EP3546703A1 - Aube mobile de turbine pour une turbine à gaz - Google Patents

Aube mobile de turbine pour une turbine à gaz Download PDF

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Publication number
EP3546703A1
EP3546703A1 EP18165014.4A EP18165014A EP3546703A1 EP 3546703 A1 EP3546703 A1 EP 3546703A1 EP 18165014 A EP18165014 A EP 18165014A EP 3546703 A1 EP3546703 A1 EP 3546703A1
Authority
EP
European Patent Office
Prior art keywords
blade
airfoil
turbine
tip
cutting layer
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.)
Withdrawn
Application number
EP18165014.4A
Other languages
German (de)
English (en)
Inventor
Johannes Döhnert
Torsten JOKISCH
Francis Ladru
Thorsten Schulz
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP18165014.4A priority Critical patent/EP3546703A1/fr
Priority to PCT/EP2019/057718 priority patent/WO2019185713A1/fr
Publication of EP3546703A1 publication Critical patent/EP3546703A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • 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
    • 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
    • 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
    • F05D2240/307—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 tip of a rotor blade

Definitions

  • the invention relates to a turbine blade for a gas turbine according to the preamble of claim 1.
  • a corresponding to the preamble of claim 1 turbine blade is for example from the document EP 0 166 676 A2 known.
  • the previously known turbine blade has a metallic airfoil on whose outwardly pointing tip a layer of hard material particles has been applied. This is used when using the turbine blade in a gas turbine for the targeted removal of material which has been applied to the housing opposite the blade tip housing wall.
  • these housing walls defining the flow path are formed in stationary gas turbines by so-called ring segments on which the abradable material is applied not only as temperature protection but also functionally for radial gap adjustment and optimization.
  • the background is a thermal distribution occurring during operation of the gas turbine, which leads to different thermally induced strains in the housing.
  • EP 0 166 676 A2 to use on the outwardly facing surface of the blade tip a particularly hard material, thus abrading the softer, applied to the ring segments material during operation of the gas turbine to set minimum gap and also to improve the warm start behavior there.
  • blades used to dig into an abradable layer may tend to locally lose the thermal barrier coating at its outer end. This reduces the protection of the blade against hot gas influences, so that at the locations of missing heat-insulating layers, the metallic material of the turbine blade can age prematurely. This can shorten the life of the turbine blade, which in the worst case can result in premature replacement of the damaged component.
  • the object of the invention is therefore to provide a turbine blade for a gas turbine, which, configured for burying in a wear-resistant layer provided on the housing side, has a comparatively long service life.
  • a turbine blade for a gas turbine with a metallic blade comprising one of a hot gas streamable leading edge from which a suction side sidewall and a pressure side sidewall extend to a trailing edge of the airfoil, wherein the airfoil extends in a transversely extending radial direction from a root end to a tip end forming a blade tip, and at the radially outward a first cutting layer is applied, in which at least one of the two side walls, in particular on the suction side wall of the airfoil and / or in the region of the leading edge of the airfoil on the tip side, a further cutting layer is applied.
  • the invention is based on the finding that the first cutting layer has a thickness which can be detected in the radial direction, which is comparatively low.
  • the turbine blade in question can dig into the material of the housing wall to be abraded so deeply in the radial direction that contact between the heat-insulating layer applied to the side walls or on the front edge and the material to be abraded the housing wall occurs.
  • two comparatively soft materials meet, so that it is not absolutely necessary to rub off the material of the housing wall that is to be abraded. Rather, the applied also on the tip-side ends of the airfoil thermal insulation layer due to the unwanted contact locally flake.
  • the first cutting layer applied to the radially outwardly facing surface of the blade tip can significantly heat when buried in the opposite abradable layer applied to the housing wall.
  • the heating leads to thermal strains in the cutting layer and also in the adjacent areas.
  • the heat-insulating layer attached on the side walls and on the front edge of the blade can be heated to an impermissibly high level, so that the risk of spalling of the heat-insulating layer on the tip side is increased.
  • the invention proposes that not only on the radially outwardly facing surface of the blade tip is a first cutting layer applied, but that at least on one of the two side walls, in particular on the suction side, because leading side wall of the airfoil and / or in the region of the leading edge of the blade on the tip side, a further cutting layer is applied.
  • the first cutting layer and the further cutting layer merge into each other and encompass the edge between the side wall and the outwardly facing surface.
  • the terms "first” and "further” cutting layer merely serve to identify two possibly contiguous regions of the cutting layer, which can be applied in one production step.
  • the cutting layer usually enriched with hard material particles, in particular cubic or hexagonal boron nitride, thus have a sufficient strength and hardness, which makes it possible that only the material applied to the housing wall material is removed there.
  • the applied on the side walls of the airfoil thermal barrier coating is thus protected from destructive contact with the coated housing wall.
  • a mixture of cubic boron nitride (cBN) and MAX phase powder is applied as a cutting layer, so that the abrasion resistance of the turbine blade improves significantly.
  • the cubic boron nitride has a very high hardness and is characterized by an outstanding wear resistance.
  • the cubic boron nitride embedding material should also have good wear resistance combined with good oxidation resistance and high thermal resistance. This combination of properties is optimally covered by the MAX phases.
  • MAX phases are materials whose properties lie between those of ceramics and metals.
  • M stands for an element of the transition metals (eg Ti, Cr, Nb, Ta, etc.)
  • A stands for Element from the A group (eg Al, Si, etc.)
  • X is carbon or nitrogen (C or N).
  • Typical representatives of the MAX phases are Ti2AlC, Cr2AlC and Nb2AlC.
  • the mixture of cubic boron nitride and MAX phase could be applied via laser powder build-up welding.
  • preforms could be sintered, which are then connected to the turbine blade via a soldering process.
  • the sustained protection of the airfoil due to the continued existence of the ceramic thermal barrier coating on the sidewalls of the airfoil can improve turbine blade life compared to prior art turbine blades.
  • the blade tip comprises at least one, preferably at least two squealer edges each having a first, the suction side facing side surface on which side surface, the further cutting layer is applied.
  • the invention is not only applicable only to flat and thus unprofiled blade tips, but also in those blade tips in which the turbine blade known to have used squealer edges. Since the suction-side side wall of the pressure-side side wall protrudes in the case of rotating turbine rotor blades, it is particularly advantageous if surfaces facing the suction side have the further cutting layer on the tip side.
  • the respective side wall of the airfoil or the respective side surface of the squeal edge has a recessed step towards the blade tip.
  • the depth of the step corresponds approximately to the thickness of the applied further cutting layer.
  • At least one further layer in particular an adhesion promoter layer and / or a ceramic thermal insulation layer, are provided on the tip side between the further cutting layer and the metallic blade.
  • at least one adhesive layer which also represents a corrosion protection layer in the form of a MCrAlY at the same time, this area of the turbine blade protects against the harmful effects of the hot gas.
  • FIG. 1 is shown in a perspective view of a turbine blade 10.
  • a turbine blade 10 Along an axis coincident with the radial direction R of a gas turbine in which the turbine blade 10 is installed, it comprises a blade root 12, a platform 14, and an airfoil 16 seen from the inside out.
  • turbine blades 10 are internally cooled. Thus, they are usually manufactured in a casting process, so that they are formed entirely of a metallic base material. However, for the invention, it is sufficient if the airfoil 16 is metallic. This has a front edge 18, which can be inflated by a hot gas S, and a trailing edge 20.
  • a suction-side side wall 22 and a pressure-side side wall 24 extend, which extend in the transverse direction and thus in the radial direction R from a foot-side end 26 to a tip-side end 28.
  • the latter also forms the blade tip 30, which does not necessarily have to be flat.
  • the blade tip 30 is provided with a border, which is also referred to as the squealer edge 32.
  • On its radially outwardly facing surface is an in FIG. 1 Not shown cutting layer applied, but in the FIGS. 2 and 3 can be seen in detail.
  • FIGS. 2 and 3 each show in a longitudinal section along the lines II-II and III-III different embodiments of the invention, in which the cutting layer 36 is disposed not only on the radially outwardly facing surface of the blade tip 30, but also on the suction-side side wall 24 of the metallic airfoil This applies to both the suction side and the pressure side arranged squealer 32.
  • the irrelevant for understanding the invention elements of the turbine blade are - as always in schematic representations - not shown.
  • the blade tip 30 is equipped, for example, both on the suction side and on the pressure side, each with a squeal edge 32, which are not only covered by the first cutting layer 36 at their radially outwardly facing surfaces.
  • the cutting layer according to the invention also extends over a corner 38 on those side surfaces 34 of the squealer edges 32, which point to the suction side 24 or are part of the front edge 18. This part of the cutting layer 36 is referred to as a further cutting layer.
  • the section line III-III is arranged such that it extends through the front edge 18 of the blade and the pressure-side side wall 24.
  • the cutting layer 36 according to FIG. 3 on the blade tip side also in the region of the front edge 18 on the surface to be stirred by the hot gas and even extends slightly up to the pressure side side wall 24.
  • This embodiment is particularly useful when the rotor of the gas turbine equipped with such a turbine blade 10 is also displaceable in the axial direction A.
  • the airfoil 16 is coated on both the suction side and on the pressure side or on the front edge over a large area first of all by a bonding agent layer 40, which in turn is covered by a ceramic thermal barrier coating 42.
  • a bonding agent layer 40 which in turn is covered by a ceramic thermal barrier coating 42.
  • two layers 40, 42 abut directly on the further cutting layer.
  • the second embodiment according to FIG. 3 a step 44 on the tip side, which recesses relative to the front edge 18 or, if appropriate, based on the suction side wall 22.
  • the primer layer 40 may - as in FIG. 3 shown as an example - be arranged between the cutting layer 36 on the one hand and the squeal edge 32 and the blade 16 on the other. In this case, only the ceramic thermal barrier coating 42 reaches to the further cutting layer.
  • the invention relates to a turbine blade 10 for a gas turbine having a metallic airfoil 16 comprising a hot gas S vorstreibbar leading edge 18, from which a suction-side side wall 22 and a pressure-side side wall 24 extend to a trailing edge 20 of the airfoil 16, wherein the airfoil 16 extends in a transversely extending radial direction R from a base end 26 to a blade tip 30 forming tip-side end 28 and wherein on the radially outwardly facing surface of the blade tip 30, a first cutting layer 36 is applied.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP18165014.4A 2018-03-29 2018-03-29 Aube mobile de turbine pour une turbine à gaz Withdrawn EP3546703A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP18165014.4A EP3546703A1 (fr) 2018-03-29 2018-03-29 Aube mobile de turbine pour une turbine à gaz
PCT/EP2019/057718 WO2019185713A1 (fr) 2018-03-29 2019-03-27 Pale de turbine pour turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP18165014.4A EP3546703A1 (fr) 2018-03-29 2018-03-29 Aube mobile de turbine pour une turbine à gaz

Publications (1)

Publication Number Publication Date
EP3546703A1 true EP3546703A1 (fr) 2019-10-02

Family

ID=61868236

Family Applications (1)

Application Number Title Priority Date Filing Date
EP18165014.4A Withdrawn EP3546703A1 (fr) 2018-03-29 2018-03-29 Aube mobile de turbine pour une turbine à gaz

Country Status (2)

Country Link
EP (1) EP3546703A1 (fr)
WO (1) WO2019185713A1 (fr)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2075129A (en) * 1980-05-01 1981-11-11 Gen Electric Tip cap for a rotor blade and method of replacement
EP0166676A2 (fr) 1984-06-25 1986-01-02 United Technologies Corporation Article à surface abrasive pour utilisation à haute température
EP1820938A1 (fr) * 2006-02-20 2007-08-22 ABB Turbo Systems AG Eléments de nettoyage sur les extrémités des aubes d' une turbine
EP2317078A2 (fr) * 2009-11-02 2011-05-04 Alstom Technology Ltd Aube de turbine abrasive monocristalline
EP2316988A1 (fr) * 2009-11-02 2011-05-04 Alstom Technology Ltd Aube de turbine résistant à l'usure et à l'oxydation
GB2529854A (en) * 2014-09-04 2016-03-09 Rolls Royce Plc Rotary blade tip

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2075129A (en) * 1980-05-01 1981-11-11 Gen Electric Tip cap for a rotor blade and method of replacement
EP0166676A2 (fr) 1984-06-25 1986-01-02 United Technologies Corporation Article à surface abrasive pour utilisation à haute température
EP1820938A1 (fr) * 2006-02-20 2007-08-22 ABB Turbo Systems AG Eléments de nettoyage sur les extrémités des aubes d' une turbine
EP2317078A2 (fr) * 2009-11-02 2011-05-04 Alstom Technology Ltd Aube de turbine abrasive monocristalline
EP2316988A1 (fr) * 2009-11-02 2011-05-04 Alstom Technology Ltd Aube de turbine résistant à l'usure et à l'oxydation
GB2529854A (en) * 2014-09-04 2016-03-09 Rolls Royce Plc Rotary blade tip

Also Published As

Publication number Publication date
WO2019185713A1 (fr) 2019-10-03

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