EP2604797B1 - Aube de rotor dotée d'un agencement de nervures avec revêtement abrasif - Google Patents

Aube de rotor dotée d'un agencement de nervures avec revêtement abrasif Download PDF

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Publication number
EP2604797B1
EP2604797B1 EP11193177.0A EP11193177A EP2604797B1 EP 2604797 B1 EP2604797 B1 EP 2604797B1 EP 11193177 A EP11193177 A EP 11193177A EP 2604797 B1 EP2604797 B1 EP 2604797B1
Authority
EP
European Patent Office
Prior art keywords
ribs
rotor blade
rib
coating
radial
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
EP11193177.0A
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German (de)
English (en)
Other versions
EP2604797A1 (fr
Inventor
Alexander Böck
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
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 ES11193177T priority Critical patent/ES2773743T3/es
Priority to EP11193177.0A priority patent/EP2604797B1/fr
Priority to US13/709,322 priority patent/US9797264B2/en
Publication of EP2604797A1 publication Critical patent/EP2604797A1/fr
Application granted granted Critical
Publication of EP2604797B1 publication Critical patent/EP2604797B1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C24/00—Coating starting from inorganic powder
    • C23C24/02—Coating starting from inorganic powder by application of pressure only
    • C23C24/04—Impact or kinetic deposition of particles
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/01—Selective coating, e.g. pattern coating, without pre-treatment of the material to be coated
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • 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
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/311—Layer deposition by torch or flame spraying
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/312—Layer deposition by plasma spraying
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/126—Baffles or ribs

Definitions

  • the present invention relates to a rotor blade for a compressor or turbine stage of a gas turbine, with a radially outer rib arrangement arranged on a shroud of the rotor blade and having at least two ribs directed radially outwards.
  • the present invention further relates to a turbomachine, in particular a gas turbine, with at least one such blade.
  • the object of the present invention is to provide an improved turbomachine.
  • a rotor blade with the features of claim 1 is proposed, which can be used in a compressor and / or turbine stage of a gas turbine.
  • Claim 6 provides a turbomachine, in particular a gas turbine, with a rotor blade arrangement with such rotor blades under protection. Preferred developments are the subject of the dependent claims.
  • One aspect of the present invention is based on the idea of not providing a surface or not only a harder surface but (also) a larger surface by means of a rib coating.
  • a rotor blade has a radially outer rib arrangement arranged on a shroud of the rotor blade.
  • the rib arrangement has at least two radially outwardly directed ribs.
  • the ribs have at least on the two side surfaces a coating on. These coatings are connected to one another via their radially outer end faces of the respective ribs. The thickness of the coating increases, in relation to a cut transverse to the rib, radially outwards on the two radial side surfaces of the rib.
  • the rotor blade has a rib arrangement with a plurality of ribs arranged one behind the other in the axial direction.
  • the axial direction refers in particular to a coordinate direction that is aligned with an axis of rotation of the rotor blade or turbomachine, in particular a gas turbine, a direction that extends perpendicularly from the axis of rotation as a radial direction and a direction that is perpendicular to the axis of rotation as the circumferential direction and extends perpendicular to the radial direction, in particular in the direction of rotation of the rotor blade or turbomachine, in particular gas turbine.
  • a coating is arranged on at least two or more, in particular adjacent, and preferably on all the ribs of the rib arrangement. This is preferably made of metal, plastic and / or ceramic. In a preferred embodiment, the coating has a greater hardness than the rib itself. A hardness according to Vickers, Rockwell, Brinell or a similar test protocol is referred to in the present case as hardness.
  • coatings of the rib arrangement each have an outer contour in a meridian section, which contour extends outward in the radial direction, ie expanded with increasing radial distance from the axis of rotation, axially or in the axial direction.
  • a meridian section is understood to mean, in particular, a cross section which contains the axial direction and the radial direction.
  • an outer contour can expand monotonically, in particular strictly monotonously, in the radial direction to the outside. In the present case, this is understood in particular to mean that a distance in the axial direction between the two outer flanks of the outer contour always remains at least essentially (monotonically) or even always increases (strictly monotonous) with increasing radial distance from the axis of rotation. Equally, however, outer contours are also included, the outer flanks of which approach each other in limited radial areas.
  • General is therefore an outer contour that extends outward in the radial direction, in particular an outer contour with two mutually opposite outer flanks, the distance of which in the axial direction is smaller at a first, smaller distance from the axis of rotation than at a second, larger distance from the axis of rotation,
  • a gap between mutually facing flanks of adjacent coatings on adjacent ribs of the rib arrangement corresponds at most to an axial width of a radially outer end face of one of the two adjacent ribs.
  • the axial width refers in particular to the distance between a front and rear edge in the axial direction of a radially outer end face of a rib. Due to the preferred limitation of the gap to the front axial width of a rib, the leakage in the space between adjacent ribs can be reduced to a level that is not critical for the efficiency.
  • a gap between mutually facing flanks of adjacent coatings of adjacent ribs of the rib arrangement corresponds to at most 75% and preferably at most 50% of such an axial width.
  • smaller gaps between coatings are preferred, with a gap advantageously having a certain minimum dimension, which in particular can be at least 20% of an axial width of a radially outer end face of one of the two adjacent ribs, in order to prevent the coating from flaking off.
  • the ribs of the rib arrangement are inclined in the circumferential direction by an angle which is not equal to 0 ° and less than 10 ° in amount, in particular less than 5 ° and preferably less than 3 °.
  • two or more, in particular all, of the ribs of the rib arrangement have outer end faces in the radial direction which, at least essentially, lie at the same radial height. Starting from these end faces, the ribs extend inward in the radial direction at different depths, i.e. are of different heights in the radial direction. On the one hand, this enables the formation of small gaps between the ribs and, on the other hand, an adaptation to blades with varying radial heights.
  • outer end faces of two or more, in particular all, of the ribs of the rib arrangement can have a different radial height, in particular — at least essentially — lie on a virtual conical surface.
  • two or more, in particular all, ribs of the rib arrangement can have different heights in the radial direction.
  • the rib arrangement is arranged on a cover band of the moving blade.
  • a shroud is understood to mean, in particular, a flange which extends in the axial and circumferential directions and, in a preferred development, bears in a form-fitting manner on shrouds in the circumferential direction of adjacent blades.
  • the cover band can be inclined in the axial direction in order to support the ribs of different heights explained above.
  • the coating can be carried out by means of a method for coating one or, preferably, in particular in time in parallel or in succession, a plurality of ribs of a radially outer rib arrangement of a rotor blade, which is particularly suitable for coating a rotor blade according to the aspect explained above.
  • a coating material can be sprayed onto the fin arrangement from at least two opposite spray directions, in particular plasma sprayed, flame sprayed, in particular high speed flame sprayed, detonation sprayed, cold gas sprayed, arc sprayed, and / or laser sprayed.
  • plasma spraying is understood in particular to mean that, for example in a plasma torch, an electric arc is generated between the anode (s) and cathode (s) by a voltage, and gas or gas mixture is passed through the electric arc and thereby ionized. The dissociation or subsequent ionization generates a highly heated, electrically conductive gas from positive ions and Electrons.
  • Powdery coating material can be injected into this generated plasma jet, which is melted by the high plasma temperature.
  • the plasma stream entrains the powder particles and hurls them onto the rotor blade to be coated.
  • the plasma coating is preferably carried out in a normal atmosphere, inert atmosphere, in vacuum or under water.
  • the spray directions can be inclined in opposite directions, but with the same amount, against the radial direction, preferably by an spray angle which is greater than 20 °, in particular greater than 40 °, and / or less than 70 °, in particular less than 50 °.
  • the coating material can be sprayed on in succession or simultaneously from the two spray directions.
  • One or more coatings can be reworked, simultaneously or in succession, after the coating material has been sprayed on.
  • a radially outer end face of the coatings can, for example, be ground, polished or reworked in some other way.
  • Fig. 3 shows a meridian section of a gas turbine stage according to an embodiment of the present invention with a moving blade 5, on the inclined cover band 1 of which a rib arrangement with five ribs 2 arranged one behind the other in the axial direction is arranged.
  • a honeycomb-like sealing surface 4 is arranged radially opposite the rib arrangement 2.
  • the honeycomb-like sealing surface 4 instead of the honeycomb-like sealing surface 4 'with one or two (dashed) counter rib (s) is provided.
  • This coating 3 is applied by sequential plasma spraying first in a first spray direction S 1 , and then in an opposite or mirror-symmetrical second spray direction S 2 , as in FIG Fig. 2 indicated by arrows, applied.
  • an essentially flat end face of the coatings 3 can be represented.
  • the coating in particular its radially outer end face (top in Fig. 2 ) post-processed, in particular ground, after spraying.
  • the ribs 2 are inclined against the circumferential direction U by an angle ⁇ , which is 2 ° in the exemplary embodiment.
  • ⁇ which is 2 ° in the exemplary embodiment.
  • the circumferential direction U and a radial direction R are indicated in the figures, wherein 2 to 4 one section horizontally to the plane of the drawing Fig. 1 can represent, so an axial direction in all figures runs horizontally from left to right.
  • the spray layer is not shown.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)

Claims (6)

  1. Aube de rotor (5) d'un étage de compresseur ou de turbine d'une turbine à gaz, dotée d'un agencement de nervures radialement extérieures disposé sur une bande de recouvrement (1) de l'aube de rotor (5) et comportant au moins deux nervures (2) orientées radialement vers l'extérieur, les nervures (2) étant disposées en série dans la direction axiale et étant inclinées, dans la direction périphérique (U), d'un angle (α) différent de 0°, lequel angle est inférieur à 10°, les nervures (2) comportant un revêtement (3) sur les deux faces latérales axialement opposées respectives et sur la face frontale radialement extérieure des nervures (2) par lesquelles les faces latérales sont reliées, l'épaisseur du revêtement (3) augmentant dans une section transversale par rapport à la nervure (2) sur les deux faces latérales radiales de la nervure (2) avec un espacement radial croissant par rapport à l'axe de rotation de la turbine à gaz.
  2. Aube de rotor (5) selon la revendication 1, caractérisée en ce qu'un revêtement (3) est disposé respectivement sur au moins deux nervures adjacentes (2), et en ce qu'un espace (s) entre des flancs (3.1) se faisant face des revêtements adjacents (3) correspond au plus à une largeur axiale (b) d'une face frontale radialement extérieure d'une des deux nervures adjacentes (2).
  3. Aube de rotor (5) selon l'une des revendications précédentes, caractérisée en ce qu'au moins deux nervures (2) de l'agencement de nervures comportent une face frontale extérieure dans une direction radiale (R), ladite face frontale se trouvant au moins sensiblement à la même hauteur radiale, et ce que lesdites au moins deux nervures de l'agencement de nervures, à partir de la face frontale, sont de hauteur différente dans la direction radiale vers l'intérieur.
  4. Aube de rotor (5) selon l'une des revendications 1 à 3, caractérisée en ce qu'au moins deux nervures (2) de l'agencement de nervures comportent une face frontale extérieure dans la direction radiale (R), lesdites au moins deux nervures de l'agencement de nervures étant situées à des hauteurs radiales différentes, les nervures (2) étant de hauteur différente dans la direction radiale.
  5. Aube de rotor (5) selon l'une des revendications précédentes, caractérisée en ce qu'un revêtement (3) présente une dureté supérieure à celle de la nervure (2) sur laquelle il est disposé.
  6. Turbomachine dotée d'un agencement d'aubes de rotor comprenant au moins une aube de rotor (5) selon l'une des revendications précédentes.
EP11193177.0A 2011-12-13 2011-12-13 Aube de rotor dotée d'un agencement de nervures avec revêtement abrasif Active EP2604797B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
ES11193177T ES2773743T3 (es) 2011-12-13 2011-12-13 Paleta que tiene un conjunto de nervaduras con un recubrimiento abrasivo
EP11193177.0A EP2604797B1 (fr) 2011-12-13 2011-12-13 Aube de rotor dotée d'un agencement de nervures avec revêtement abrasif
US13/709,322 US9797264B2 (en) 2011-12-13 2012-12-10 Rotating blade having a rib arrangement with a coating

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11193177.0A EP2604797B1 (fr) 2011-12-13 2011-12-13 Aube de rotor dotée d'un agencement de nervures avec revêtement abrasif

Publications (2)

Publication Number Publication Date
EP2604797A1 EP2604797A1 (fr) 2013-06-19
EP2604797B1 true EP2604797B1 (fr) 2020-01-22

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EP11193177.0A Active EP2604797B1 (fr) 2011-12-13 2011-12-13 Aube de rotor dotée d'un agencement de nervures avec revêtement abrasif

Country Status (3)

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US (1) US9797264B2 (fr)
EP (1) EP2604797B1 (fr)
ES (1) ES2773743T3 (fr)

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DE102015213555A1 (de) * 2015-07-20 2017-03-09 MTU Aero Engines AG Dichtrippenpanzerung und Verfahren zur Herstellung derselben
DE102016211337A1 (de) * 2016-06-24 2017-12-28 MTU Aero Engines AG Verdickter radial äußerer Ringbereich eines Dichtfins
DE102016222720A1 (de) * 2016-11-18 2018-05-24 MTU Aero Engines AG Dichtungssystem für eine axiale Strömungsmaschine und axiale Strömungsmaschine
CN110312846B (zh) * 2017-02-23 2022-05-10 三菱动力株式会社 涡轮动叶以及燃气轮机
FR3073595B1 (fr) * 2017-11-15 2020-02-07 Safran Helicopter Engines Joint a labyrinthe comprenant une lechette dotee d'un deflecteur
JP7086595B2 (ja) * 2017-12-28 2022-06-20 三菱重工航空エンジン株式会社 航空機用ガスタービン
PL3865660T3 (pl) 2020-02-11 2024-06-24 Mtu Aero Engines Gmbh Sposób obróbki łopatki i łopatka dla turbomaszyny

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Also Published As

Publication number Publication date
EP2604797A1 (fr) 2013-06-19
US20130149165A1 (en) 2013-06-13
ES2773743T3 (es) 2020-07-14
US9797264B2 (en) 2017-10-24

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