EP2746537B1 - Aube rotorique carénée avec dent de coupe - Google Patents

Aube rotorique carénée avec dent de coupe Download PDF

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Publication number
EP2746537B1
EP2746537B1 EP12198862.0A EP12198862A EP2746537B1 EP 2746537 B1 EP2746537 B1 EP 2746537B1 EP 12198862 A EP12198862 A EP 12198862A EP 2746537 B1 EP2746537 B1 EP 2746537B1
Authority
EP
European Patent Office
Prior art keywords
shroud
blade
rotor blade
sealing lip
section
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
EP12198862.0A
Other languages
German (de)
English (en)
Other versions
EP2746537A1 (fr
Inventor
Alexander Böck
Stephen Royston Williams
Manfred Feldmann
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP12198862.0A priority Critical patent/EP2746537B1/fr
Priority to ES12198862.0T priority patent/ES2579065T3/es
Priority to US14/101,956 priority patent/US10221697B2/en
Publication of EP2746537A1 publication Critical patent/EP2746537A1/fr
Application granted granted Critical
Publication of EP2746537B1 publication Critical patent/EP2746537B1/fr
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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
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F01D11/125—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material with a reinforcing structure
    • 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
    • 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
    • F05D2240/304—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 trailing edge of a rotor blade

Definitions

  • the present invention relates to a gas turbine blade, in particular a turbine blade with a blade profile, a shroud or a shroud section, and an incisor according to claim 1.
  • An object of the present invention is to propose a further turbine blade with a blade profile, a shroud or a shroud section.
  • the object of the invention can be achieved by a turbine blade with the features of claim 1.
  • a turbine blade with a blade profile which a shroud or a Shroud section on or in the radially outer region. Furthermore, the turbine blade in this radially outer region at least one incisor, which is provided for at least one engagement in at least one inlet lining of a turbine housing in the use of the turbine blade.
  • the incisor is a section of the blade profile. The incisor may cut at an initial start, a first rotation or when starting the engine in an inner lining of the housing and thus create a gap as a sealing gap between the turbine blade and the turbine housing.
  • the incisor is connected to the shroud or shroud section.
  • Embodiments of the invention may include one or more of the features mentioned below.
  • the incisor is also connected to a sealing lip of the shroud or the shroud portion.
  • a sealing lip may be an edge or a web of the shroud.
  • the incisor is configured to produce or prepare a Gap between the turbine blade and a housing surrounding the turbine blade, the turbine housing.
  • the gap seal can be designed as a rubbing seal.
  • the incisor is provided to cut a portion, which may be referred to as inlet lining, of an inner lining of the turbine housing and strip or strip a portion of the liner during a first rotation or engine start-up, followed by a gap forms as a sealing gap between the turbine blade and turbine housing.
  • the inner lining of the turbine housing may have sealing segments that at least partially have a so-called “honeycomb” structure (English: “honeycombs").
  • the sealing segments may be formed as inlet lining.
  • the inner lining may also have any other suitable shape.
  • the incisor is a section of the blade profile.
  • the incisor may be an integral portion of the airfoil profile.
  • integral is understood such that the incisor and the blade profile are to be understood as one unit.
  • a unit may mean that both parts (incisor and blade profile) are made of one material and / or in a common manufacturing process or manufacturing step. Furthermore, a unit may mean that both parts constructively form a shape and / or fulfill a common function.
  • the incisor with the portion of the blade profile is also a portion of the shroud or shroud portion.
  • the Incisor may be an integral portion of the shroud or shroud portion along with the portion of the airfoil.
  • the incisor may be an integral portion of the shroud or shroud portion along with the integral portion of the airfoil, or vice versa.
  • the shroud of the turbine blade has, in many embodiments according to the invention, a front sealing lip and a rear sealing lip. Both sealing lips extend in the radial direction beyond a shroud surface of the shroud or over this over.
  • the shroud of the turbine blade has a forward sealing lip and a rearward sealing lip. Both sealing lips extend in the radial direction beyond a shroud surface of the shroud or over this over.
  • the incisor is with the portion of the blade profile as Stiffening element designed for the shroud or the shroud section.
  • stiffening element is understood in some embodiments according to the invention to be a constructive element with the aid of which a higher rigidity is achieved for the respective section which is arranged around the stiffening element or for the entire component, for example compared to a section or component without stiffening element.
  • a higher rigidity can bring about a higher strength and / or a higher stability of the component.
  • a stiffening element can serve to optimize dynamic properties of the respective section or of the entire component. For example, the vibration characteristics due to the stiffening may be altered, such as e.g. Shifts in the resonant frequency or the natural frequency. The natural frequency can be shifted to more distant oscillation frequency ranges with respect to the operating point and / or design point of the component. With a stiffening element critical vibrations can be avoided or reduced.
  • the incisor is designed as a continuous extension of the blade profile.
  • the blade profile can be lengthened, for example, in the direction of the sealing lip of the shroud or shroud section and along this / this first. Subsequently or radially closing to this extension of the incisor can be formed (see also FIG. 2 and 3 ).
  • This extension with trained incisor can be an integral molding, for example, a continuous molding with each other transition surfaces of the incisor, the sealing lip of the shroud and the extended blade profile.
  • At least a portion of the shroud is extended beyond a shroud cutback.
  • shroud cutback in some embodiments of the invention, a shroud width (meaning the shroud width of the base or base surface of the shroud meant), which is smaller than the projected perpendicular to the rotation axis chord length of the turbine blade. This means that the chord length of the turbine blade projected in this way projects beyond the shroud. However, this does not say that possible shroud edges, which may be inclined outwards, can not project beyond the chord length.
  • the width of the "shroud cutback” indicates by what width or distance (eg in millimeters or centimeters) the chord of the turbine blade overhangs the shroud, or in other words, how large the distance of the "cutback" of the shroud from the chord length thus projected the turbine blade is. To further clarify the term is on the Fig. 3 as a possible embodiment.
  • the portion of the shroud extending beyond the shroud cutback or the sealing lip or portions thereof are at least 10 ° (eg, in a range of 10 ° -50 °, 10 ° -30 °, 10 ° -20 ° , 10 ° -15 °) against a blade longitudinal axis against a main direction of flow of the turbine blade, or less than 80 ° (for example, in FIG a range of 50 ° -80 °, 60 ° -80 °, 70 ° -80 °, 75 ° -80 °) against the main inflow direction of the blade, or less than 80 degrees (for example in a range of 50 ° -80 °, 60 ° -80 °, 70 ° -80 °, 75 ° -80 °) are inclined against the axial extent of the outer shroud surface.
  • the shroud surface may be that area of the shroud in the circumferential direction of the turbine or viewed in the axial
  • Some or all embodiments according to the invention may have one, several or all of the advantages mentioned above and / or below.
  • the turbine blade according to the invention can advantageously allow a larger axial sealing tip distance (the sealing lip) with unchanged cover band recess, which allows better sealing overlap with large axial displacements.
  • the turbine blade according to the invention may advantageously have a lower weight than turbine blades according to the prior art.
  • the turbine blade according to the invention can advantageously have a reduced sealing leakage by means of an inclined sealing lip in combination with the incisor tooth.
  • the sealing lip of the shroud and the extended incisor can advantageously account for a mass accumulation on the blade leading edge (in Hauptanströmraum the blade profile).
  • Fig. 1a schematically shows schematically a turbine blade 100 according to the invention with a shroud 200, an incisor 300, a blade profile 1 and extending in the x direction Hauptanströmcardi 3 in a perspective view.
  • the shroud 200 is positioned at the radial end of the blade profile 1.
  • the entire turbine blade 100 with the shroud 200, the cutting tooth 300, and a blade root 400 may be manufactured as a casting.
  • Fig. 1b shows a section Fig. 1a with enlarged radial end section of the turbine blade 100 according to the invention with shroud 200 and sheath tooth 300.
  • the shroud 200 has a shroud surface 5 bounded by an upstream (relative to the main flow direction, i.e., in the x-direction) front seal lip 7a and a downstream rear seal lip 7b.
  • the sealing lips 7a, 7b are intended to prevent the medium flowing through flows past the radially outer edge of the turbine blade 100 between the turbine blade and the turbine housing (not shown), but must flow against the blade profile 1 and thus contribute to the energy transfer of the turbine blade 100.
  • Fig. 2 shows the shroud 200 with front sealing lip 7a and rear sealing lip 7b, cutting tooth 300 and a portion of the blade profile.
  • 1 Fig. 2 is a side view.
  • the blade profile 1 is connected to the cutting tooth 300 by means of a blade profile extension 9.
  • the cutting tooth 300 may be referred to as a section or as an integral portion of the blade profile 1.
  • both the cutting tooth 300 and the blade profile 1 are connected by means of the blade profile extension 9 with the shroud 200 by means of the front sealing lip 7 a, which is a portion of the shroud 200.
  • the Unit of incisor 300, blade portion 9, and front sealing lip 7a may be configured as an integral portion of turbine blade 100.
  • Fig. 3 shows the shroud 200 with front sealing lip 7a, cutting tooth 300 and a portion of the blade profile. 1 Fig. 3 shows a section Fig. 2 in another view.
  • a shroud cutback 11 is shown as a distance between the leading edge 13 of the base of the shroud 200 and the forward (in the x-direction upstream) end of the airfoil 1.
  • the front sealing lip 7a is inclined or tilted forwards (that is to say in the direction of the x direction) in the in Fig. 3 shown embodiment by an inclination angle 15 of about 33 degrees.
  • the front sealing lip 7a is not only inclined forward, but according to the invention extends beyond the shroud cutback 11 addition. In Fig. 3 this extension is represented by the distance 17 beyond the cover band cutback 11.
  • the extension of the front sealing lip 7a beyond the shroud cutback 11 addition, together with the integration, or merging, of the blade profile 1 with the cutting tooth 300 by means of the blade extension 9 an advantageous structural design, for example, in terms of stiffness.
  • the blade extension 9 can also as " Underlying rib "below the front sealing lip 7a of the shroud 200 are understood.
  • Fig. 4 shows a section through the in Fig. 1b shown shroud 200 of the turbine blade 100.
  • Both the front Sealing lip 7a and the rear sealing lip 7b of the shroud 200 extend in the radial direction beyond the shroud surface 5 of the shroud 200 addition.
  • the shroud surface 5 forms together with the front and the rear sealing lip 7a, 7b in the plane of Fig. 4 corresponding sectional plane, which is perpendicular to the shroud surface 5 and which extends in the axial direction of the turbine blade 100, the shape of a trapezoid or - as in Fig. 4 shown - a rectangular trapezoid.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (7)

  1. Aube rotorique (100) présentant un profil d'aube (1), l'aube rotorique (100) comportant dans sa zone radialement extérieure au moins un profil caréné (200) ou au moins une partie de profil caréné et au moins une dent de coupe (300) destinée à s'engager au moins une fois dans l'au moins un revêtement de guidage d'un boîtier de turbine en cours d'utilisation de l'aube rotorique (100) et la dent de coupe (300) étant reliée au profil caréné (200) ou la partie de profil caréné,
    caractérisée en ce que
    la dent de coupe est une partie du profil (1).
  2. Aube rotorique (100) selon la revendication 1, dans laquelle la dent de coupe (300) est une partie du profil caréné (200) ou de la partie de profil caréné.
  3. Aube rotorique (100) selon la revendication 1 ou 2, dans laquelle la dent de coupe (300) pourvue de la partie du profil (1) est configurée en élément de renfort du profil caréné (200) ou de la partie de profil caréné.
  4. Aube rotorique (100) selon l'une des revendications précédentes, dans laquelle au moins une partie du profil caréné (200) s'étend au-delà d'une découpe en retrait (11) du profil caréné.
  5. Aube rotorique (100) selon la revendication 4, la partie du profil caréné (200) qui s'étend au-delà de la découpe en retrait (11) du profil caréné est inclinée d'au moins 10° par rapport à un axe longitudinal d'aube dans une direction d'écoulement principale (3) de l'aube rotorique.
  6. Aube rotorique (100) selon l'une des revendications précédentes, dans laquelle le profil caréné (200) comporte une lèvre d'étanchéité avant (7a) et une lèvre d'étanchéité arrière (7b) qui s'étend dans une direction radiale au-delà d'une surface (5) du profil caréné (200), la lèvre d'étanchéité avant (7a) étant plus longue que la lèvre d'étanchéité arrière (7b).
  7. Aube rotorique (100) selon l'une des revendications précédentes, dans laquelle le profil caréné (200) comporte une lèvre d'étanchéité avant (7a) et une lèvre d'étanchéité arrière (7b) qui s'étendent dans une direction radiale au-delà d'une surface (5) du profil caréné (200), le profil caréné (200) pourvu de ses lèvre d'étanchéité avant et arrière (7a, 7b) ayant la forme d'un trapèze ou d'un trapèze rectangle dans un plan de coupe, passant par l'aube rotorique (100), qui est perpendiculaire à la surface (5) du profil caréné et qui s'étend dans une direction axiale de l'aube rotorique (100).
EP12198862.0A 2012-12-21 2012-12-21 Aube rotorique carénée avec dent de coupe Active EP2746537B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP12198862.0A EP2746537B1 (fr) 2012-12-21 2012-12-21 Aube rotorique carénée avec dent de coupe
ES12198862.0T ES2579065T3 (es) 2012-12-21 2012-12-21 Álabe de turbina con anillo de refuerzo y diente de corte
US14/101,956 US10221697B2 (en) 2012-12-21 2013-12-10 Turbine blade having a shroud and a cutting tooth

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12198862.0A EP2746537B1 (fr) 2012-12-21 2012-12-21 Aube rotorique carénée avec dent de coupe

Publications (2)

Publication Number Publication Date
EP2746537A1 EP2746537A1 (fr) 2014-06-25
EP2746537B1 true EP2746537B1 (fr) 2016-06-22

Family

ID=47552811

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12198862.0A Active EP2746537B1 (fr) 2012-12-21 2012-12-21 Aube rotorique carénée avec dent de coupe

Country Status (3)

Country Link
US (1) US10221697B2 (fr)
EP (1) EP2746537B1 (fr)
ES (1) ES2579065T3 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3728796A1 (fr) * 2017-12-19 2020-10-28 Safran Helicopter Engines Roue de turbine
DE102018200964A1 (de) * 2018-01-23 2019-07-25 MTU Aero Engines AG Rotorschaufeldeckband für eine Strömungsmaschine, Rotorschaufel, Verfahren zum Herstellen eines Rotorschaufeldeckbands und einer Rotorschaufel
FR3085993B1 (fr) * 2018-09-17 2020-12-25 Safran Aircraft Engines Aube mobile pour une roue d'une turbomachine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH08303204A (ja) * 1995-05-08 1996-11-19 Ishikawajima Harima Heavy Ind Co Ltd ガスタービンの動翼シール構造
US7686568B2 (en) * 2006-09-22 2010-03-30 General Electric Company Methods and apparatus for fabricating turbine engines
DE102007031711A1 (de) * 2007-07-06 2009-01-08 Rolls-Royce Deutschland Ltd & Co Kg Gehäusedeckbandsegment-Aufhängung
CH699598A1 (de) * 2008-09-29 2010-03-31 Alstom Technology Ltd Schaufelreihe für die Endstufe einer Dampfturbine.
US20120195742A1 (en) * 2011-01-28 2012-08-02 Jain Sanjeev Kumar Turbine bucket for use in gas turbine engines and methods for fabricating the same
US9163519B2 (en) * 2011-07-28 2015-10-20 General Electric Company Cap for ceramic blade tip shroud

Also Published As

Publication number Publication date
US10221697B2 (en) 2019-03-05
US20140178201A1 (en) 2014-06-26
ES2579065T3 (es) 2016-08-04
EP2746537A1 (fr) 2014-06-25

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