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EP2746537B1 - Shrouded rotor blade with cutting tooth - Google Patents

Shrouded rotor blade with cutting tooth 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)
French (fr)
Other versions
EP2746537A1 (en
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 ES12198862.0T priority Critical patent/ES2579065T3/en
Priority to EP12198862.0A priority patent/EP2746537B1/en
Priority to US14/101,956 priority patent/US10221697B2/en
Publication of EP2746537A1 publication Critical patent/EP2746537A1/en
Application granted granted Critical
Publication of EP2746537B1 publication Critical patent/EP2746537B1/en
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
    • F01D5/14—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.

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

Description

Die vorliegende Erfindung betrifft eine Gasturbinenschaufel, insbesondere eine Turbinenschaufel mit einem Schaufelprofil, einem Deckband oder einem Deckbandabschnitt, und einem Schneidezahn gemäß Anspruch 1.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.

Aus der Praxis sind Turbinenschaufeln mit Schaufelprofilen bekannt, die Deckbänder mit Dichtlippen aufweisen. Diese sollen verhindern, dass das die Turbinen durchströmende Medium an der radial äußeren Kante der Turbinenschaufel vorbeiströmt, was den Wirkungsgrad der Turbine verringert.From practice turbine blades with blade profiles are known which have shrouds with sealing lips. These are intended to prevent the medium flowing through the turbines from flowing past the radially outer edge of the turbine blade, which reduces the efficiency of the turbine.

Aus der US 2008/075600 A1 ist ein Verfahren und eine Vorrichtung zur Herstellung von Turbinentriebwerke bekannt.From the US 2008/075600 A1 For example, a method and apparatus for producing turbine engines is known.

Aus der JP 8 303204 A ist eine bewegliche Schaufeldichtung für Gasturbinen bekannt.From the JP 8303204 A is a moving blade gas turbine gas turbine known.

Aus der WO 2010/034614 A1 ist eine Schaufelreihe für eine Endstufe einer Dampfturbine bekannt.From the WO 2010/034614 A1 is a row of blades for a final stage of a steam turbine known.

Eine Aufgabe der vorliegenden Erfindung ist es, eine weitere Turbinenschaufel mit einem Schaufelprofil, einem Deckband oder einem Deckbandabschnitt vorzuschlagen.An object of the present invention is to propose a further turbine blade with a blade profile, a shroud or a shroud section.

Die erfindungsgemäße Aufgabe kann durch eine Turbinenschaufel mit den Merkmalen des Anspruchs 1 gelöst werden.The object of the invention can be achieved by a turbine blade with the features of claim 1.

Erfindungsgemäß wird somit eine Turbinenschaufel mit einem Schaufelprofil vorgeschlagen, welche ein Deckband oder ein Deckbandabschnitt am oder im radial äußeren Bereich aufweist. Weiterhin weist die Turbinenschaufel in diesem radial äußeren Bereich wenigstens einen Schneidezahn auf, der zum wenigstens einmaligen Eingriff in wenigstens einen Einlaufbelag eines Turbinengehäuses im Gebrauch der Turbinenschaufel vorgesehen ist. Der Schneidezahn ist ein Abschnitt des Schaufelprofils. Der Schneidezahn kann bei einem ersten Anlaufen, einer ersten Rotation oder beim Starten des Triebwerks in eine Innenauskleidung des Gehäuses einschneiden und damit einen Spalt als Dichtspalt zwischen Turbinenschaufel und Turbinengehäuse erzeugen. Der Schneidezahn ist mit dem Deckband oder dem Deckbandabschnitt verbunden.According to the invention, a turbine blade with a blade profile is thus proposed 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.

Bei allen vorstehenden und folgenden Ausführungen ist der Gebrauch des Ausdrucks "kann sein" bzw. "kann haben" usw. synonym zu "ist vorzugsweise" bzw. "hat vorzugsweise" usw. zu verstehen und soll erfindungsgemäße Ausführungsformen erläutern.In all the above and following embodiments, the use of the term "may be" or "may have" etc. is synonymous with "preferably" or "preferably has", etc., and is intended to explain embodiments of the invention.

Vorteilhafte Weiterentwicklungen der vorliegenden Erfindung sind jeweils Gegenstand von Unteransprüchen und Ausführungsformen.Advantageous developments of the present invention are the subject of subclaims and embodiments.

Erfindungsgemäße Ausführungsformen können eines oder mehrere der im Folgenden genannten Merkmale aufweisen.Embodiments of the invention may include one or more of the features mentioned below.

In bestimmten erfindungsgemäßen Ausführungsformen ist der Schneidezahn zudem mit einer Dichtlippe des Deckbandes oder dem Deckbandabschnitt verbunden. Eine Dichtlippe kann eine Kante oder ein Steg des Deckbandes sein.In certain embodiments of the invention, 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.

In einigen erfindungsgemäßen Ausführungsformen ist der Schneidezahn ausgestaltet zum Erzeugen oder Vorbereiten einer Spaltdichtung zwischen der Turbinenschaufel und einem die Turbinenschaufel umgebenden Gehäuse, dem Turbinengehäuse. Die Spaltdichtung kann als Anstreifdichtung ausgestaltet sein.In some embodiments of the invention, 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.

In gewissen erfindungsgemäßen Ausführungsformen ist der Schneidezahn dazu vorgesehen, bei einer ersten Rotation oder beim Starten eines Triebwerks einen Teil, welcher als Einlaufbelag bezeichnet werden kann, einer Innenauskleidung des Turbinengehäuses einzuschneiden und derart zu streifen oder einen Teil der Auskleidung abzustreifen, dass sich anschließend ein Spalt als Dichtspalt zwischen Turbinenschaufel und Turbinengehäuse bildet. Die Innenauskleidung des Turbinengehäuses kann Dichtsegmente aufweisen, die zumindest teilweise eine sogenannte "Honigwaben"-Struktur aufweisen (englisch: "honeycombs"). Die Dichtsegmente können als Einlaufbelag ausgebildet sein. Die Innenauskleidung kann jedoch auch jede andere geeignete Form aufweisen.In certain embodiments of the invention, 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. However, the inner lining may also have any other suitable shape.

Der Schneidezahn ist ein Abschnitt des Schaufelprofils. Der Schneidezahn kann ein integraler Abschnitt des Schaufelprofils sein. "Integral" wird hierbei derart verstanden, dass der Schneidezahn und das Schaufelprofil als eine Einheit zu verstehen sind. Eine Einheit kann bedeuten, dass beide Teile (Schneidezahn und Schaufelprofil) aus einem Material und/oder in einem gemeinsamen Fertigungsverfahren oder Fertigungsschritt hergestellt wurden. Ferner kann eine Einheit bedeuten, dass beide Teile konstruktiv eine Form bilden und/oder eine gemeinsame Funktion erfüllen.The incisor is a section of the blade profile. The incisor may be an integral portion of the airfoil profile. In this case, "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.

In einigen erfindungsgemäßen Ausführungsformen ist der Schneidezahn mit dem Abschnitt des Schaufelprofils zudem auch ein Abschnitt des Deckbandes oder des Deckbandabschnitts. Der Schneidezahn kann zusammen mit dem Abschnitt des Schaufelprofils ein integraler Abschnitt des Deckbandes oder des Deckbandabschnitts sein. Ebenso kann der Schneidezahn gemeinsam mit dem integralen Abschnitt des Schaufelprofils ein integraler Abschnitt des Deckbandes oder des Deckbandabschnitts sein, oder umgekehrt.In some embodiments of the invention, the incisor with the portion of the blade profile is also a portion of the shroud or shroud portion. Of the Incisor may be an integral portion of the shroud or shroud portion along with the portion of the airfoil. Similarly, the incisor may be an integral portion of the shroud or shroud portion along with the integral portion of the airfoil, or vice versa.

Das Deckband der Turbinenschaufel weist in vielen erfindungsgemäßen Ausführungsformen eine vordere Dichtlippe und eine hintere Dichtlippe auf. Beide Dichtlippen erstrecken sich in radialer Richtung über eine Deckbandoberfläche des Deckbands hinaus oder stehen über diese über. Dabei kann die vordere Dichtlippe - absolut oder in radialer Richtung und/oder in Hauptanströmungsrichtung der Turbinenschaufel und nicht in Umfangsrichtung gesehen - länger in radialer Richtung und/oder in Hauptanströmungsrichtung der Turbinenschaufel ausgestaltet sein als die hintere Dichtlippe.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. In this case, the front sealing lip-seen absolutely or in the radial direction and / or in the main flow direction of the turbine blade and not in the circumferential direction-can be made longer in the radial direction and / or in the main flow direction of the turbine blade than the rear sealing lip.

In einigen erfindungsgemäßen Ausführungsformen weist das Deckband der Turbinenschaufel eine vordere Dichtlippe und eine hintere Dichtlippe auf. Beide Dichtlippen erstrecken sich in radialer Richtung über eine Deckbandoberfläche des Deckbands hinaus oder stehen über diese über. Dabei hat das Deckband zusammen mit seiner vorderen und seiner hinteren Dichtlippe in einer Schnittebene durch die Turbinenschaufel, welche senkrecht zur Deckbandoberfläche steht und welche sich in axialer Richtung der Turbinenschaufel erstreckt, die Form eines (ggfs. nach oben oder radial offenen) Trapez oder rechtwinkligen Trapez.In some embodiments of the invention, 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. In this case, the shroud, together with its front and rear sealing lips in a sectional plane through the turbine blade, which is perpendicular to the shroud surface and which extends in the axial direction of the turbine blade, the shape of a (possibly. Upwards or radially open) trapezoid or right angle trapezoid ,

In bestimmten erfindungsgemäßen Ausführungsformen ist der Schneidezahn mit dem Abschnitt des Schaufelprofils als Versteifungselement für das Deckband oder den Deckbandabschnitt ausgestaltet.In certain embodiments of the invention, the incisor is with the portion of the blade profile as Stiffening element designed for the shroud or the shroud section.

Mit dem Begriff "Versteifungselement" wird in einigen erfindungsgemäßen Ausführungsformen ein konstruktives Element verstanden, mit dessen Hilfe für den jeweiligen Abschnitt, welcher um das Versteifungselement herum angeordnet ist, oder für das gesamte Bauteil eine höhere Steifigkeit erreicht wird, beispielsweise verglichen mit einem Abschnitt oder Bauteil ohne Versteifungselement. Eine höhere Steifigkeit kann eine höhere Festigkeit und/oder eine höhere Stabilität des Bauteils bewirken. Weiterhin kann ein Versteifungselement zur Optimierung dynamischer Eigenschaften des jeweiligen Abschnitts oder des gesamten Bauteils dienen. Beispielsweise können die Schwingungseigenschaften aufgrund der Versteifung verändert werden, wie z.B. Verschiebungen der Resonanzfrequenz oder der Eigenfrequenz. Die Eigenfrequenz kann in weiter entfernte Schwingungsfrequenzbereiche in Bezug auf den Betriebspunkt und/oder Auslegungspunkt des Bauteils verschoben werden. Mit einem Versteifungselement können kritische Schwingungen vermieden oder verringert werden.The term "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. Furthermore, 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.

In manchen erfindungsgemäßen Ausführungsformen ist der Schneidezahn als durchgehende Verlängerung des Schaufelprofils ausgestaltet. Das Schaufelprofil kann beispielsweise in Richtung zur Dichtlippe des Deckbandes oder des Deckbandabschnitts und entlang dieser/diesem zunächst verlängert werden. Anschließend oder radial abschließend an diese Verlängerung kann der Schneidezahn ausgebildet sein (siehe auch Figur 2 und 3). Diese Verlängerung mit ausgebildetem Schneidezahn kann ein integrales Formteil sein, beispielsweise ein kontinuierliches Formteil mit ineinander übergehenden Oberflächen des Schneidezahns, der Dichtlippe des Deckbandes und dem verlängerten Schaufelprofil.In some embodiments of the invention, 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.

In bestimmten erfindungsgemäßen Ausführungsformen ist wenigstens ein Abschnitt des Deckbandes über einen Deckband-Rückschnitt hinaus verlängert.In certain embodiments of the invention, at least a portion of the shroud is extended beyond a shroud cutback.

Mit dem Begriff "Deckband-Rückschnitt" wird in einigen erfindungsgemäßen Ausführungsformen eine Deckbandbreite (damit ist die Deckbandbreite der Grundfläche oder Basisfläche des Deckbandes gemeint) verstanden, die kleiner ist als die senkrecht zur Rotationsachse projizierte Sehnenlänge der Turbinenschaufel. Dies bedeutet, dass die so projizierte Sehnenlänge der Turbinenschaufel das Deckband überragt. Damit wird jedoch nicht ausgesagt, dass mögliche Deckbandkanten, die nach aussen geneigt sein können, die Sehnenlänge nicht dennoch überragen können. Die Breite des "Deckband-Rückschnittes" gibt an, um welche Breite oder Distanz (z.B. in Millimeter oder Zentimeter) die Sehne der Turbinenschaufel das Deckband überragt, oder anders ausgedrückt, wie groß die Distanz des "Rückschnitts" des Deckbandes gegenüber der so projizierten Sehnenlänge der Turbinenschaufel ist. Zur weiteren Verdeutlichung des Begriffs wird auf die Fig. 3 als mögliche Ausführungsform verwiesen.The term "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.

In bestimmten erfindungsgemäßen Ausführungsformen sind der über den Deckband-Rückschnitt hinaus verlängerte Abschnitt des Deckbandes oder die Dichtlippe oder jeweils Abschnitte hiervon um wenigstens 10° (beispielsweise in einem Bereich von 10°-50°, 10°-30°, 10°-20°, 10°-15°) gegen eine Schaufellängsachse entgegen einer Hauptanströmungsrichtung der Turbinenschaufel, oder weniger als 80° (beispielsweise in einem Bereich von 50°-80°, 60°-80°, 70°-80°, 75°-80°) gegen die Hauptanströmungsrichtung der Schaufel, oder weniger als 80 Grad (beispielsweise in einem Bereich von 50°-80°, 60°-80°, 70°-80°, 75°-80°) gegen die axiale Erstreckung der äußeren Deckbandoberfläche geneigt. Die Deckbandoberfläche kann jene Fläche des Deckbandes in Umfangsrichtung der Turbine oder in axialer Richtung hiervon betrachtet werden (siehe dazu auch Fig. 1).In certain embodiments of the invention, 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 direction thereof (see also Fig. 1 ).

Manche oder alle erfindungsgemäßen Ausführungsformen können einen, mehrere oder alle der oben und/oder im Folgenden genannten Vorteile aufweisen.Some or all embodiments according to the invention may have one, several or all of the advantages mentioned above and / or below.

Die erfindungsgemäße Turbinenschaufel kann vorteilhaft bei unverändertem Deckbandrückschnitt einen größeren axialen Dichtspitzenabstand (der Dichtlippe) ermöglichen, was eine bessere Dichtungs-Überdeckung bei großen Axialverschiebungen ermöglicht.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.

Die erfindungsgemäße Turbinenschaufel kann vorteilhaft ein geringeres Gewicht haben als Turbinenschaufeln nach dem Stand der Technik.The turbine blade according to the invention may advantageously have a lower weight than turbine blades according to the prior art.

Die erfindungsgemäße Turbinenschaufel kann vorteilhaft durch eine geneigte Dichtlippe in Kombination mit dem Schneidezahn eine verringerte Dichtungs-Leckage aufweisen.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.

Mittels eines integralen Formteils mit ineinander übergehenden Oberflächen des Schneidezahns, der Dichtlippe des Deckbandes und dem verlängerten Schneidezahn kann vorteilhaft eine Massenansammlung an der Schaufelvorderkante (in Hauptanströmrichtung des Schaufelprofils) entfallen.By means of an integral molded part with mutually merging surfaces of the incisor, the sealing lip of the shroud and the extended incisor can advantageously account for a mass accumulation on the blade leading edge (in Hauptanströmrichtung the blade profile).

Die vorliegende Erfindung wird im Folgenden anhand der beigefügten Zeichnung, in welcher identische Bezugszeichen gleiche oder ähnliche Bauteile bezeichnen, exemplarisch erläutert. In den zum Teil stark vereinfachten Figuren gilt:

Fig. 1a
zeigt schematisch vereinfacht eine erfindungsgemäße Turbinenschaufel mit einem Deckband und einem Schneidezahn in perspektivischer Darstellung;
Fig. 1b
zeigt in Vergrößerung einen Ausschnitt aus Fig. 1a mit dem radialem Endabschnitt der erfindungsgemäßen Turbinenschaufel;
Fig. 2
zeigt das Deckband mit Schneidezahn in einer Seitenansicht;
Fig. 3
zeigt das Deckband der Fig. 2 mit Schneidezahn in einer weiteren Seitenansicht; und
Fig. 4
zeigt einen Schnitt durch das in Fig. 1b gezeigte Deckband.
The present invention will be explained in the following with reference to the accompanying drawings, in which identical reference numerals designate the same or similar components, by way of example. In the partially simplified figures:
Fig. 1a
shows schematically simplified a turbine blade according to the invention with a shroud and an incisor in a perspective view;
Fig. 1b
shows in enlargement a section Fig. 1a with the radial end portion of the turbine blade according to the invention;
Fig. 2
shows the shroud with incisor in a side view;
Fig. 3
shows the shroud the Fig. 2 with incisor in another side view; and
Fig. 4
shows a section through the in Fig. 1b Shroud shown.

Fig. 1a zeigt schematisch vereinfacht eine erfindungsgemäße Turbinenschaufel 100 mit einem Deckband 200, einem Schneidezahn 300, einem Schaufelprofil 1 und einer sich in x-Richtung erstreckenden Hauptanströmrichtung 3 in perspektivischer Darstellung. 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 Hauptanströmrichtung 3 in a perspective view.

Das Deckband 200 ist am radialen Ende des Schaufelprofils 1 positioniert.The shroud 200 is positioned at the radial end of the blade profile 1.

Die gesamte Turbinenschaufel 100 mit dem Deckband 200, dem Schneidezahn 300 und einem Schaufelfuß 400 kann als ein Gußteil hergestellt werden.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 zeigt einen Ausschnitt aus Fig. 1a mit vergrößertem radialem Endabschnitt der erfindungsgemäßen Turbinenschaufel 100 mit Deckband 200 und Scheidezahn 300. 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.

Das Deckband 200 weist eine Deckbandoberfläche 5 auf, die von einer stromauf (in Bezug auf die Hauptströmungsrichtung, d.h. in x-Richtung) gelegenen vorderen Dichtlippe 7a und einer stromab gelegenen hinteren Dichtlippe 7b begrenzt wird. Die Dichtlippen 7a, 7b sollen verhindern, dass das durchströmende Medium am radial äußeren Rand der Turbinenschaufel 100 zwischen Turbinenschaufel und Turbinengehäuse (nicht dargestellt) vorbeiströmt, sondern das Schaufelprofil 1 anströmen muss und so zur Energieübertragung der Turbinenschaufel 100 beiträgt.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 zeigt das Deckband 200 mit vorderer Dichtlippe 7a und hinterer Dichtlippe 7b, Schneidezahn 300 sowie einem Abschnitt des Schaufelprofils 1. Fig. 2 ist eine Seitenansicht. 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.

Das Schaufelprofil 1 ist mit dem Schneidezahn 300 mittels einer Schaufelprofilverlängerung 9 verbunden. Damit kann der Schneidezahn 300 als Abschnitt oder als integraler Abschnitt des Schaufelprofils 1 bezeichnet werden.The blade profile 1 is connected to the cutting tooth 300 by means of a blade profile extension 9. Thus, the cutting tooth 300 may be referred to as a section or as an integral portion of the blade profile 1.

Weiterhin sind sowohl der Schneidezahn 300 als auch das Schaufelprofil 1 mittels der Schaufelprofilverlängerung 9 auch mit dem Deckband 200 mittels der vorderen Dichtlippe 7a, die ein Abschnitt des Deckbandes 200 ist, verbunden. Die Einheit Schneidezahn 300, Schaufelabschnitt 9 und vordere Dichtlippe 7a kann als ein integraler Abschnitt der Turbinenschaufel 100 ausgestaltet sein.Furthermore, 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 zeigt das Deckband 200 mit vorderer Dichtlippe 7a, Schneidezahn 300 sowie einem Abschnitt des Schaufelprofils 1. Fig. 3 zeigt einen Ausschnitt aus Fig. 2 in einer weiteren Ansicht. 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.

In Fig. 3 wird ein Deckband-Rückschnitt 11 als Abstand zwischen der vorderen Kante 13 der Grundfläche des Deckbandes 200 und dem vorderen (in Bezug auf die Hauptströmungsrichtung in x-Richtung stromauf gelegenen) Ende des Schaufelprofils 1 gezeigt. Die vordere Dichtlippe 7a ist erfindungsgemäß nach vorne (d.h. gegen die x-Richtung) geneigt oder gekippt, in der in Fig. 3 gezeigten Ausführungsform beispielhaft um einen Neigungswinkel 15 von ca. 33 Grad. Weiterhin ist die vordere Dichtlippe 7a nicht nur nach vorne geneigt, sondern erstreckt sich erfindungsgemäß über den Deckband-Rückschnitt 11 hinaus. In Fig. 3 wird diese Erstreckung über den Deckband-Rückschnitt 11 hinaus mittels der Distanz 17 dargestellt.In Fig. 3 For example, 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. According to the invention, 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. Furthermore, 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.

Die Erstreckung der vorderen Dichtlippe 7a über den Deckband-Rückschnitt 11 hinaus stellt zusammen mit der Integration, oder Verschmelzung, des Schaufelprofils 1 mit dem Schneidezahn 300 mittels der Schaufelverlängerung 9 eine vorteilhafte konstruktive Ausgestaltung beispielsweise hinsichtlich der Steifigkeit dar. Die Schaufelverlängerung 9 kann auch als "unterbauende Rippe" unterhalb der vorderen Dichtlippe 7a des Deckbandes 200 verstanden werden.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 zeigt einen Schnitt durch das in Fig. 1b gezeigte Deckband 200 der Turbinenschaufel 100. Sowohl die vordere Dichtlippe 7a als auch die hintere Dichtlippe 7b das Deckbands 200 erstrecken sich in radialer Richtung über die Deckbandoberfläche 5 des Deckbands 200 hinaus. Dabei bildet die Deckbandoberfläche 5 zusammen mit der vorderen und der hinteren Dichtlippe 7a, 7b in der der Zeichenebene von Fig. 4 entsprechenden Schnittebene, welche senkrecht zur Deckbandoberfläche 5 steht und welche sich in axialer Richtung der Turbinenschaufel 100 erstreckt, die Form eines Trapez oder - wie in Fig. 4 gezeigt - eines rechtwinkligen Trapez. Bezugszeichenliste Bezugszeichen Beschreibung 100 Turbinenschaufel 200 Deckband 300 Schneidezahn 400 Schaufelfuß 1 Schaufelprofil 3 Hauptanströmrichtung 5 Deckbandoberfläche 7a vordere Dichtlippe 7b hintere Dichtlippe 9 Schaufelprofilverlängerung 11 Deckband-Rückschnitt 13 äußere Kante der Grundfläche des Deckbandes 14 vorderes Ende des Schaufelprofils 15 Neigungswinkel 17 Distanz; Erstreckung über den Deckband-Rückschnitt hinaus 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. In this case, 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. <B> LIST OF REFERENCES </ b> reference numeral description 100 turbine blade 200 shroud 300 incisor 400 blade 1 blade profile 3 Hauptanströmrichtung 5 Shroud surface 7a front sealing lip 7b rear sealing lip 9 Blade profile extension 11 Shroud-pruning 13 outer edge of the base of the shroud 14 front end of the blade profile 15 tilt angle 17 Distance; Extension beyond the cover band cutback

Claims (7)

  1. A rotor blade (100) having a blade profile (1), wherein the rotor blade (100) has, in its radially outer region, at least one shroud (200) or at least one shroud section as well as at least one cutting tooth (300) for the at least one-time engagement of at least one inlet coating of a rotor housing using the rotor blade, and wherein the cutting tooth (300) is connected with the shroud (200) or the shroud section,
    characterized in that
    the cutting tooth is a section of the blade profile (1).
  2. The rotor blade (100) according to claim 1, wherein the cutting tooth (300) is a section of the shroud (200) or of the shroud section.
  3. The rotor blade (100) according to claim 1 or 2, wherein the cutting tooth (300) with the section of the blade profile (1) is formed as a stiffening element for the shroud (200) or the shroud section.
  4. The rotor blade (100) according to one of the preceding claims, wherein at least one section of the shroud (200) is extended beyond a cut back (11) of the shroud.
  5. The rotor blade (100) according to claim 4, wherein the section of the shroud (200) extended beyond the cut back (11) of the shroud is inclined by at least 10 degrees against a longitudinal axis of the blade against a main flow direction (3) of the rotor blade.
  6. The rotor blade (100) according to one of the preceding claims, wherein the shroud (200) has a front sealing lip (7a) and a rear sealing lip (7b) which extend in the radial direction beyond a shroud surface (5) of the shroud (200), wherein the front sealing lip (7a) has a longer form than the rear sealing lip (7b).
  7. The rotor blade (100) according to one of the preceding claims, wherein the shroud (200) has a front sealing lip (7a) and a rear sealing lip (7b) which extend in the radial direction beyond a shroud surface (5) of the shroud (200), wherein the shroud (200) with its front and its rear sealing lip (7a, 7b) has the form of a trapezoid or of a rectangular trapezoid in a sectional plane through the rotor blade (100) which is perpendicular to the shroud surface (5) and which extends in the axial direction of the rotor blade (100).
EP12198862.0A 2012-12-21 2012-12-21 Shrouded rotor blade with cutting tooth Active EP2746537B1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
ES12198862.0T ES2579065T3 (en) 2012-12-21 2012-12-21 Turbine blade with reinforcement ring and cutting tooth
EP12198862.0A EP2746537B1 (en) 2012-12-21 2012-12-21 Shrouded rotor blade with cutting tooth
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 (en) 2012-12-21 2012-12-21 Shrouded rotor blade with cutting tooth

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EP2746537B1 true EP2746537B1 (en) 2016-06-22

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WO2019122541A1 (en) * 2017-12-19 2019-06-27 Safran Helicopter Engines Turbine wheel
DE102018200964A1 (en) * 2018-01-23 2019-07-25 MTU Aero Engines AG Rotor bucket cover for a turbomachine, rotor blade, method of making a rotor blade shroud and a rotor blade
FR3085993B1 (en) 2018-09-17 2020-12-25 Safran Aircraft Engines MOBILE DAWN FOR ONE WHEEL OF A TURBOMACHINE

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JPH08303204A (en) * 1995-05-08 1996-11-19 Ishikawajima Harima Heavy Ind Co Ltd Gas turbine rotor blade seal structure
US7686568B2 (en) * 2006-09-22 2010-03-30 General Electric Company Methods and apparatus for fabricating turbine engines
DE102007031711A1 (en) * 2007-07-06 2009-01-08 Rolls-Royce Deutschland Ltd & Co Kg Housing shroud segment suspension
CH699598A1 (en) * 2008-09-29 2010-03-31 Alstom Technology Ltd Blade row for the final stage of a steam turbine.
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

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US10221697B2 (en) 2019-03-05
ES2579065T3 (en) 2016-08-04
US20140178201A1 (en) 2014-06-26

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