EP1076157A2 - Elément de friction pour une turbomachine - Google Patents

Elément de friction pour une turbomachine Download PDF

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Publication number
EP1076157A2
EP1076157A2 EP00810658A EP00810658A EP1076157A2 EP 1076157 A2 EP1076157 A2 EP 1076157A2 EP 00810658 A EP00810658 A EP 00810658A EP 00810658 A EP00810658 A EP 00810658A EP 1076157 A2 EP1076157 A2 EP 1076157A2
Authority
EP
European Patent Office
Prior art keywords
component
intermetallic felt
intermetallic
felt
thermal turbomachine
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.)
Granted
Application number
EP00810658A
Other languages
German (de)
English (en)
Other versions
EP1076157B1 (fr
EP1076157A3 (fr
Inventor
Alexander Dr. Beeck
Mohamed Dr. Nazmy
Markus Dr. Oehl
Christoph Dr. Töennes
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
Alstom Power Schweiz 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 Alstom Technology AG, Alstom Power Schweiz AG filed Critical Alstom Technology AG
Publication of EP1076157A2 publication Critical patent/EP1076157A2/fr
Publication of EP1076157A3 publication Critical patent/EP1076157A3/fr
Application granted granted Critical
Publication of EP1076157B1 publication Critical patent/EP1076157B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • 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

Definitions

  • the invention is a component of a friction thermal turbomachine according to the preamble of claim 1.
  • the guide and rotor blades of gas turbines are exposed to heavy loads.
  • Impeller of the gas turbine with a very small clearance to the stator so that it comes to brushing.
  • the honeycomb structure consists of a heat-resistant metal alloy.
  • Another type are smooth, coated or uncoated Heat accumulation segments (WSS), which of the rotating blades on the outer radius face radially. The tip of the blade then rubs against it Heat accumulation segments. To prevent the tip of the blade from rubbing itself , it can be coated in order to then to a greater extent To wipe away heat accumulation segments.
  • WSS Heat accumulation segments
  • To prevent the tip of the blade from rubbing itself it can be coated in order to then to a greater extent To wipe away heat accumulation segments.
  • the disadvantage of this embodiment however, that the coating has limited adhesion to the turbine blade. It is also disadvantageous that cooling air bores, with which either Heat accumulation segment and / or the blade can be provided when rubbing get clogged.
  • metal felts at various locations of gas turbine components use, e.g. at the tip of a turbine blade (DE-C2-32 03 869), between a metal core or a ceramic outer skin (DE-C2 32 35 230) or as a jacket of the turbine blade (EP-B1-132 667).
  • a turbine blade DE-C2-32 03 869
  • a metal core or a ceramic outer skin DE-C2 32 35 230
  • EP-B1-132 667 metal felts at various locations of gas turbine components use, e.g. at the tip of a turbine blade (DE-C2-32 03 869), between a metal core or a ceramic outer skin (DE-C2 32 35 230) or as a jacket of the turbine blade (EP-B1-132 667).
  • the metal felt used is insufficient Has oxidation resistance.
  • the metal felts in the the fonts mentioned no longer meet
  • the aim of the invention is to overcome these disadvantages.
  • the invention solves the Task to create a component of a thermal turbomachine which sufficient mechanical strength and a constant cooling effect has areas subject to friction. It should also be sufficient Resistance to oxidation can be guaranteed. In addition, the costs should be reduced become.
  • the goal of a friction component thermal turbomachine according to the preamble of claim 1 thereby achieved that the component with a intermetallic felt. It can be the top one Turbine blade, around which the turbine blade is arranged opposite Heat accumulation segments or the platform of the turbine blade.
  • the intermetallic felt has sufficient strength, resistance to oxidation and deformability.
  • Another advantage arises when the intermetallic felt with a ceramic Material is covered because of the rough surface of the intermetallic felt very good adhesion of the ceramic material is achieved. This gives for example, the tip of the guide or rotor blade provides good protection against thermal and against mechanical effects caused by friction.
  • Another advantage arises from the fact that cooling air bores due to abrasion during do not clog the plant as it is a porous material.
  • FIG. 1 shows a turbine blade 1 with a tip 11, an airfoil 14, a platform 12 and a blade root 13.
  • This can be, for example, a guide vane or a rotor blade of a gas turbine or a compressor.
  • an intermetallic felt 2 is arranged at the tip 11 of this turbine blade 1.
  • the intermetallic felt 2 can be produced on the basis of an Fe aluminide, Ni aluminide or Co aluminide.
  • the elements Ta, Cr, Y, B and Zr are added to achieve sufficient strength, oxidation resistance and deformability.
  • Table 1 shows a possible composition, for example for an Fe alumind and a Ni aluminide. However, materials with the same properties can be used just as well.
  • Composition of intermetallic felts (specified for Fe aluminides or Ni aluminides) Iron aluminides (figures in% by weight) Fe Al Cr Ta or W or Mo Hf Y B C. Zr rest 5-20% 15-25% 0-7% 0-0.5% 0-0.5% 0-0.2% 0-0.1% 0-0.2% Nickel aluminides (figures in% by weight) Ni Al Cr Ta Y Hf Zr B Fe rest 20-30% 0-15% 0-10% 0-0.5% 0-1% 0-0.2% 0-0.2% 0-4%
  • Metallic high-temperature fibers are also described in VDI report 1151, 1995 (Metallic high-temperature fibers by melt extraction - production, properties, applications) .
  • intermetallic felts 2 The advantage of intermetallic felts 2 is the significantly improved resistance to oxidation.
  • FIG. 7 shows the oxidation of various intermetallic felts 2 in comparison with the Hastelloy X commercial nickel-based alloy.
  • Table 2 shows the composition of the test alloys. Composition of test alloys (figures in% by weight) Ref.
  • FIG. 7 shows the weight increase in [mg / cm 2 ] given in Table 2 over a period of 12 hours at a temperature of 1200 ° C.
  • the weight increase is plotted for the oxidation of the materials.
  • the comparative alloy Hastelloy X already after a short time of approx. 100 min. up to approx. 300 min. has a double weight gain.
  • the weight gain of the Hastelloy X continues to increase, while the intermetallic felts IM12-15 adjust to a constant value between 0.6 - 0.8 mg / cm 2 .
  • the resistance to oxidation in the intermetallic felts is significantly improved.
  • the resistance to oxidation is one of the most important factors for the life of the entire component.
  • the intermetallic felt 2 with a ceramic material 3rd are coated, for example with a TBC (Thermal Barrier Coating). It TBC is a Zr oxide stabilized with Y. Equivalent materials are also conceivable.
  • the ceramic material 3 can on the intermetallic felt 2, it has an uneven surface the intermetallic felt 2 has a very good hold on it and a good one Resistance to oxidation.
  • the ceramic material 3 is a good protection against thermal and mechanical, for example friction-related effects. Cooling air bores, which are located in the turbine blade 1 or on Rotor / stator 4 may be present, do not clog, since it is intermetallic felt 2 is a porous material.
  • FIG. Figure 2 shows schematic representation of a gas turbine with a rotor 4a, a stator 4b.
  • rotor blades 6 on the rotor 4a and guide blades 7 on the stator 7 attached.
  • the guide / rotor blades are usually on the rotor 4a or on the stator 4b 6.7 arranged opposite heat accumulation segments 8.
  • these heat accumulation segments 8 can also be entirely or partly consist of an intermetallic felt.
  • the abrasion can, as already described can be reduced by a layer of TBC.
  • the component can also be cooled under the TBC layer as the cooling medium passes through the porous side Felt can escape.
  • FIG. 5 shows a heat accumulation segment 8 according to the invention Section V in Figure 2.
  • the intermetallic felt 2 was on a load-bearing Basic structure 5 attached.
  • the load-bearing basic structure 5 has fastening means 9 which, for attachment to the rotor 4a or not shown in FIG. Serve stator 4b.
  • the lateral fastening means 9 are by struts 10 connected with each other. Between the struts 10 is on the side that the Turbine blades facing, the intermetallic felt 2 used and with it mechanically connected. This can be done, for example, by soldering, welding or done by pouring. For reasons of durability, the felt should be cohesive be attached to the supporting base structure 5.
  • FIG. 6 shows the section VI-VI of Figure 5. It can be seen that the struts 10 connecting the two fastening means 9 the intermetallic felt 2 not penetrate, but the intermetallic felt 2 is only attached to them. As can be seen from FIG. 6, the temperature resistance of the To increase heat accumulation segment 8, the intermetallic felt 2 in turn are coated with a ceramic material 3, for example with a TBC (Thermal barrier coating). Equivalent materials are also conceivable. How in the turbine blade 1 of FIG. 1, a cooling effect also remains with one Receive abrasion since there is no clogging of the intermetallic felt 2.
  • the intermetallic felt in the exemplary embodiment is shown in FIG 3 on the platform 12 of the turbine blade 1 of the thermal Turbo machine attached.
  • the TBC also serves as protection against wear.
  • FIG. 4 shows a second variant of the exemplary embodiment of detail IV Figure 3.
  • the intermetallic felt 2 Between two turbine blades 1 - on the platform 12 of the Turbine blade 1 - is the intermetallic felt 2 on a basic structure 5, consisting of a casting or another metal attached.
  • the main one Basic structure 5 can also consist of different chambers in order to to ensure optimal air supply to the intermetallic felt 2.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP00810658A 1999-08-09 2000-07-24 Composant de friction d' une turbomachine thermique. Expired - Lifetime EP1076157B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19937577 1999-08-09
DE19937577A DE19937577A1 (de) 1999-08-09 1999-08-09 Reibungsbehaftete Gasturbinenkomponente

Publications (3)

Publication Number Publication Date
EP1076157A2 true EP1076157A2 (fr) 2001-02-14
EP1076157A3 EP1076157A3 (fr) 2004-01-02
EP1076157B1 EP1076157B1 (fr) 2011-07-13

Family

ID=7917752

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00810658A Expired - Lifetime EP1076157B1 (fr) 1999-08-09 2000-07-24 Composant de friction d' une turbomachine thermique.

Country Status (4)

Country Link
US (1) US6499943B1 (fr)
EP (1) EP1076157B1 (fr)
JP (1) JP2001050005A (fr)
DE (1) DE19937577A1 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003027445A1 (fr) * 2001-09-25 2003-04-03 Alstom Technology Ltd Systeme de joint destine a reduire un espace d'etancheite dans une turbomachine rotative
WO2004016819A1 (fr) * 2002-08-16 2004-02-26 Alstom Technology Ltd Materiau intermetallique et son utilisation
DE10356586A1 (de) * 2003-12-04 2005-07-07 Alstom Technology Ltd Verdichterrotor
EP2031080A1 (fr) * 2007-08-30 2009-03-04 ALSTOM Technology Ltd Alliage résistant aux températures élevées
EP2067930A2 (fr) 2007-12-04 2009-06-10 Hitachi Ltd. Dispositif d'étanchéité pour une turbine à vapeur
CH699206A1 (de) * 2008-07-25 2010-01-29 Alstom Technology Ltd Hochtemperaturlegierung.
EP2392779A1 (fr) * 2010-06-03 2011-12-07 General Electric Company Virole de compresseur de turbomachine
FR2963382A1 (fr) * 2010-08-02 2012-02-03 Snecma Roue de turbine a aubes en composite a matrice ceramique

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6670046B1 (en) * 2000-08-31 2003-12-30 Siemens Westinghouse Power Corporation Thermal barrier coating system for turbine components
DE10337094A1 (de) * 2003-08-12 2005-03-03 Mtu Aero Engines Gmbh Einlaufbelag für Gasturbinen sowie Verfahren zur Herstellung desselben
JP2005201079A (ja) * 2004-01-13 2005-07-28 Ishikawajima Harima Heavy Ind Co Ltd タービン翼及びその製造方法
DE102004010236A1 (de) * 2004-03-03 2005-09-15 Mtu Aero Engines Gmbh Ringstruktur in Metallbauweise
US8211524B1 (en) 2008-04-24 2012-07-03 Siemens Energy, Inc. CMC anchor for attaching a ceramic thermal barrier to metal
JP5339503B2 (ja) * 2008-09-12 2013-11-13 国立大学法人京都大学 スーパーｏｄｓ鋼
US9394795B1 (en) * 2010-02-16 2016-07-19 J & S Design Llc Multiple piece turbine rotor blade
US8888446B2 (en) * 2011-10-07 2014-11-18 General Electric Company Turbomachine rotor having patterned coating
EP2971560B1 (fr) * 2013-03-15 2020-05-06 United Technologies Corporation Matériaux composites à maxmet pour pointes de pièces de moteur à turbine

Citations (5)

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Publication number Priority date Publication date Assignee Title
DE3203869C2 (de) 1982-02-05 1984-05-10 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Turbinenlaufschaufel für Strömungsmaschinen, insbesondere Gasturbinentriebwerke
EP0132667A1 (fr) 1983-07-28 1985-02-13 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Aube de turbine refroidie soumise à une charge thermique élevée
DE3235230C2 (fr) 1982-09-23 1990-04-19 Mtu Muenchen Gmbh
DE19750516A1 (de) 1997-11-14 1999-05-20 Asea Brown Boveri Abreibbare Dichtung
EP0919699A2 (fr) 1997-11-26 1999-06-02 United Technologies Corporation Revêtement abrasif d'oxide de zirconium à structure en colonne pour un système d'étanchéité de turbine à gaz

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US3964877A (en) * 1975-08-22 1976-06-22 General Electric Company Porous high temperature seal abradable member
DE2945531C2 (de) * 1979-11-10 1982-01-07 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Turboschaufel mit einem Matellkern und einem Keramikblatt
WO1993024672A1 (fr) * 1992-05-29 1993-12-09 United Technologies Corporation Revetement en ceramique formant une barriere thermique pour pieces soumises a des cycles thermiques rapides
DE19615549B8 (de) * 1996-04-19 2005-07-07 Alstom Vorrichtung zum thermischen Schutz eines Rotors eines Hochdruckverdichters
DE19848104A1 (de) * 1998-10-19 2000-04-20 Asea Brown Boveri Turbinenschaufel
DE19848103A1 (de) * 1998-10-19 2000-04-20 Asea Brown Boveri Dichtungsanordnung
US6235370B1 (en) * 1999-03-03 2001-05-22 Siemens Westinghouse Power Corporation High temperature erosion resistant, abradable thermal barrier composite coating

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3203869C2 (de) 1982-02-05 1984-05-10 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Turbinenlaufschaufel für Strömungsmaschinen, insbesondere Gasturbinentriebwerke
DE3235230C2 (fr) 1982-09-23 1990-04-19 Mtu Muenchen Gmbh
EP0132667A1 (fr) 1983-07-28 1985-02-13 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Aube de turbine refroidie soumise à une charge thermique élevée
EP0132667B1 (fr) 1983-07-28 1987-10-28 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Aube de turbine refroidie soumise à une charge thermique élevée
DE19750516A1 (de) 1997-11-14 1999-05-20 Asea Brown Boveri Abreibbare Dichtung
EP0919699A2 (fr) 1997-11-26 1999-06-02 United Technologies Corporation Revêtement abrasif d'oxide de zirconium à structure en colonne pour un système d'étanchéité de turbine à gaz

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003027445A1 (fr) * 2001-09-25 2003-04-03 Alstom Technology Ltd Systeme de joint destine a reduire un espace d'etancheite dans une turbomachine rotative
US7175387B2 (en) 2001-09-25 2007-02-13 Alstom Technology Ltd. Seal arrangement for reducing the seal gaps within a rotary flow machine
WO2004016819A1 (fr) * 2002-08-16 2004-02-26 Alstom Technology Ltd Materiau intermetallique et son utilisation
US7141128B2 (en) 2002-08-16 2006-11-28 Alstom Technology Ltd Intermetallic material and use of this material
DE10356586A1 (de) * 2003-12-04 2005-07-07 Alstom Technology Ltd Verdichterrotor
US8033784B2 (en) 2003-12-04 2011-10-11 Alstom Technology Ltd. Compressor rotor
EP2031080A1 (fr) * 2007-08-30 2009-03-04 ALSTOM Technology Ltd Alliage résistant aux températures élevées
US8435443B2 (en) 2007-08-30 2013-05-07 Alstom Technology Ltd. High-temperature alloy
EP2067930A2 (fr) 2007-12-04 2009-06-10 Hitachi Ltd. Dispositif d'étanchéité pour une turbine à vapeur
EP2067930A3 (fr) * 2007-12-04 2010-06-30 Hitachi Ltd. Dispositif d'étanchéité pour une turbine à vapeur
EP2372103A1 (fr) * 2007-12-04 2011-10-05 Hitachi Ltd. joint de turbine à vapeur
US8500397B2 (en) 2007-12-04 2013-08-06 Hitachi, Ltd. Seals in steam turbine
US8128351B2 (en) 2007-12-04 2012-03-06 Hitachi, Ltd. Seals in steam turbine
EP2154261A1 (fr) * 2008-07-25 2010-02-17 ALSTOM Technology Ltd Alliage résistant aux températures élevées
US8153054B2 (en) 2008-07-25 2012-04-10 Alstom Technology Ltd High-temperature alloy
CH699206A1 (de) * 2008-07-25 2010-01-29 Alstom Technology Ltd Hochtemperaturlegierung.
EP2392779A1 (fr) * 2010-06-03 2011-12-07 General Electric Company Virole de compresseur de turbomachine
FR2963382A1 (fr) * 2010-08-02 2012-02-03 Snecma Roue de turbine a aubes en composite a matrice ceramique

Also Published As

Publication number Publication date
DE19937577A1 (de) 2001-02-15
JP2001050005A (ja) 2001-02-23
EP1076157B1 (fr) 2011-07-13
EP1076157A3 (fr) 2004-01-02
US6499943B1 (en) 2002-12-31

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