EP0661415A1 - Joint d'étanchéité entre un carter et un corps rotatif - Google Patents

Joint d'étanchéité entre un carter et un corps rotatif Download PDF

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Publication number
EP0661415A1
EP0661415A1 EP93810890A EP93810890A EP0661415A1 EP 0661415 A1 EP0661415 A1 EP 0661415A1 EP 93810890 A EP93810890 A EP 93810890A EP 93810890 A EP93810890 A EP 93810890A EP 0661415 A1 EP0661415 A1 EP 0661415A1
Authority
EP
European Patent Office
Prior art keywords
ceramic
composite
casting
blade
sealing gap
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Withdrawn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
EP93810890A
Other languages
German (de)
English (en)
Inventor
Fritz Staub
Richard Schmid
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.)
Sulzer Markets and Technology AG
Original Assignee
Sulzer Innotec 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 Sulzer Innotec AG filed Critical Sulzer Innotec AG
Priority to EP93810890A priority Critical patent/EP0661415A1/fr
Publication of EP0661415A1 publication Critical patent/EP0661415A1/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Withdrawn legal-status Critical Current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
    • F01D5/14—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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F01D11/125—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 with a reinforcing structure
    • 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
    • F05D2230/90—Coating; Surface treatment

Definitions

  • the invention relates to a device with a rotatable body, housing and intermediate sealing gap according to the preamble of claim 1.
  • the invention also relates to a part of this device and to the production of this part.
  • Devices of the generic type are special turbomachines, in particular gas turbines, but also centrifugal pumps. It is also possible for the rotatable body to be a shaft arranged in a housing, which together with the housing forms a labyrinth seal with respect to an axially flowing medium.
  • a casting process for the production of partially wear-protected castings is known.
  • a penetration composite is produced from a cast metal and hard material particles, the hard material particles, together with binding agent and flux, being brought into the form of porous carrier cores and these carrier cores being inserted into the cavity of a mold shell.
  • the tips of turbine blades can be armored with a composite or composite that is composed of a metal matrix and ceramic particles.
  • the abrasive material is produced from a powder mixture of metal and ceramic, the mixture being heated to a temperature at which the metal melts and thus produces the composite after solidification.
  • the porous ceramic body is in the form of a ceramic framework with an open-cell foam structure.
  • a smooth surface is provided for the armor of the blade tip formed with this composite.
  • the bond on the abrasive surface is carried out in such a way that the ceramic phase forms elevations on the surface which emerge from the bond. This property is obtained, for example, by selectively etching away the metallic matrix on the surface a few tenths of a millimeter deep.
  • the elevations of the ceramic phase are in the form of labyrinth-like structural elements.
  • the structured ceramic has a honeycomb structure.
  • the honeycomb walls which partially protrude above the metal matrix, are essentially perpendicular to the surface or enclose an acute angle with the surface normal.
  • the honeycomb structure can be created, for example, by means of an extrusion process - just like in the production of auto-catalysts - and by subsequent separation into parts that are in line with the product.
  • FIG. 1 The following parts of a gas turbine can be seen in FIG. 1: the impeller 1 (rotor) with the axis of rotation 4; Turbine blades 10 on the impeller 1; an annular region 20 (stator) of the housing 2, which concentrically surrounds the impeller; a sealing gap 3 between the blades 10 and the inner housing surface; and stator blades 10 '.
  • the width of the sealing gap 3 is kept to a minimum; contact between the blades and the stator can therefore occur during operation.
  • stator surface and the blade tips should be designed in such a way that the blades are not damaged when they are touched. (For more detailed explanations of this problem, see for example: M.Borel, R.Schmid “Abradables Increase Turbine Blade Life” SULZER TECHNICAL REVIEW 4/1990, p.7-11).
  • FIG. 2 shows an enlarged perspective view of the turbine blade 10.
  • the tip of the turbine blade is shown in more detail in FIG.
  • the labyrinth-like structural elements are formed from parts of the structural ceramic that emerge from the composite as elevations 14.
  • the arrow 15 indicates the direction of movement of the blade tip.
  • FIGS. 4 to 7 relate to the composite, which is composed of a honeycomb-shaped structural ceramic 13 and a metallic matrix 12, this composite being provided as armor for a turbine blade.
  • Figure 4 is a section along the line IV-IV in Figure 5, while Figure 5 is a section along the line V-V in Figure 4. 5 also shows the stator surface 21 'and the sealing gap 3.
  • the arrow 15 indicates the direction of rotation of the impeller 1 (Fig.1). Parts of the ceramic phase 13 protrude with the elevations 14 from the composite 12, 13 into the sealing gap 3.
  • the stator surface 21 ' is present as a coating 21 made of zirconium oxide, for example.
  • the structural ceramic 13 consists of a material that is more resistant than the coating 21 in the operating state of the gas turbine.
  • FIGS. 5 to 7 show three examples of the geometry of the elevations 14.
  • the honeycomb walls 13a are perpendicular to the surface (FIGS. 5, 6) and have one or two beveled flanks 14a and 14b.
  • the honeycomb walls 13a can also form an acute angle with the surface normal 16 (FIG. 7).
  • the structural ceramics can be produced by means of various known processes: for example by extrusion or casting processes (including the subsequent sintering) or by thermal spraying.
  • the structural ceramic produced in this way is cut into pieces with the shape according to the product, using cutting discs, for example, or using a high-pressure water jet.
  • the "cutting edge geometry" of the elevations 14 can be adjusted when the cut is made and can be optimized on the basis of results from brushing tests ("abradable tests").
  • the casting takes place under vacuum or protective gas.
  • the mold is poured using a mold shell which is open at the bottom and which is preheated and mounted on a cooling plate.
  • a selection system is additionally integrated in the mold shell between the cooling plate and the workpiece. Tests have shown that the stored Ceramic structures do not result in growth disturbances in the formation of stem or single crystal structures.
  • Anchoring tabs are provided at suitable points for fixing the structural ceramic in the molded shell; Platinum pins can also be used for the same purpose.
  • thorium oxide ThO2 which has a high melting point (3573 K)
  • the nitrides mentioned in claim 9 have the advantage that they are resistant to oxidation and, moreover, do not undergo any reactions with the metallic matrix.
  • a separation layer made of borides is provided for the carbides, in order to prevent reactions between Ni and Si and C, for example in the case of a ceramic phase made of SiC and a metallic phase made of a nickel-based alloy. The separating layer is produced by coating the structural ceramic before the composite is produced.
  • the most effective cutting edge and labyrinth formation is created at the tip of the blade by grinding and lapping as well as by subsequent deep etching of the metallic matrix. Since the blade tips are exposed to high temperatures in the gas turbine, they may need to be protected against oxidation. This is achieved, for example, by means of aluminizing.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP93810890A 1993-12-17 1993-12-17 Joint d'étanchéité entre un carter et un corps rotatif Withdrawn EP0661415A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP93810890A EP0661415A1 (fr) 1993-12-17 1993-12-17 Joint d'étanchéité entre un carter et un corps rotatif

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP93810890A EP0661415A1 (fr) 1993-12-17 1993-12-17 Joint d'étanchéité entre un carter et un corps rotatif

Publications (1)

Publication Number Publication Date
EP0661415A1 true EP0661415A1 (fr) 1995-07-05

Family

ID=8215095

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93810890A Withdrawn EP0661415A1 (fr) 1993-12-17 1993-12-17 Joint d'étanchéité entre un carter et un corps rotatif

Country Status (1)

Country Link
EP (1) EP0661415A1 (fr)

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0702130A3 (fr) * 1994-09-16 1998-06-10 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Extrémité d'aube avec un revêtement coupant
EP0916811A3 (fr) * 1997-11-17 2000-08-23 General Electric Company Extrémité rainurée d'aube de turbine
WO2003010419A1 (fr) * 2001-07-23 2003-02-06 Alstom Technology Ltd Dispositif pour reduire la fente d'etancheite entre composant mobile et composant stationnaire a l'interieur d'une turbomachine
EP1764478A2 (fr) 2005-09-19 2007-03-21 General Electric Company Aube de turbine à vapeur et procédé associé
EP1876326A2 (fr) * 2006-07-05 2008-01-09 United Technologies Corporation Rotor pour moteur de turbine à gaz
DE102009012945A1 (de) 2009-03-12 2010-09-16 Mtu Aero Engines Gmbh Verfahren zur Herstellung einer abrasiven Beschichtung und Bauteil für eine Turbomaschine
US20110014060A1 (en) * 2009-07-17 2011-01-20 Rolls-Royce Corporation Substrate Features for Mitigating Stress
EP2309098A1 (fr) * 2009-09-30 2011-04-13 Siemens Aktiengesellschaft Profil et aube directrice, aube rotorique, turbine à gaz et turbomachine associées
WO2010121597A3 (fr) * 2009-04-23 2011-07-07 Mtu Aero Engines Gmbh Procédé de production d'un blindage d'un bout d'aube et aubes ainsi produites et turbines à gaz
WO2011026468A3 (fr) * 2009-09-04 2011-10-13 Mtu Aero Engines Gmbh Turbomachine et procédé de production d'un revêtement de rodage structuré
EP2492443A1 (fr) * 2011-02-22 2012-08-29 Siemens Aktiengesellschaft Procédé de fabrication d'une couche de protection pour une aube directrice
EP1111195B2 (fr) † 1999-12-20 2013-05-01 Sulzer Metco AG Surface structurée utilisée comme couche de rasage dans les turbomachines
WO2014099814A1 (fr) * 2012-12-17 2014-06-26 General Electric Company Aubes de turbine robustes
DE10140742B4 (de) * 2000-12-16 2015-02-12 Alstom Technology Ltd. Vorrichtung zur Dichtspaltreduzierung zwischen einer rotierenden und einer stationären Komponente innerhalb einer axial durchströmten Strömungsmaschine
US9713912B2 (en) 2010-01-11 2017-07-25 Rolls-Royce Corporation Features for mitigating thermal or mechanical stress on an environmental barrier coating
EP3323984A1 (fr) * 2016-11-17 2018-05-23 United Technologies Corporation Profil aérodynamique comportant une section de revêtement segmentée géométriquement
EP3323986A1 (fr) * 2016-11-17 2018-05-23 United Technologies Corporation Profil aérodynamique comportant une section de revêtement segmentée géométriquement
US10040094B2 (en) 2013-03-15 2018-08-07 Rolls-Royce Corporation Coating interface
DE102017211643A1 (de) * 2017-07-07 2019-01-10 MTU Aero Engines AG Turbomaschinen-Dichtungselement
WO2021055004A1 (fr) * 2019-09-20 2021-03-25 Raytheon Technologies Corporation Systèmes abradables de turbomoteur

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2119460A5 (fr) * 1970-12-21 1972-08-04 Clevite Corp
US4148494A (en) * 1977-12-21 1979-04-10 General Electric Company Rotary labyrinth seal member
GB2010982A (en) * 1977-12-21 1979-07-04 Gen Electric Gas seal and method for making
EP0158307A1 (fr) * 1984-04-10 1985-10-16 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Boîtier pour une turbomachine
DE8411277U1 (de) * 1984-04-10 1986-08-14 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Gehäuse einer Strömungsmaschine
US4735656A (en) * 1986-12-29 1988-04-05 United Technologies Corporation Abrasive material, especially for turbine blade tips
EP0376071A2 (fr) * 1988-12-30 1990-07-04 Textron Inc. Elément de joint constitué de filaments tressés
DE4107416A1 (de) * 1990-04-25 1991-11-28 Gisag Ag Giesserei Masch Verfahren zur herstellung von partiell verschleissgeschuetzten gussstuecken
EP0477136A1 (fr) * 1990-09-21 1992-03-25 Sulzer Innotec Ag Procédé pour fabriquer des pièces coulées par solidification dirigée ou monocristalline

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2119460A5 (fr) * 1970-12-21 1972-08-04 Clevite Corp
US4148494A (en) * 1977-12-21 1979-04-10 General Electric Company Rotary labyrinth seal member
GB2010982A (en) * 1977-12-21 1979-07-04 Gen Electric Gas seal and method for making
EP0158307A1 (fr) * 1984-04-10 1985-10-16 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Boîtier pour une turbomachine
DE8411277U1 (de) * 1984-04-10 1986-08-14 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Gehäuse einer Strömungsmaschine
US4735656A (en) * 1986-12-29 1988-04-05 United Technologies Corporation Abrasive material, especially for turbine blade tips
EP0376071A2 (fr) * 1988-12-30 1990-07-04 Textron Inc. Elément de joint constitué de filaments tressés
DE4107416A1 (de) * 1990-04-25 1991-11-28 Gisag Ag Giesserei Masch Verfahren zur herstellung von partiell verschleissgeschuetzten gussstuecken
EP0477136A1 (fr) * 1990-09-21 1992-03-25 Sulzer Innotec Ag Procédé pour fabriquer des pièces coulées par solidification dirigée ou monocristalline

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
M. BOREL ET AL.: "Grâce aux abradables les ailettes de turbines vivent plus longtemps", REVUE TECHNIQUE SULZER, no. 4, 1990, WINTERTHUR, CH, pages 7 - 11 *

Cited By (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0702130A3 (fr) * 1994-09-16 1998-06-10 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Extrémité d'aube avec un revêtement coupant
EP0916811A3 (fr) * 1997-11-17 2000-08-23 General Electric Company Extrémité rainurée d'aube de turbine
EP1111195B2 (fr) † 1999-12-20 2013-05-01 Sulzer Metco AG Surface structurée utilisée comme couche de rasage dans les turbomachines
DE10140742B4 (de) * 2000-12-16 2015-02-12 Alstom Technology Ltd. Vorrichtung zur Dichtspaltreduzierung zwischen einer rotierenden und einer stationären Komponente innerhalb einer axial durchströmten Strömungsmaschine
WO2003010419A1 (fr) * 2001-07-23 2003-02-06 Alstom Technology Ltd Dispositif pour reduire la fente d'etancheite entre composant mobile et composant stationnaire a l'interieur d'une turbomachine
EP1764478A3 (fr) * 2005-09-19 2008-10-29 General Electric Company Aube de turbine à vapeur et procédé associé
JP2007085344A (ja) * 2005-09-19 2007-04-05 General Electric Co <Ge> 翼端漏れ損失低減のための蒸気冷却型ガスタービン動翼
US7922455B2 (en) 2005-09-19 2011-04-12 General Electric Company Steam-cooled gas turbine bucker for reduced tip leakage loss
EP1764478A2 (fr) 2005-09-19 2007-03-21 General Electric Company Aube de turbine à vapeur et procédé associé
EP1876326A2 (fr) * 2006-07-05 2008-01-09 United Technologies Corporation Rotor pour moteur de turbine à gaz
EP1876326A3 (fr) * 2006-07-05 2011-08-10 United Technologies Corporation Rotor pour moteur de turbine à gaz
DE102009012945A1 (de) 2009-03-12 2010-09-16 Mtu Aero Engines Gmbh Verfahren zur Herstellung einer abrasiven Beschichtung und Bauteil für eine Turbomaschine
US9021696B2 (en) 2009-04-23 2015-05-05 MTU Aero Engines AG Method for producing a plating of a vane tip and correspondingly produced vanes and gas turbines
WO2010121597A3 (fr) * 2009-04-23 2011-07-07 Mtu Aero Engines Gmbh Procédé de production d'un blindage d'un bout d'aube et aubes ainsi produites et turbines à gaz
EP2275646A3 (fr) * 2009-07-17 2017-12-13 Rolls-Royce Corporation Extrémité d'aube comprenant des caractéristiques de réduction de la fatigue
US20110014060A1 (en) * 2009-07-17 2011-01-20 Rolls-Royce Corporation Substrate Features for Mitigating Stress
US9194243B2 (en) * 2009-07-17 2015-11-24 Rolls-Royce Corporation Substrate features for mitigating stress
WO2011026468A3 (fr) * 2009-09-04 2011-10-13 Mtu Aero Engines Gmbh Turbomachine et procédé de production d'un revêtement de rodage structuré
EP2309098A1 (fr) * 2009-09-30 2011-04-13 Siemens Aktiengesellschaft Profil et aube directrice, aube rotorique, turbine à gaz et turbomachine associées
US20120230818A1 (en) * 2009-09-30 2012-09-13 Andrew Shepherd Airfoil and corresponding guide vane, blade, gas turbine and turbomachine
US9713912B2 (en) 2010-01-11 2017-07-25 Rolls-Royce Corporation Features for mitigating thermal or mechanical stress on an environmental barrier coating
WO2012113486A1 (fr) * 2011-02-22 2012-08-30 Siemens Aktiengesellschaft Procédé de fabrication d'une couche de protection pour aube mobile
EP2492443A1 (fr) * 2011-02-22 2012-08-29 Siemens Aktiengesellschaft Procédé de fabrication d'une couche de protection pour une aube directrice
CN104838092A (zh) * 2012-12-17 2015-08-12 通用电气公司 耐用涡轮叶片
WO2014099814A1 (fr) * 2012-12-17 2014-06-26 General Electric Company Aubes de turbine robustes
US10040094B2 (en) 2013-03-15 2018-08-07 Rolls-Royce Corporation Coating interface
EP3323984A1 (fr) * 2016-11-17 2018-05-23 United Technologies Corporation Profil aérodynamique comportant une section de revêtement segmentée géométriquement
EP3323986A1 (fr) * 2016-11-17 2018-05-23 United Technologies Corporation Profil aérodynamique comportant une section de revêtement segmentée géométriquement
US10480334B2 (en) 2016-11-17 2019-11-19 United Technologies Corporation Airfoil with geometrically segmented coating section
US10711624B2 (en) 2016-11-17 2020-07-14 Raytheon Technologies Corporation Airfoil with geometrically segmented coating section
DE102017211643A1 (de) * 2017-07-07 2019-01-10 MTU Aero Engines AG Turbomaschinen-Dichtungselement
WO2021055004A1 (fr) * 2019-09-20 2021-03-25 Raytheon Technologies Corporation Systèmes abradables de turbomoteur
EP4378911A3 (fr) * 2019-09-20 2024-08-07 RTX Corporation Systèmes abradables de moteur à turbine

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