas turbine blade tip without recoating the repaired blade tip
US7686582B2 (en) * 2006-07-28 2010-03-30 United Technologies Corporation Radial split serpentine microcircuits
US8172518B2 (en) * 2006-12-29 2012-05-08 General Electric Company Methods and apparatus for fabricating a rotor assembly

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0441097A1 (de) 1990-02-07 1991-08-14 United Technologies Corporation Flügelprofil für die Verdichtungsstufe einer rotierenden Maschine
EP0833060A2 (de) 1996-09-30 1998-04-01 Kabushiki Kaisha Toshiba Schaufel für axiale Strömungsmaschine
EP1688586A1 (de) 2003-10-31 2006-08-09 Kabushiki Kaisha Toshiba Turbinenkaskadenkonstruktion
US20080099177A1 (en) * 2006-10-31 2008-05-01 General Electric Company Investment casting process and apparatus to facilitate superior grain structure in a DS turbine bucket with shroud

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9163511B2 (en) 2012-08-09 2015-10-20 General Electric Company Steam turbine bucket tenon restoration through solid state bonding process

Also Published As

Publication number Publication date
CA2647154A1 (fr) 2009-06-14
RU2498082C2 (ru) 2013-11-10
US8128375B2 (en) 2012-03-06
JP2009144722A (ja) 2009-07-02
FR2924958B1 (fr) 2012-08-24
RU2008149419A (ru) 2010-06-20
US20090155085A1 (en) 2009-06-18
FR2924958A1 (fr) 2009-06-19
DE602008006153D1 (de) 2011-05-26
JP5462477B2 (ja) 2014-04-02
EP2071125B1 (de) 2011-04-13
CA2647154C (fr) 2015-11-24

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