DE102007056452A1 - Sealing system of a turbomachine - Google Patents
Sealing system of a turbomachine Download PDFInfo
- Publication number
- DE102007056452A1 DE102007056452A1 DE200710056452 DE102007056452A DE102007056452A1 DE 102007056452 A1 DE102007056452 A1 DE 102007056452A1 DE 200710056452 DE200710056452 DE 200710056452 DE 102007056452 A DE102007056452 A DE 102007056452A DE 102007056452 A1 DE102007056452 A1 DE 102007056452A1
- Authority
- DE
- Germany
- Prior art keywords
- armor
- based alloy
- sealing system
- component
- inlet lining
- 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- Withdrawn
Links
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
- 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
-
- 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
- C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
- F05C2201/00—Metals
- F05C2201/04—Heavy metals
- F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
- F05C2201/0466—Nickel
-
- 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
-
- 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
-
- 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
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/11—Iron
-
- 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
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/12—Light metals
- F05D2300/121—Aluminium
-
- 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
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
- F05D2300/133—Titanium
-
- 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
- F05D2300/50—Intrinsic material properties or characteristics
- F05D2300/506—Hardness
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Die Erfindung betrifft ein Dichtsystem für Verdichtermodule einer Turbomaschine, insbesondere einer Gasturbine, nämlich zur Abdichtung eines Spalts zwischen einem rotierenden Bauteil (10), insbesondere einer rotorseitigen Laufschaufel, und einem feststehenden Bauteil (12), insbesondere einem statorseitigen Gehäuse, wobei dem feststehenden Bauteil (12) ein Einlaufbelag (13) und dem rotierenden Bauteil (10) eine in den Einlaufbelag (12) einlaufende Panzerung (11) zugeordnet ist. Erfindungsgemäß ist a) das rotierende Bauteil (10) aus einem relativ weichen Werkstoff, nämlich aus einer Titanbasislegierung oder einer Aluminiumbasislegierung oder einer Magnesiumbasislegierung, hergestellt; b) die dem rotierenden Bauteil (10) zugeordnete Panzerung (11) aus einem relativ harten Werkstoff, nämlich aus einer Nickelbasislegierung oder Eisenbasislegierung, hergestellt und c) der dem feststehenden Bauteil (12) zugeordnete Einlaufbelag (13) aus einem erosionsbeständigen Werkstoff hergestellt, der eine geringere Härte als der relativ harte Werkstoff der Panzerung aufweist.The invention relates to a sealing system for compressor modules of a turbomachine, in particular a gas turbine, namely for sealing a gap between a rotating component (10), in particular a rotor-side blade, and a stationary component (12), in particular a stator-side housing, wherein the stationary component ( 12) an inlet lining (13) and the rotating component (10) in the inlet lining (12) incoming armor (11) is assigned. According to the invention, a) the rotating component (10) is made of a relatively soft material, namely a titanium-based alloy or an aluminum-based alloy or a magnesium-based alloy; b) the armor (11) associated with the rotating component (10) is made of a relatively hard material, namely a nickel-based alloy or iron-based alloy, and c) the inlet lining (13) associated with the fixed component (12) is made of an erosion-resistant material, the has a lower hardness than the relatively hard material of the armor.
Description
Die Erfindung betrifft ein Dichtsystem einer Turbomaschine, insbesondere einer Gasturbine, nach dem Oberbegriff des Anspruchs 1. Des Weiteren betrifft die Erfindung ein Verfahren zum Aufbringen einer Panzerung auf ein Bauteil einer Turbomaschine nach dem Oberbegriff des Anspruchs 11.The The invention relates to a sealing system of a turbomachine, in particular a gas turbine, according to the preamble of claim 1. Furthermore The invention relates to a method for applying an armor to a component of a turbomachine according to the preamble of the claim 11th
Turbomaschinen, wie zum Beispiel Gasturbinen, umfassen in der Regel mehrere rotierende Laufschaufeln sowie mehrere feststehende Leitschaufeln, wobei die Laufschaufeln zusammen mit einem Rotor rotieren, und wobei die Laufschaufeln sowie die Leitschaufeln von einem feststehenden Gehäuse umschlossen sind. Zur Leistungssteigerung ist es von Bedeutung, alle Komponenten und Subsysteme zu optimieren. Hierzu zählen auch die sogenannten Dichtsysteme.Turbomachinery such as gas turbines, typically include multiple rotating ones Blades and several fixed vanes, wherein the Rotate blades together with a rotor, and with the blades and the vanes enclosed by a fixed housing are. It is important to increase the performance of all components and subsystems to optimize. These include the so-called sealing systems.
Besonders problematisch ist bei Turbomaschinen die Einhaltung eines minimalen Spalts zwischen den rotierenden Laufschaufeln und dem feststehenden Gehäuse eines Hochdruckverdichters. Bei Hochdruckverdichtern treten nämlich die größten absoluten Temperaturen sowie Temperaturengradienten auf, was die Spalthaltung der rotierenden Laufschaufeln zum feststehenden Gehäuse erschwert. Dies liegt unter anderem auch darin begründet, dass bei Verdichterlaufschaufeln auf Deckbänder, wie sie bei Turbinenlaufschaufeln verwendet werden, verzichtet werden kann.Especially The problem with turbomachinery is the maintenance of a minimum Gaps between the rotating blades and the fixed one Housing of a high pressure compressor. At high pressure compressors namely, the largest absolute Temperatures and temperature gradients on what the gap attitude the rotating blades to the fixed housing difficult. This is partly due to the fact that that with compressor blades on shrouds, as in Turbine blades can be used, can be omitted.
Wie bereits erwähnt, kann bei Laufschaufeln im Verdichter auf ein Deckband verzichtet werden. Daher sind Enden bzw. Spitzen der Laufschaufeln beim sogenannten Anstreifen in das feststehende Gehäuse einem direkten Reibkontakt mit einem dem Gehäuse zugeordneten Einlaufbelag ausgesetzt. Ein solches Anstreifen der Spitzen der Laufschaufeln in den Einlaufbelag wird bei Einstellung eines minimalen Radialspalts durch Fertigungstoleranzen hervorgerufen. Da durch den Reibkontakt der Spitzen der Laufschaufeln an denselben Material abgetragen wird, kann sich über den gesamten Umfang von Gehäuse und Rotor eine unerwünschte Spaltvergrößerung einstellen. Um dies zu vermeiden ist es aus dem Stand der Technik bereits bekannt, die Enden bzw. Spitzen der Laufschaufeln mit einer Schaufelspitzenpanzerung zu versehen.As already mentioned, can with blades in the compressor a shroud be waived. Therefore, ends or tips of the Blades during so-called rubbing into the fixed housing a direct frictional contact with a housing associated Inlet lining exposed. Such a brushing of the tips of the Blades in the inlet lining will set a minimum Radial gaps caused by manufacturing tolerances. Thereby the frictional contact of the tips of the blades with the same material can be removed over the entire circumference of Housing and rotor an undesirable gap enlargement to adjust. To avoid this, it is known from the prior art already known, the ends or tips of the blades with a To provide blade tip armor.
Die
Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, ein neuartiges Dichtsystem einer Turbomaschine, insbesondere einer Gasturbine, sowie ein neuartiges Verfahren zum Aufbringen einer Panzerung auf ein Bauteil einer Turbomaschine zu schaffen.Of these, Based on the present invention, the problem underlying a novel sealing system of a turbomachine, in particular a Gas turbine, as well as a novel method for applying a To create armor on a component of a turbomachine.
Dieses Problem wird durch ein Dichtsystem im Sinne von Anspruch 1 gelöst.This Problem is solved by a sealing system in the sense of claim 1.
Erfindungsgemäß ist a) das rotierende Bauteil aus einem relativ weichen Werkstoff, nämlich aus einer Titanbasislegierung oder einer Aluminiumbasislegierung oder einer Magnesiumbasislegierung, hergestellt; b) die dem rotierenden Bauteil zugeordnete Panzerung aus einem relativ harten Werkstoff, nämlich aus einer Nickelbasislegierung oder Eisenbasislegierung, hergestellt; und c) der dem feststehenden Bauteil zugeordnete Einlaufbelag aus einem erosionsbeständigen Werkstoff hergestellt, der eine geringere Härte als der relativ harte Werkstoff der Panzerung aufweist.According to the invention a) the rotating component of a relatively soft material, namely from a titanium-base alloy or an aluminum-based alloy or a magnesium-based alloy, prepared; b) the rotating one Component associated armor made of a relatively hard material, namely, a nickel-base alloy or iron-based alloy, produced; and c) the inlet lining associated with the stationary component made of an erosion-resistant material, the a lower hardness than the relatively hard material of Has armor.
Das erfindungsgemäße Verfahren zum Aufbringen einer Panzerung auf ein Bauteil einer Turbomaschine ist in Anspruch 11 definiert.The inventive method for applying a Armor on a component of a turbomachine is in claim 11 Are defined.
Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den Unteransprüchen und der nachfolgenden Beschreibung. Ausführungsbeispiele der Erfindung werden, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. Dabei zeigt:preferred Further developments of the invention will become apparent from the dependent claims and the description below. Embodiments of the Invention are provided without being limited thereto explained in detail the drawing. Showing:
Das
Dichtsystem der
Beim
erfindungsgemäßen Dichtsystem ist die rotorseitige
Laufschaufel
Der
Werkstoff des Einlaufbelags
In
der Nickelbasislegierung oder der Eisenbasislegierung der Panzerung
Der
erosionsbeständige Werkstoff des Einlaufbelags
Nach
einer vorteilhaften Weiterbildung der hier vorliegenden Erfindung
ist die Panzerung
Das
Aufbringen der Panzerung
Das
Kalt-Kinetische-Kompaktieren bzw. kinetische Kaltgasspritzen erfolgt
bei einer Geschwindigkeit zwischen 500 und 1000 m/sec, wobei es
sich bei dieser Geschwindigkeit um die Geschwindigkeit handelt,
mit Hilfe derer in einem Trägergas enthaltene Partikel
aus dem Werkstoff der Panzerung zum Herstellen der Panzerung
Hierbei
werden über das Trägergas Partikel aus dem Werkstoff
der Panzerung
Die über
Kalt-Kinetisches-Kompaktieren bzw. kinetische Kaltgasspritzen auf
die Laufschaufel
Obwohl
unter Bezugnahme auf
Die Herstellung von Panzerungen über Kalt-Kinetisches-Kompaktieren bzw. kinetisches Kaltgasspritzen verfügt über den Vorteil, dass einerseits die Panzerung hochgenau mit Hilfe eines dünnen Spritzstrahls und des Weiteren relativ kostengünstig hergestellt werden kann. Mit dem erfindungsgemäßen Dichtsystem ist es möglich, in Verdichtern Laufschaufeln aus einem relativ weichen Werkstoff, nämlich aus einer Titanbasislegierung oder Aluminiumbasislegierung oder Magnesiumbasislegierung zu verwenden, wobei die über kinetisches Kaltgasspritzen bzw. Kalt-Kinetisches-Kompaktieren aufgebrachte Panzerung aus einer Nickelbasislegierung oder Eisenbasislegierung besteht und demnach relativ hart ist.The Production of armor by cold-kinetic compaction or kinetic cold gas spraying has the advantage that on the one hand the armor with the help of a high precision thin spray jet and further relatively inexpensive can be produced. With the invention Sealing system makes it possible in compressors blades from a relatively soft material, namely from a Titanium based alloy or aluminum based alloy or magnesium based alloy using the kinetic cold gas spraying Cold-kinetic compacting applied armor from a Nickel-based alloy or iron-based alloy exists and accordingly is relatively hard.
Die so gepanzerten Laufschaufeln laufen in den Einlaufbelag ein, der aus einem erosionsbeständigen Werkstoff gebildet ist, der eine größere Härte aufweist als der relativ weiche Werkstoff der Laufschaufeln und der eine geringere Härte aufweist als der relativ harte Werkstoff der Panzerung der Laufschaufeln.The so armored blades enter the inlet lining, the is formed of an erosion-resistant material, the has a higher hardness than the relative soft material of the blades and the lower hardness has as the relatively hard material of the armor of the blades.
Derartige Panzerungen verfügen über eine gute Haftung und Duktilität, weshalb die Gefahr einer Rissbildung in der Panzerung und die Gefahr einer Rissfortsetzung in den Grundwerkstoff mit der hier vorliegenden Erfindung deutlich verringert werden kann. Das erfindungsgemäße Dichtsystem ist durch einen dauerhaft geringeren Verschleiß gekennzeichnet.such Armor has good adhesion and Ductility, which is why there is a risk of cracking in the Armor and the risk of crack propagation in the base material can be significantly reduced with the present invention. The sealing system according to the invention is characterized by a marked permanently lower wear.
- 1010
- Laufschaufelblade
- 1111
- Panzerungplating
- 1212
- Gehäusecasing
- 1313
- Einlaufbelaginlet lining
- 1414
- Spaltgap
ZITATE ENTHALTEN IN DER BESCHREIBUNGQUOTES INCLUDE IN THE DESCRIPTION
Diese Liste der vom Anmelder aufgeführten Dokumente wurde automatisiert erzeugt und ist ausschließlich zur besseren Information des Lesers aufgenommen. Die Liste ist nicht Bestandteil der deutschen Patent- bzw. Gebrauchsmusteranmeldung. Das DPMA übernimmt keinerlei Haftung für etwaige Fehler oder Auslassungen.This list The documents listed by the applicant have been automated generated and is solely for better information recorded by the reader. The list is not part of the German Patent or utility model application. The DPMA takes over no liability for any errors or omissions.
Zitierte PatentliteraturCited patent literature
- - US 6194086 B1 [0005] - US 6194086 B1 [0005]
Claims (12)
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200710056452 DE102007056452A1 (en) | 2007-11-23 | 2007-11-23 | Sealing system of a turbomachine |
EP08169608A EP2063072A3 (en) | 2007-11-23 | 2008-11-21 | Sealing arrangement of a turbomachine and method of applying a protecting layer on a component of this turbomachine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200710056452 DE102007056452A1 (en) | 2007-11-23 | 2007-11-23 | Sealing system of a turbomachine |
Publications (1)
Publication Number | Publication Date |
---|---|
DE102007056452A1 true DE102007056452A1 (en) | 2009-05-28 |
Family
ID=40191089
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE200710056452 Withdrawn DE102007056452A1 (en) | 2007-11-23 | 2007-11-23 | Sealing system of a turbomachine |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP2063072A3 (en) |
DE (1) | DE102007056452A1 (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102010052729A1 (en) | 2010-11-26 | 2012-05-31 | Mtu Aero Engines Gmbh | Metal matrix composite armor for component e.g. rotary blade of e.g. aircraft engine, has spray layer that comprises metal matrix that is embedded with hard particles that is homogeneously distributed in layer form |
DE102011084990A1 (en) * | 2011-10-21 | 2013-04-25 | Mahle International Gmbh | Piston used in tribological system of cylinder crankcase for combustion engine, has piston shaft having piston hubs that are connected over running surfaces which are partially provided with coating portion squirted in cold gas process |
DE102014213911A1 (en) | 2014-07-17 | 2016-01-21 | MTU Aero Engines AG | Airgel lining element for turbomachinery |
EP3216980A1 (en) | 2016-03-08 | 2017-09-13 | Siemens Aktiengesellschaft | Method for manufacturing or repairing a rotor blade and/or a housing of a turbomachine |
EP3222812A1 (en) | 2016-03-24 | 2017-09-27 | Siemens Aktiengesellschaft | Method for making or repairing a rotor blade, rotor blade, method for manufacturing or repairing a housing for a fluid flow machine and said housing |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102010019958B4 (en) * | 2010-05-08 | 2016-05-04 | MTU Aero Engines AG | Method for producing an inlet lining |
US8777562B2 (en) * | 2011-09-27 | 2014-07-15 | United Techologies Corporation | Blade air seal with integral barrier |
EP3239467A1 (en) * | 2016-04-27 | 2017-11-01 | Siemens Aktiengesellschaft | Flow machine, rotor blade and housing |
CN106148879A (en) * | 2016-08-18 | 2016-11-23 | 沈阳理工大学 | A kind of nickel 60 base is containing cobalt and the preparation method of chromium metal plasma spraying axial workpiece wear-resistant coating |
Citations (1)
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---|---|---|---|---|
US6194086B1 (en) | 1997-11-06 | 2001-02-27 | Chromalloy Gas Turbine Corporation | Method for producing abrasive tips for gas turbine blades |
Family Cites Families (9)
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US4566700A (en) * | 1982-08-09 | 1986-01-28 | United Technologies Corporation | Abrasive/abradable gas path seal system |
US4884820A (en) * | 1987-05-19 | 1989-12-05 | Union Carbide Corporation | Wear resistant, abrasive laser-engraved ceramic or metallic carbide surfaces for rotary labyrinth seal members |
US5476363A (en) * | 1993-10-15 | 1995-12-19 | Charles E. Sohl | Method and apparatus for reducing stress on the tips of turbine or compressor blades |
EP1391537B1 (en) * | 2001-05-31 | 2012-02-22 | Mitsubishi Heavy Industries, Ltd. | Coating forming method and coating forming material, and abrasive coating forming sheet |
FR2829524B1 (en) * | 2001-09-11 | 2004-03-05 | Snecma Moteurs | PROCESS FOR PRODUCING RADIAL END PORTIONS OF MOBILE PARTS OF TURBOMACHINES |
US6916529B2 (en) * | 2003-01-09 | 2005-07-12 | General Electric Company | High temperature, oxidation-resistant abradable coatings containing microballoons and method for applying same |
DE10356953B4 (en) * | 2003-12-05 | 2016-01-21 | MTU Aero Engines AG | Inlet lining for gas turbines and method for producing the same |
US20060134321A1 (en) * | 2004-12-22 | 2006-06-22 | United Technologies Corporation | Blade platform restoration using cold spray |
US7836591B2 (en) * | 2005-03-17 | 2010-11-23 | Siemens Energy, Inc. | Method for forming turbine seal by cold spray process |
-
2007
- 2007-11-23 DE DE200710056452 patent/DE102007056452A1/en not_active Withdrawn
-
2008
- 2008-11-21 EP EP08169608A patent/EP2063072A3/en not_active Withdrawn
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6194086B1 (en) | 1997-11-06 | 2001-02-27 | Chromalloy Gas Turbine Corporation | Method for producing abrasive tips for gas turbine blades |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102010052729A1 (en) | 2010-11-26 | 2012-05-31 | Mtu Aero Engines Gmbh | Metal matrix composite armor for component e.g. rotary blade of e.g. aircraft engine, has spray layer that comprises metal matrix that is embedded with hard particles that is homogeneously distributed in layer form |
DE102010052729B4 (en) * | 2010-11-26 | 2016-01-21 | MTU Aero Engines AG | Oxidation-resistant armor of blade tips |
DE102011084990A1 (en) * | 2011-10-21 | 2013-04-25 | Mahle International Gmbh | Piston used in tribological system of cylinder crankcase for combustion engine, has piston shaft having piston hubs that are connected over running surfaces which are partially provided with coating portion squirted in cold gas process |
DE102014213911A1 (en) | 2014-07-17 | 2016-01-21 | MTU Aero Engines AG | Airgel lining element for turbomachinery |
EP3216980A1 (en) | 2016-03-08 | 2017-09-13 | Siemens Aktiengesellschaft | Method for manufacturing or repairing a rotor blade and/or a housing of a turbomachine |
EP3222812A1 (en) | 2016-03-24 | 2017-09-27 | Siemens Aktiengesellschaft | Method for making or repairing a rotor blade, rotor blade, method for manufacturing or repairing a housing for a fluid flow machine and said housing |
Also Published As
Publication number | Publication date |
---|---|
EP2063072A3 (en) | 2011-03-09 |
EP2063072A2 (en) | 2009-05-27 |
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