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EP2784268A1 - Etanchéité extérieur d'une aube de turbine comprenant un revêtement ceramique sur le stator et le rotor respectivement - Google Patents

Etanchéité extérieur d'une aube de turbine comprenant un revêtement ceramique sur le stator et le rotor respectivement Download PDF

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Publication number
EP2784268A1
EP2784268A1 EP13161673.2A EP13161673A EP2784268A1 EP 2784268 A1 EP2784268 A1 EP 2784268A1 EP 13161673 A EP13161673 A EP 13161673A EP 2784268 A1 EP2784268 A1 EP 2784268A1
Authority
EP
European Patent Office
Prior art keywords
stator
rotor
radial gap
coatings
coating
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Withdrawn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
EP13161673.2A
Other languages
German (de)
English (en)
Inventor
Sven Hiller
Erwin Bayer
Thomas Hess
Peter Geiger
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 EP13161673.2A priority Critical patent/EP2784268A1/fr
Priority to US14/228,471 priority patent/US9605554B2/en
Publication of EP2784268A1 publication Critical patent/EP2784268A1/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Withdrawn legal-status Critical Current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
    • 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
    • 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
    • F01D5/005—Repairing methods or devices
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/284—Selection of ceramic materials
    • 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
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating

Definitions

  • the invention relates to a turbomachine according to the preamble of patent claim 1 and a turbomachine according to the preamble of patent claim 7.
  • radial gaps between rotating and static machine parts must be sealed in order to avoid secondary flow losses. This applies, for example, for the sealing of the radial gap between a vane tip and an opposite disc wing or between a blade tip and an opposite stator section.
  • labyrinth seals are conventionally used.
  • the machine parts forming the labyrinth seals are subject to high wear and high heating during rubbing. Grinding and heating can lead to cracks, which can have serious consequences especially for the rotating parts. Therefore, usually the rotating part is provided with a so-called armor.
  • the armor is in particular a hard coat, which is applied by a thermal spraying process.
  • the static part remains uncoated and thus soft against the rotating component. As a result, the static component is abraded and worn accordingly when rubbing.
  • the armor is usually rough, which leads to a corresponding warming when rubbing. In addition, it has been shown that the armor tends to flaking.
  • the object of the invention is to provide a turbomachine, which allow a long-lasting seal or reduction of a radial gap between a rotor and a stator of the turbomachine.
  • a turbomachine according to the invention has a rotor and a stator.
  • a seal for reducing the radial gap is arranged, which according to the invention has two opposing coatings, of which the one coating is applied to a radial gap radially outwardly limiting stator and the other coating on a radial gap radially inside limiting rotor section is applied, wherein the coatings are composed of a ceramic powder whose particle size is smaller than 1.0 microns.
  • the so-called nano-ceramic coatings according to the invention have a low risk of spalling, which they can be connected very well to the main body and thus to the rotor section and the stator section.
  • the ceramic powder is disposed on the rotor portion and the stator portion via an organometallic compound, respectively, and then subjected to pressure and temperature treatment.
  • the coatings can be made by sintering at only 800 ° C.
  • the nano-ceramic coatings are very thin, which further reduces the risk of chipping.
  • a total layer thickness is at most 0.1 mm.
  • the particle size is preferably at most 100 nm.
  • the nano-ceramic coatings have a very smooth surface, resulting in low friction coefficients when rubbing, whereby only a slight heating of the coatings takes place.
  • a particular surface quality of the nano-ceramic coatings can be additionally improved by smoothing grinding.
  • the coatings can have a different hardness.
  • the rotor-side coating is harder than the stator-side coating formed. This can prevent a catastrophic failure of the rotor section.
  • the coatings may have different thicknesses to create a certain elasticity in the sealing area during hard rubbing.
  • the rotor-side coating is made thicker than the stator-side coating, which also catastrophic failure of the rotating component can be prevented.
  • the coatings consist of a plurality of individual layers.
  • the individual layers each have a single-layer thickness, which in total does not exceed the total layer thickness of 0.1 mm. Through the single layers, the total layer thickness can be easily varied. In addition, a high stability of the coatings is achieved even with a high total layer thickness.
  • the individual layers are preferably applied in powder form in succession and subjected together to the pressure and temperature treatment. The individual layers are no longer recognizable after the pressure and temperature treatment, so that in the case of exclusive use of ceramic powder after the pressure and temperature treatment is a one-piece all-ceramic.
  • An alternative turbomachine has a rotor and a stator.
  • a seal for reducing the radial gap is arranged, which according to the invention has two opposing coatings, of which the one coating is applied to a radial gap radially outwardly limiting stator and the other coating on a radial gap radially inner rotor portion is applied, wherein the coatings are constructed of powder-based individual layers whose outer layer has a higher ceramic content than a rotor or statorabna near base layer, wherein the particle size of the powder material is less than 1.0 microns.
  • the coating Due to the graduated formation of the coatings, large material jumps between the rotor and stator section and the coating can be prevented.
  • the coating can thus be adapted in layers in terms of their thermal expansion or their modulus of elasticity to the rotor and stator.
  • the outer single layer has a ceramic content of 100% and thus consists exclusively of a nano-ceramic powder.
  • the base layer has a very high metal content.
  • a high sealing effect can be achieved if the radial gap seal takes place in the form of a labyrinth seal in both embodiments, wherein at least the rotor section is formed with a plurality of elevations pointing in the direction of the stator section.
  • Other advantageous embodiments of the invention are the subject of further subclaims.
  • FIG. 1 a seal 1 for reducing a radial gap s between a rotor section 2 and a stator section 4 of a turbomachine 6 is shown.
  • the turbomachine 6 is preferably a gas turbine and in particular an aircraft engine. However, the turbomachine 6 may also be designed as a steam turbine and the like.
  • the rotor section 2 forms part of an in FIG. 2
  • the rotor 8 rotates about a machine axis M extending in the axial direction of the turbomachine 6 and essentially has a multiplicity of rotor disks 10 arranged behind one another in the direction of flow of a hot gas, each of which carries a row of blades with a multiplicity of rotor blades 12 and are arranged on a common rotor hub, not shown.
  • the stator section 4 forms part of an in FIG. 2
  • the stator 14 essentially has a housing 16 and a multiplicity of guide blade rows arranged alternately with the rotor blade rows, which consist of individual guide blades 18 inserted in receptacles of the housing 16.
  • the stator 14 between the grilling vanes 18 and thus opposite to the blades 12 each have an outer sealing ring 20 inserted into the housing 16.
  • the outer sealing ring 20 may be a one-piece and circumferentially closed outer sealing ring or one of a plurality of sealing ring segments.
  • the seal 1 is for example in the in FIG. 2 sketched areas 22, 24, 26 each provided as a so-called intermediate stage seal.
  • the rotor section 2 is formed by the outer shrouds 28 of the blades of a front blade row and the opposite stator section 4 by the opposing outer sealing ring 20. This construction also applies to the rear region 26.
  • the rotor section 2 In the middle region 24, the rotor section 2, a rotor blade 10 extending between the rotor disks 10 and the stator section 4 an inner sealing ring 32, which is arranged on the guide vanes 18 interconnecting inner ring.
  • the seal 1 has a plurality of consecutively arranged elevations 34, 36, 38, a rotor-side coating 40 and a stator-side coating 42.
  • the elevations 34, 36, 38 are arranged on the rotor side.
  • the elevations 34, 36, 38 are then, for example, sealing tips of the outer cover strips 28.
  • the elevations 34, 36, 38 can in principle also be arranged on the stator side.
  • the respective opposing rotor section 2 or stator section 4 is preferably flat, but may also be provided with corresponding projections, which dip radially between each two elevations 34, 36, 38.
  • elevations 34, 36, 38 extend in the circumferential direction and in the radial direction of the turbomachine 8 in the direction of the stator section 4.
  • the seal 1 is designed as a labyrinth seal.
  • the elevations 34, 36, 38 have such a radial extension that they are minimally objected to in the heated state of the turbomachine 6 of the stator section 4 or easy to grind along the stator side coating 42, so that the radial gap s is closed.
  • three elevations 34, 36, 38 are shown, however, more or fewer elevations 34, 36, 38 may be provided.
  • the elevations 34, 36, 38 and laterally of the elevations 34, 36, 38 extending planar surfaces 44, 46, 48, 50 of the rotor section 2 are each provided with the rotor-side coating 40.
  • the coatings 40, 42 are so-called nano-ceramic coatings, each having a total layer thickness of preferably not more than 0.1 mm. They are each made up of a ceramic powder whose particle size is smaller than 1.0 microns. Preferably, their particle size is 100 nm.
  • the coatings 40, 42 are connected to the rotor section 4 or the stator section 6 by means of a pressure and temperature treatment, in particular a sintering process. As a result, a compound with high adhesion forces forms between the rotor section 4 or the stator section 6 and the coatings 40, 42.
  • the ceramic powder for application to the sections 4, 6 is bound in an organometallic compound.
  • the coatings 40, 42 each consist of a plurality of individual layers, which together do not exceed the total layer thickness.
  • the individual layers exist in the in FIG. 2 embodiment shown exclusively from the ceramic powder, so that ndi coatings 40, 42 are fully ceramics after their production.
  • the individual layers may have different ceramic components, and so an outer single layer may have a higher proportion of ceramic than a base layer close to the rotor or stator.
  • the outer single layer has a ceramic content of 100%, since such a low coefficient of friction is achieved.
  • the base layer has a very high metal content.
  • a particle size of the ceramic powder and the metal powder is always smaller than 1.0 ⁇ m. Consequently, in this exemplary embodiment, the proportion of ceramic, starting from the rotor section 4 or stator section 6, is increased in the direction of the outer individual layer and the metal component is lowered correspondingly. This makes it possible to prevent large material jumps between the rotor section 4 or the stator section 6 and the coatings 40, 42.
  • individual ceramic layers and metal layers may be arranged alternately, wherein in each case a ceramic layer forms the outer layer.
  • the coatings 40, 42 are of different hardness.
  • the rotor-side coating 40 is harder than the stator side Coating 42.
  • the elevations 34,36, 38 run in the case of a violent brushing in the stator-side coating 42 and do not break off.
  • the coatings 40, 42 are made different thickness.
  • the rotor-side coating 40 is thicker than the stator-side coating 42.
  • the different coating hardnesses and the different coating thicknesses can be realized both as individual features and in combination with one another.
  • a turbomachine with at least one radial gap seal which has at least two opposing ceramic coatings, each composed of a ceramic powder whose particle size is smaller than 1.0 microns, and a turbomachine with at least one radial gap seal, wherein the coatings are constructed of powder-based individual layers whose outer layer has a higher ceramic content than a rotor or statorabitessnahe base layer, wherein the particle size of the powder material is less than 1.0 microns.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP13161673.2A 2013-03-28 2013-03-28 Etanchéité extérieur d'une aube de turbine comprenant un revêtement ceramique sur le stator et le rotor respectivement Withdrawn EP2784268A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP13161673.2A EP2784268A1 (fr) 2013-03-28 2013-03-28 Etanchéité extérieur d'une aube de turbine comprenant un revêtement ceramique sur le stator et le rotor respectivement
US14/228,471 US9605554B2 (en) 2013-03-28 2014-03-28 Turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13161673.2A EP2784268A1 (fr) 2013-03-28 2013-03-28 Etanchéité extérieur d'une aube de turbine comprenant un revêtement ceramique sur le stator et le rotor respectivement

Publications (1)

Publication Number Publication Date
EP2784268A1 true EP2784268A1 (fr) 2014-10-01

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EP13161673.2A Withdrawn EP2784268A1 (fr) 2013-03-28 2013-03-28 Etanchéité extérieur d'une aube de turbine comprenant un revêtement ceramique sur le stator et le rotor respectivement

Country Status (2)

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US (1) US9605554B2 (fr)
EP (1) EP2784268A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015224379A1 (de) * 2015-12-04 2017-06-08 MTU Aero Engines AG Stabilisierter Dichtring für eine Strömungsmaschine
FR3065482B1 (fr) * 2017-04-20 2019-07-05 Safran Aircraft Engines Element d'anneau d'etancheite pour turbine comportant une cavite inclinee dans un materiau abradable

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0292250A1 (fr) * 1987-05-19 1988-11-23 Union Carbide Corporation Joint d'étanchéité de gaz tournant et aubes pour turbine et compresseur
DE10225532C1 (de) * 2002-06-10 2003-12-04 Mtu Aero Engines Gmbh Schichtsystem für die Rotor-/Statordichtung einer Strömungsmaschine
EP1739204A2 (fr) * 2005-06-29 2007-01-03 The General Electric Company Revêtement haute température lisse usure réparable
EP2009141A2 (fr) * 2007-06-19 2008-12-31 United Technologies Corporation Système de barrière thermique et procédé de liaison
DE102009012945A1 (de) * 2009-03-12 2010-09-16 Mtu Aero Engines Gmbh Verfahren zur Herstellung einer abrasiven Beschichtung und Bauteil für eine Turbomaschine
DE102011081323B3 (de) * 2011-08-22 2012-06-21 Siemens Aktiengesellschaft Laufschaufel für eine Strömungsmaschine und Strömungsmaschine mit der Laufschaufel
EP2540973A1 (fr) * 2011-06-30 2013-01-02 Siemens Aktiengesellschaft Système d'étanchéité pour turbine à gaz

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4299865A (en) * 1979-09-06 1981-11-10 General Motors Corporation Abradable ceramic seal and method of making same
US6682821B2 (en) * 2001-12-28 2004-01-27 Kyocera Corporation Corrosion-resistant ceramics
EP1806432A1 (fr) * 2006-01-09 2007-07-11 Siemens Aktiengesellschaft Système de revêtement avec 2 phases de pyrochlore
DE102007019476A1 (de) * 2007-04-25 2008-11-06 Mtu Aero Engines Gmbh Verfahren zum Herstellen eines Anstreifbelags
DE102010010595A1 (de) * 2010-03-08 2011-09-08 Lufthansa Technik Ag Verfahren zur Reparatur von Dichtsegmenten in der Rotor-/Statordichtung einer Gasturbine

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0292250A1 (fr) * 1987-05-19 1988-11-23 Union Carbide Corporation Joint d'étanchéité de gaz tournant et aubes pour turbine et compresseur
DE10225532C1 (de) * 2002-06-10 2003-12-04 Mtu Aero Engines Gmbh Schichtsystem für die Rotor-/Statordichtung einer Strömungsmaschine
EP1739204A2 (fr) * 2005-06-29 2007-01-03 The General Electric Company Revêtement haute température lisse usure réparable
EP2009141A2 (fr) * 2007-06-19 2008-12-31 United Technologies Corporation Système de barrière thermique et procédé de liaison
DE102009012945A1 (de) * 2009-03-12 2010-09-16 Mtu Aero Engines Gmbh Verfahren zur Herstellung einer abrasiven Beschichtung und Bauteil für eine Turbomaschine
EP2540973A1 (fr) * 2011-06-30 2013-01-02 Siemens Aktiengesellschaft Système d'étanchéité pour turbine à gaz
DE102011081323B3 (de) * 2011-08-22 2012-06-21 Siemens Aktiengesellschaft Laufschaufel für eine Strömungsmaschine und Strömungsmaschine mit der Laufschaufel

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Publication number Publication date
US9605554B2 (en) 2017-03-28
US20140294570A1 (en) 2014-10-02

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