EP2848770B1 - Pale de rotor d'une turbomachine axiale et élément d'amortissement - Google Patents

Pale de rotor d'une turbomachine axiale et élément d'amortissement Download PDF

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Publication number
EP2848770B1
EP2848770B1 EP13184785.7A EP13184785A EP2848770B1 EP 2848770 B1 EP2848770 B1 EP 2848770B1 EP 13184785 A EP13184785 A EP 13184785A EP 2848770 B1 EP2848770 B1 EP 2848770B1
Authority
EP
European Patent Office
Prior art keywords
damping element
blade
pocket
impeller blade
impeller
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.)
Not-in-force
Application number
EP13184785.7A
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German (de)
English (en)
Other versions
EP2848770A1 (fr
Inventor
Martin Pernleitner
Manfred Schill
Rudolf Stanka
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
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MTU Aero Engines AG
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Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to ES13184785.7T priority Critical patent/ES2622424T3/es
Priority to EP13184785.7A priority patent/EP2848770B1/fr
Publication of EP2848770A1 publication Critical patent/EP2848770A1/fr
Application granted granted Critical
Publication of EP2848770B1 publication Critical patent/EP2848770B1/fr
Not-in-force 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations

Definitions

  • the present invention relates to an impeller blade of an axial flow machine, with a blade root, an airfoil and a blade platform according to the preamble of claim 1.
  • a generic impeller blade is for example from EP 2 280 151 A1 , of the EP 0 437 977 A1 , of the WO 2010/051453 A2 and the US 3,887,298 A known.
  • An object of the present invention is to propose a blade for axial flow machines, which allows easy positioning of damping elements without position elements and thus without additional weight. It is another object of the present invention to provide a damping element for inclusion in a blade according to the invention.
  • an impeller blade of an axial flow machine which has at least one blade root, an airfoil and a blade platform.
  • the impeller blade is fixed by means of the blade root on a rotor disk of the turbomachine.
  • On the rotor disk further impeller blades are arranged, which are positioned in the circumferential direction.
  • the Impeller blade on a pocket-shaped body, which is arranged below the blade and above the blade root and in the region of the blade platform.
  • the bag-shaped body is bounded by axial and radial webs, preferably completely or in sections thereof.
  • a damping element is arranged within these axial and radial webs.
  • the bag-shaped body is arranged in or on a cavity of the blade platform.
  • the cavity forms an enlarged cavity with another cavity of an impeller blade adjacent to the rotor disk.
  • the pocket-shaped body also forms, with another pocket-shaped body with a blade adjacent to the rotor disk, an enlarged pocket-shaped body for receiving the damping element.
  • Embodiments of the invention may include one or more of the features mentioned below.
  • gas turbines are described as axial flow machines purely by way of example, but without wishing to restrict axial flow machines to gas turbines.
  • the blade root has a shape with which the blade root is connected to the rotor disk (in the axial direction of the gas turbine), in particular is detachably connected again.
  • the blade root can be pushed into a groove in the rotor disk.
  • the blade root may have a so-called dovetail shape.
  • the blade platform has a front, a middle and a rear blade platform area, each viewed in the direction of flow of the gas turbine.
  • the front and the rear blade platform area may be formed as a web or as a collar.
  • the blade platform in particular the middle blade platform, connects the blade root with the blade leaf.
  • the airfoil, blade platform, and blade shape are made in one piece.
  • Such a component may be referred to as "integral.”
  • the impeller blade and the further impeller blades are arranged side by side on the rotor disk, in particular parallel next to one another.
  • the bag-shaped body is cup-shaped or trough-shaped.
  • the bag-shaped body may have a depth, a length and a width.
  • the pocket-shaped body has in particular an open cross-section.
  • the shape of the open cross section may be round, oval, square, polygonal or other shape.
  • the bag-shaped body has a rectangular shell shape with rounded corners.
  • the radially outer wall and the radially inner wall is aligned parallel to the axis of rotation of the gas turbine.
  • the axially front and the axially rear wall (viewed in the flow direction) aligned radially.
  • the axially parallel walls can be referred to as horizontal walls and the walls in radial alignment as vertical walls.
  • the walls of the pocket-shaped body are at least partially referred to as webs.
  • the pocket-shaped body is bounded, at least in sections, by axial webs (or axially parallel as viewed in the flow direction) and the webs have a closed shape in a plane perpendicular to the flow direction.
  • the axial and radial webs have an open shape in a plane perpendicular to the flow direction of the pocket-shaped body, wherein in particular the radially inner web is open.
  • the radially inner web has a breakthrough, so that the bag-shaped body is open to the adjacent cavity.
  • the cavity is cup-shaped or trough-shaped.
  • the cavity may have a depth, a length and a width.
  • the cavity has in particular an open cross section.
  • the shape of the open cross section may be round, oval, square, polygonal or other shape.
  • the cavity may have one or more undercuts.
  • the cavity has a wall, in particular towards the root of the blade.
  • these walls can seal the cavity towards the blade root.
  • a sealing gap eg for compensating thermal expansions in the operating state
  • the cavity is open to the blade root.
  • the extended bag-shaped body is symmetrical to the two bag-shaped bodies of the paddle platform that form the extended bag-shaped body.
  • the plane of symmetry is in particular the plane of the open cross-section of both pocket-shaped bodies, on which the two bodies are brought together.
  • a damping element is an element or body that dampens mechanical vibrations of a dynamic system.
  • a damping element may be made of plastic or of another material.
  • a damping element may have specific material properties for mechanical vibrations of a dynamic system (eg, specific visco-elastic properties).
  • a damping element may have a specific weight for a dynamic system (eg, to dampen certain resonances or certain vibration frequencies). By way of example only, the weight of the damping element can be between 1.5 g and 4 g, in particular 2.5 g.
  • the damping element is solid in some embodiments of the invention. However, the damping element may also be hollow inside.
  • the widened cavity and / or the widened pocket-shaped body has a sealing gap, in particular a thermal sealing gap.
  • a thermal sealing gap can compensate for material expansion during a material heating, thus avoiding possible stress peaks in the material or material distortion or material breakage.
  • the bag-shaped body has an opening to the cavity.
  • An opening may be an open wall portion, an open boundary or a hole in a wall between the bag-shaped body and the cavity.
  • the opening between the bag-shaped body and the cavity is arranged parallel to the axis of rotation of the gas turbine.
  • the damping element has a length L D in the axial direction a and a width W D in the circumferential direction u perpendicular to the axial direction a, wherein the axial direction a is the axis of rotation of the gas turbine.
  • the ratio of the length L D to the width W D is smaller than 1 according to the invention.
  • the damping element is arranged in its longitudinal direction in the enlarged pocket-shaped body parallel to the axis of rotation of the turbomachine.
  • the damping element is configured in a cross section perpendicular to the longitudinal direction symmetrical to the vertical center axis of the damping element.
  • the damping element is designed trapezoidal or rectangular in a cross section perpendicular to the longitudinal orientation.
  • the length L D of the damping element is at least 1 mm smaller than the length L T of the extended pocket-shaped body of the impeller blade and / or the width W L of the damping element is at least 1 mm smaller than the width W T of the pocket portion of the impeller blade ,
  • the damping element is arranged symmetrically in the enlarged pocket-shaped body of two adjacent blades.
  • Some or all embodiments according to the invention may have one, several or all of the advantages mentioned above and / or below.
  • damping elements can be used, their use no further positioning aids for the damping elements in make the blades necessary and thus advantageously cause no weight increase.
  • the damping element according to the invention is advantageously easy to handle and to be introduced into pocket-shaped bodies or other areas in impeller blades.
  • damping elements can advantageously be positioned well, simply and accurately.
  • Fig. 1 shows a side view of an impeller blade 100 according to the invention with a cavity 1 and a bag-shaped body. 3
  • the impeller blades 100 have a blade root 5, an airfoil 7 and a blade platform 9.
  • the impeller vane 100 is integral, at least with respect to the vane root 5, the airfoil 7 and the vane platform 9.
  • the impeller vane 100 is made of, for example, a casting alloy.
  • the blade platform 9 has a front 11, a middle 13 and a rear 15 blade platform area.
  • the front 11 and the rear 15 blade platform area are formed as a shoulder or as a collar.
  • the bag-shaped body 3 has an approximately square shell shape with rounded corners and with a chamfer in the interior in the rear (seen in the axial direction, a downstream) area.
  • the bag-shaped body 3 may be referred to as a closed box, with an opening in the axial-radial plane (in the direction perpendicular to the plane of the drawing).
  • the pocket-shaped body 3 has two axial webs 29 and two radial webs 31.
  • the illustrated closed shell shape of the bag-shaped body 3 can in a further embodiment (see Fig. 6 ) have an opening or an opening in one of the webs or the walls, in particular to the cavity 1 out.
  • Fig. 2 shows a longitudinal sectional view of the impeller blade 100 according to the invention with the cavity 1, the pocket-shaped body 3 and a damping element 17th
  • a web width 19 at the rear end of the middle blade platform area viewed in the axial direction may, by way of example only, have a value of approximately 1.25 mm.
  • the damping element 17 has a square cross-sectional shape in this sectional view.
  • the damping element 17 fills a part of the volume of the bag-shaped body 3.
  • Fig. 3 shows a longitudinal section AA (see in FIG Fig. 1 and in Fig. 2 the sectional planes AA) in the circumferential direction of two juxtaposed impeller blades 100 according to the invention with the damping element 17.
  • the damping element 17 has a width W D and a length L D.
  • the damping element 17 is arranged centrally in the pocket-shaped body 3, surrounded by a respective gap.
  • the two cavities 1 increase to an enlarged cavity 21.
  • the two pocket-shaped body 3 enlarge to an enlarged pocket-shaped body 23rd
  • Fig. 4 shows a cross-sectional view BB (see in FIG Fig. 1 and in Fig. 2 the sectional planes BB) in the radial direction r of two juxtaposed impeller blades 100 according to the invention with the damping element 17.
  • the damping element 17 has a trapezoidal cross-section and a height H D and a width W D.
  • the damping element 17 is arranged centrally in the pocket-shaped body 3, but is located in the radially outer region on the walls and the axial webs 29 of the two bag-shaped body 3 (in the operating state, the damping element 17 is pressed due to the radial forces on the radially outer walls). Below the damping element 17, a gap 27 is shown below the damping element 17, a gap 27 is shown below the damping element 17, a gap 27 is shown below the damping element 17, a gap 27 is shown below the damping element 17, a gap 27 is shown below the damping element 17, a gap 27 is shown below the damping element 17, a gap 27 is shown below the damping element 17, a gap 27 is shown below the damping element 17, a gap 27 is shown below the damping element 17, a gap 27 is shown below the damping element 17, a gap 27 is shown below the damping element 17, a gap 27 is shown.
  • Fig. 5 shows a side view of another impeller blade 100 according to the invention with a, with respect to the plane shown in the axial direction and a radial direction r, closed pocket-shaped body 3.
  • the pocket-shaped body 3 is referred to as closed, because the axial webs 29 and the radial webs 31 a have closed circumferential contour. In particular, this contour is closed with respect to the cavity 1.
  • Fig. 6 shows a side view of another impeller blade 100 according to the invention with a, in relation to the plane shown in the axial direction a and in the radial direction r, open pocket-shaped body.
  • the bag-shaped body 3 is referred to as open, because the radially inner (in Fig. 6 the lower web) axial web 29 only about half of the total length in the axial direction a of the pocket-shaped body 3 has.
  • the bag-shaped body 3 is open with respect to the cavity l.
  • the pocket-shaped body 3 has an opening to the cavity 1.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (7)

  1. Pale de roue mobile (100) d'une turbomachine axiale, comprenant une emplanture de pale (5), un profil d'aile (7) et une plateforme de pale (9), dans laquelle la pale de roue mobile (100) peut être fixée au moyen de l'emplanture de pale (5) sur un plateau de rotor et est agencée avec d'autres pales de roue mobile (100) sur le plateau de rotor dans la direction circonférentielle, dans laquelle la pale de roue mobile (100) présente un corps en forme de poche (3) qui est agencé en dessous du profil d'aile (7) et au-dessus de l'emplanture de pale (5) ainsi que dans la zone de la plateforme de pale (9), dans laquelle le corps en forme de poche (3) est agencé dans ou sur un espace creux (1) de la plateforme de pale (9), dans laquelle l'espace creux (1) forme avec un autre espace creux (1) d'une pale de roue mobile voisine (100) sur le plateau de rotor un espace creux élargi (21), dans laquelle le corps de forme de poche (3) forme avec un autre corps en forme de poche (3) de la pale de roue mobile (100) voisine sur le plateau de rotor un corps en forme de poche élargi (23) pour recevoir un élément d'amortissement (17), dans laquelle le corps en forme de poche (3) est délimité au moins par deux âmes axiales (29) et deux âmes radiales (31), dans laquelle l'élément d'amortissement (17) est agencé à l'intérieur de ces âmes,
    dans laquelle la pale de roue mobile (100) comprend en outre l'élément d'amortissement (17) qui est aménagé pour être reçu dans le corps en forme de poche élargi (23) de la pale de roue mobile (100), dans laquelle l'élément d'amortissement (17) présente une longueur LD et une largeur WD,
    dans laquelle l'élément d'amortissement (17) est agencé dans sa direction longitudinale dans le corps en forme de poche élargi (23) parallèlement à l'axe de rotation de la turbomachine, et
    dans laquelle l'élément d'amortissement (17) est conçu en forme trapézoïdale ou rectangulaire en coupe transversale perpendiculairement à l'orientation longitudinale de l'élément d'amortissement (17),
    caractérisée en ce que
    le rapport de la longueur LD à la largeur WD est inférieur à 1.
  2. Pale de roue mobile (100) selon la revendication 1, dans laquelle l'espace creux élargi (21) présente un intervalle d'étanchéité (25) ou est relié à un intervalle d'étanchéité (25).
  3. Pale de roue mobile (100) selon la revendication 1 ou 2, dans laquelle le corps en forme de poche élargi (23) présente un intervalle d'étanchéité (25) ou est relié à un intervalle d'étanchéité (25).
  4. Pale de roue mobile (100) selon l'une quelconque des revendications 1 à 3, dans laquelle le corps en forme de poche (3) présente une ouverture débouchant sur l'espace creux (1).
  5. Pale de roue mobile (100) selon la revendication 4, dans laquelle l'ouverture est agencée parallèlement à l'axe de rotation de la turbomachine.
  6. Pale de roue mobile (100) selon l'une quelconque des revendications 1 à 5, dans laquelle l'élément d'amortissement (17) est conçu en coupe transversale perpendiculairement à l'orientation longitudinale de l'élément d'amortissement (17) de manière symétrique à l'axe central vertical de l'élément d'amortissement (17).
  7. Pale de roue mobile (100) selon l'une quelconque des revendications 1 à 6, dans laquelle la longueur LD de l'élément d'amortissement (17) est plus petite d'au moins 1 mm que la longueur LT du corps en forme de poche élargi (23) de la pale de roue mobile (100) et/ou la largeur WL de l'élément d'amortissement (17) est plus petite d'au moins 1 mm que la largeur Wr du corps en forme de poche (3) de la pale de roue mobile (100).
EP13184785.7A 2013-09-17 2013-09-17 Pale de rotor d'une turbomachine axiale et élément d'amortissement Not-in-force EP2848770B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
ES13184785.7T ES2622424T3 (es) 2013-09-17 2013-09-17 Álabe de rodete de una máquina de circulación axial y elemento de amortiguación
EP13184785.7A EP2848770B1 (fr) 2013-09-17 2013-09-17 Pale de rotor d'une turbomachine axiale et élément d'amortissement

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13184785.7A EP2848770B1 (fr) 2013-09-17 2013-09-17 Pale de rotor d'une turbomachine axiale et élément d'amortissement

Publications (2)

Publication Number Publication Date
EP2848770A1 EP2848770A1 (fr) 2015-03-18
EP2848770B1 true EP2848770B1 (fr) 2017-03-29

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP13184785.7A Not-in-force EP2848770B1 (fr) 2013-09-17 2013-09-17 Pale de rotor d'une turbomachine axiale et élément d'amortissement

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EP (1) EP2848770B1 (fr)
ES (1) ES2622424T3 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102018221533A1 (de) * 2018-12-12 2020-06-18 MTU Aero Engines AG Turbomaschinen Schaufelanordnung
CN113605993A (zh) * 2021-07-26 2021-11-05 中国船舶重工集团公司第七0三研究所 一种带有阻尼减振块的高压涡轮动叶组

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5302085A (en) * 1992-02-03 1994-04-12 General Electric Company Turbine blade damper

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3887298A (en) * 1974-05-30 1975-06-03 United Aircraft Corp Apparatus for sealing turbine blade damper cavities
CH660207A5 (en) * 1983-06-29 1987-03-31 Bbc Brown Boveri & Cie Device for the damping of blade vibrations in axial flow turbo engines
EP0437977A1 (fr) * 1990-01-18 1991-07-24 United Technologies Corporation Configuration de jante de disque de turbine
US8137072B2 (en) * 2008-10-31 2012-03-20 Solar Turbines Inc. Turbine blade including a seal pocket
EP2280151A1 (fr) * 2009-06-23 2011-02-02 Alstom Technology Ltd Procédé d'exploitation d'une turbine à gaz et rotor de turbine à gaz

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5302085A (en) * 1992-02-03 1994-04-12 General Electric Company Turbine blade damper

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Publication number Publication date
EP2848770A1 (fr) 2015-03-18
ES2622424T3 (es) 2017-07-06

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