EP2215405B1 - Élément de machine et turbine à gaz - Google Patents

Élément de machine et turbine à gaz Download PDF

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Publication number
EP2215405B1
EP2215405B1 EP08857245.8A EP08857245A EP2215405B1 EP 2215405 B1 EP2215405 B1 EP 2215405B1 EP 08857245 A EP08857245 A EP 08857245A EP 2215405 B1 EP2215405 B1 EP 2215405B1
Authority
EP
European Patent Office
Prior art keywords
armor
base body
machine component
elements
plating
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.)
Active
Application number
EP08857245.8A
Other languages
German (de)
English (en)
Other versions
EP2215405A1 (fr
Inventor
Elke Henschel
Joachim Skoczowsky
Martin Stapper
Birgit Grüger
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 EP08857245.8A priority Critical patent/EP2215405B1/fr
Publication of EP2215405A1 publication Critical patent/EP2215405A1/fr
Application granted granted Critical
Publication of EP2215405B1 publication Critical patent/EP2215405B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • 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
    • C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
    • C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/02—Casings; Linings; Walls characterised by the shape of the bricks or blocks used
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05001—Preventing corrosion by using special lining materials or other techniques
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05002—Means for accommodate thermal expansion of the wall liner
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05003—Details of manufacturing specially adapted for combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05004—Special materials for walls or lining
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03342—Arrangement of silo-type combustion chambers

Definitions

  • the invention relates to a machine component with a base body made of a base material, which is provided in a portion of its surface with an armor made of a coating material with a greater hardness and / or toughness compared to the base material. It further relates to a gas turbine with a number of machine components of this type.
  • a machine component with the features of the preamble of claim 1, is known from DE 10 2004 001 722 A1 known.
  • Turbines in particular gas turbines, are used in many areas to drive generators or work machines.
  • the energy content of a fuel is used to generate a rotational movement of a turbine shaft.
  • the fuel is burned in a combustion chamber, compressed air being supplied by an air compressor.
  • the working medium produced in the combustion chamber by the combustion of the fuel, under high pressure and at high temperature, is guided via a turbine unit arranged downstream of the combustion chamber, where it relaxes to perform work.
  • a number of rotor blades which are usually combined into blade groups or blade rows, are arranged thereon and drive the turbine shaft via a momentum transfer from the working medium.
  • a turbine of this type comprises a plurality of components or machine components which are positioned in the turbine in accordance with predetermined dimensions, shapes and / or tolerances. In many cases, it may be desirable to contact the neighboring machine components or components minimize each other, so as to keep wear of the affected components particularly low. Nevertheless, during operation of the turbine, for example as a result of thermal expansion or as a result of operating vibrations or the like, there may always be undesirable contact between such components, so that some wear of such components occurs. For example, as such machine components in the region of the combustion chamber of the gas turbine usually a so-called flame tube, a mixing housing and an inner housing adjacent to each other.
  • the machine components can be manufactured in what is referred to as an armored version, the areas particularly affected by the expected wear or expected contacts with neighboring components being coated with a protective coating, also referred to as armor ,
  • An armor of this type can be formed from an application material which has a greater mechanical hardness and / or toughness compared to the base material of the respective component, so that wear occurring as a result of contact can already be reduced by such a suitable choice of material.
  • suitable different chemical compositions of the base and / or the coating material a higher corrosion resistance of the components of the machine components can be achieved.
  • thermal expansion of the base body in the area provided with the application material may lead to cracking and other damage due to the different thermal expansion behavior.
  • thermally comparatively highly loaded regions such as in the interior of the combustion chamber of a gas turbine, such armored machine components are therefore only partially suitable.
  • the machine component should be provided with a suitable armor for a fundamental applicability while maintaining wear-resistant working conditions and in order to avoid the possible disadvantages associated with an armor, it makes sense to keep the lateral extent of the armor particularly low.
  • individual zones of the armor are executed decoupled from each other, so as to allow sufficient flexibility against thermal deformation and the like. This is achieved by performing the armor segment by segment and formed by a number of armor segments.
  • the armor segments may be applied by suitable techniques on the body of the machine component.
  • the armor segments are applied by build-up welding on the base body, so that a particularly intimate connection to the body and thus a high stability of the machine component is achieved overall.
  • the welding process must often be started and stopped, which can result in distortion of the body due to the high working temperatures during build-up welding.
  • a cooling air is passed around the exterior of the body. The arrangement of the segments, the cooling air is injected in the channels provided in the hot gas path, whereby hot and cold spots are generated according to the segmentation at the intersection points formed by the approaches of the segmentation.
  • the invention is therefore based on the object of specifying a machine component of the above-mentioned type whose armor application achieves the greatest possible stability while simultaneously being able to process further, and which causes a slight stress on the machine component by the application method.
  • the occurrence of hot and cold spots should be largely avoided.
  • a gas turbine with a number of such machine components is to be specified.
  • the armor is formed by a number of armor elements, which are tilted in its longitudinal direction to the main flow of a main body flowing hot gas on the base body, wherein the tilt angle is greater than 0 ° and less than 90 °, so that the Armor elements spiraled around the base body.
  • the invention is based on the consideration that a load can be avoided by frequent start and stop operations during build-up welding when the welding process is carried out consistently. Furthermore, a particularly high transverse stability can be achieved by a suitable arrangement of the armor elements and a negative effect of the cooling air on the thermal behavior of the body can be largely avoided by a suitable guidance of the cooling air.
  • the tilt angle is designed so that the armor elements an arrangement of the kind that the formed by the obliquely executed armor geometry cooling air passage rotates the body in at least simple design and the cooling air thereby experiences a twist to the flow direction of the hot gas, thereby a largely uniform distribution of the cooling air can be achieved.
  • a tilt angle of more than zero and less than 90 ° between the main flow of the main body flowing through the hot gas and the longitudinal direction of the armor elements mounted on the body armor elements advantageously not continuously, but in segments, ie with a number of interruptions of the welding job, arranged on the body.
  • an application of the armor segments by laser powder coating welding is advantageously provided, but also an order other welding processes or by order spray conceivable.
  • the advantages achieved by the invention are in particular that a particularly high transverse stability and torsional stiffness of the body forming rings and a particularly advantageous guidance of the cooling air is achieved with simultaneous flexibility of the body for further processing by the arrangement of the armor segments.
  • the gas turbine 1 has a compressor 2 for combustion air, a combustion chamber 4 and a turbine 6 for driving the compressor 2 and a generator, not shown, or a working machine.
  • the turbine 6 and the compressor 2 are arranged on a common, also called turbine rotor turbine shaft 8, with which the generator or the working machine is connected, and which is rotatably mounted about its central axis 9.
  • the combustion chamber 4 is equipped with a number of burners 10 for the combustion of a liquid or gaseous fuel. It is also provided on its inner wall with heat shield elements not shown.
  • the turbine 6 has a number of rotatable blades 12 connected to the turbine shaft 8.
  • the blades 12 are arranged in a ring on the turbine shaft 8 and thus form a number of blade rows.
  • the turbine 6 comprises a number of fixed vanes 14, which are also fixed in a ring shape to form an airfoil on an inner casing 16 of the turbine 6.
  • the blades 12 serve to drive the turbine shaft 8 by momentum transfer from a turbine 6 flowing through the working medium M.
  • the vanes 14, however, serve to guide the flow of the working medium M between two seen in the flow direction of the working medium M consecutive blade rows or blade rings.
  • a successive pair of a ring of vanes 14 or a row of vanes and a ring of vanes 12 or a blade row is also referred to as a turbine stage.
  • Each vane 14 has a platform 18, which is arranged to fix the respective vane 14 on the inner housing 16 of the turbine 6 as a wall element.
  • the platform 18 is a thermally comparatively heavily loaded component, the outer boundary of a hot gas channel for the the turbine 6 flowing through the working medium M forms.
  • Each blade 12 is attached to the turbine shaft 8 in an analogous manner via a platform 20, also referred to as a blade root.
  • each guide ring 21 on the inner housing 16 of the turbine 6 is arranged between the spaced-apart platforms 18 of the guide vanes 14 of two adjacent rows of guide vanes.
  • the inner surface of each guide ring 21 is also exposed to the hot, the turbine 6 flowing through the working medium M and spaced in the radial direction from the outer end 22 of the opposed blades 12 a blade row through a gap 24.
  • This principle is applicable to all gas turbines 1, that is to say, for example, with can, can-annular, annular combustion chambers or silo combustion chambers.
  • gas turbine primarily means a gas turbine with silo combustion chambers. Nevertheless, this invention is applicable to all gas turbines.
  • each of the combustion chambers 4 is in its inflow, to which a number of unspecified supply lines for media, such as fuel and combustion air are connected, equipped with a so-called flame tube 30, within which the combustion of the fuel takes place.
  • a flame tube 30 is the output side connected to an inner housing 36 of the combustion chamber 4.
  • the flame tube 30, the transition piece 34 and the inner housing 36 are connected to each other in the manner of nested tubes together, so that ensures a reliable flow of media flow from the flame tube 30 into the inner housing 36 of the combustion chamber 4 is.
  • the respective nested tube ends are positioned as possible without contact to each other, while maintaining the predetermined dimensions and tolerances, so that wear due to components in contact with one another and components rubbing against one another is avoided as far as possible.
  • a recurrent contact of these components with each other can not be avoided, so that residual wear is to be expected in every case. To account for this wear, regular inspection and replacement of these components is required as part of maintenance and inspection work.
  • each of the engine components flame tube 30, transition piece 34 and inner housing 36 is constructed from a base made of base material 40, which in each case in the 3 to 5 shown portion of its surface is provided with an armor 42 of a coating material.
  • the application material is chosen such that it has a greater hardness and / or toughness compared to the base material, so that an increased resistance to mechanical and thermal stress is given.
  • the application material is applied to the base body 40 in each case by build-up welding.
  • the armor 42 of the respective machine component is performed segmented.
  • the armor 42 comprises a plurality of armor segments 44, wherein the dimensioning of the armor segments 44 with respect to the dimensioning of the actual machine component and the materials used is chosen such that an excessive impairment of the base body 40 is avoided by different thermal expansion behavior and the like.
  • the armor segments 44 are each introduced into associated recesses in the base body 40.
  • the recesses may have been introduced by suitable machining methods, such as by milling, turning or grinding.
  • the dimensioning can in principle be made such that the armor segments 44 are applied to a flat surface of the base body 40 and correspondingly their thickness corresponding recesses arise between them.
  • the preparation can also, as in the 3 to 5 is shown performed in such a way that the outer surface of the armor segments 44 with the outer surface of extending between the outer armor segments 44 webs 46 of the body 40 form a continuous and thus planar surface.
  • the armor segments 44 can also be applied to a flat, non-recessed surface.
  • a finished machine component thereby creates a component which largely corresponds to an originally provided component in terms of its shape, dimensioning and dimensional stability and in particular has a correspondingly smooth and planar surface.
  • a bent cooling air ring 50 can be embodied as an at least partially armored machine component of the type mentioned.
  • the cooling air ring 50 is also provided on its surface with armor segments 44, which are incorporated into corresponding recesses of the cooling air ring 50 forming base body 40.
  • cooling air channels 52 are additionally provided, which are formed by corresponding holes.
  • the recesses also referred to as pockets, in which the armor segments 44 are arranged
  • said recesses need not be formed as pockets, but also a circumferential groove not shown here is conceivable, the desired geometry of the cooling air ring 50 can be maintained , Nevertheless, even when using the armor segments 44, a virtually smooth and thus streamlined surface and a smooth transition to the base body 40 is created. This ensures increased wear reduction and improved bonding between the materials used.
  • FIG. 5 It is shown that as such armored machine components in particular the transition piece 34 and the flame tube 30 of the gas turbine 1 are designed in their overlapping region. Armor 42 of these machine components are provided in each case on the facing surface segments. In a.derartigen arrangement of two such armored machine components is also, as provided for the transition piece 34 and the flame tube 30, by a suitable choice of material for the armor 42 targeted focusing the wear on one of the two machine components, in particular on the lighter replaceable machine component, allows. For this purpose, in the present case specifically provided to choose the application material for the armor 42 of the flame tube 30 of lesser hardness and / or toughness than the material for the armor 42 of the transition piece 34. But also a reverse arrangement, the order material for the armor 42 of the transition piece 34 with a lower hardness and / or toughness than for the armor 42 of the flame tube 30 may be useful.
  • FIG. 6 shows the base body 40 with the cooling air channels 52 and the applied armor elements 54, in this embodiment, the angle between the main flow direction 56 of the flowing along the walls of the base body 40 hot gas and the longitudinal direction of the armor elements 54 is particularly small.
  • the armor elements 54 surround the main body 40 in such an embodiment in the form of a helix, wherein the tilt angle is to choose depending on the requirements in a range greater than 0 and less than 90 °.
  • armor elements 54 which are advantageously applied to base body 40 by laser powder build-up welding, can be applied in a continuous welding operation without start / stop operation and the risks associated with the respective breaking off and new start of the welding operation, in particular the susceptibility to errors during the welding process, be reduced.
  • the thermal impairments and thus material loads of the base body 40 and the application material can be largely avoided by a continuous welding process.
  • a segmentation of the armor 42 also in this embodiment, by interrupting the welding processes of the build-up welding conceivable.
  • an increase in the flexibility of the machine component can be achieved.
  • FIG. 7 on the base body 40 in a opposite to the view in FIG. 6
  • This is similar in shape to the threads of a screw or a threaded rod, the slope of the armor elements 54 formed by a thread of the type mentioned comparable embodiment of the Armor 42 determined by the tilt angle.
  • the tilt angle formed by the orientation of the armor elements 54 only one path, so a circulation of the build-up welding of the armor elements 54 to the body and thus only a channel for example, the leadership of the cooling air.
  • the armor elements 54 revolve around the main body 40 several times, resulting in a segmentation of the armor elements 54, that is to say a division of the armor into the armor segments 44, and the armor segments 44 are to be applied in a plurality of welding operations.
  • the individual armor segments 44 are used for transverse reinforcement of the base body 40, wherein a subsequent further processing of the provided with the application material base body 40, for example, bending or the like, due to the segmentation of the armor elements 54 is still possible.
  • channels are formed, wherein in the case of cooling air flowing into the channels, this undergoes a swirl to the flow direction 56 of the hot gas flowing through the base body 40 and thus the cooling air is more uniform than, for example, during segmentation the armor is distributed in a rectangular shape on the circumference of the base body 40.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Laser Beam Processing (AREA)

Claims (7)

  1. Elément de machine ayant un corps (40) de base en un matériau de base, qui est pourvu, dans une zone partielle de sa surface, d'un blindage (42) en un matériau d'apport ayant une dureté et/ou une ténacité plus grande que le matériau de base, caractérisé en ce que le blindage (42) est formé d'un certain nombre d'éléments (54) de blindage, les éléments (54) de blindage étant déposés sur le corps (40) de base en ayant leur direction longitudinale inclinée par rapport à la direction (56) de courant principal d'un gaz chaud passant dans le corps (40) de base, l'angle d'inclinaison étant plus grand que 0° et plus petit que 90°, de manière à ce que les éléments (54) de blindage entourent en forme de spirale le corps (40) de base.
  2. Elément de machine, suivant la revendication 1, dans lequel l'élément (54) de blindage ou les éléments (54) de blindage est ou sont segmentés.
  3. Elément de machine, suivant l'une des revendications 1 à 2, dans lequel l'élément (54) de blindage ou les éléments (54) de blindage est ou sont déposés par soudure sur le corps (40) de base.
  4. Elément de machine, suivant la revendication 3, dans lequel l'élément (54) de blindage ou les éléments (54) de blindage sont déposés sur le corps (40) de base par soudure laser avec apport de poudre.
  5. Elément de machine, suivant l'une des revendications 1 à 2, dans lequel l'élément (54) de blindage ou les éléments (54) de blindage sont déposés sur le corps de base par projection à la flamme.
  6. Turbine (1) à gaz, ayant un certain nombre d'éléments de machine suivant l'une des revendications 1 à 5.
  7. Turbine à gaz, suivant la revendication 6, dans lequel un tube (30) de flamme d'une chambre de combustion (4), une enveloppe (34) de mélange d'une chambre de combustion (4) et/ou une enveloppe intérieure d'une chambre de combustion (4) sont conformés en éléments de machine suivant l'une des revendications 1 à 3.
EP08857245.8A 2007-12-04 2008-10-31 Élément de machine et turbine à gaz Active EP2215405B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP08857245.8A EP2215405B1 (fr) 2007-12-04 2008-10-31 Élément de machine et turbine à gaz

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP07023418A EP2068082A1 (fr) 2007-12-04 2007-12-04 Composants de machines et turbine à gaz
EP08857245.8A EP2215405B1 (fr) 2007-12-04 2008-10-31 Élément de machine et turbine à gaz
PCT/EP2008/064768 WO2009071395A1 (fr) 2007-12-04 2008-10-31 Élément de machine et turbine à gaz

Publications (2)

Publication Number Publication Date
EP2215405A1 EP2215405A1 (fr) 2010-08-11
EP2215405B1 true EP2215405B1 (fr) 2016-04-20

Family

ID=39467186

Family Applications (2)

Application Number Title Priority Date Filing Date
EP07023418A Withdrawn EP2068082A1 (fr) 2007-12-04 2007-12-04 Composants de machines et turbine à gaz
EP08857245.8A Active EP2215405B1 (fr) 2007-12-04 2008-10-31 Élément de machine et turbine à gaz

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP07023418A Withdrawn EP2068082A1 (fr) 2007-12-04 2007-12-04 Composants de machines et turbine à gaz

Country Status (6)

Country Link
US (1) US9702561B2 (fr)
EP (2) EP2068082A1 (fr)
CN (1) CN101889173B (fr)
HU (1) HUE029774T2 (fr)
RU (1) RU2492327C2 (fr)
WO (1) WO2009071395A1 (fr)

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4289447A (en) * 1979-10-12 1981-09-15 General Electric Company Metal-ceramic turbine shroud and method of making the same
US5043548A (en) * 1989-02-08 1991-08-27 General Electric Company Axial flow laser plasma spraying
JPH0739859B2 (ja) 1990-11-29 1995-05-01 シーメンス アクチエンゲゼルシヤフト 支持構造のセラミック製熱遮蔽体
US5216886A (en) * 1991-08-14 1993-06-08 The United States Of America As Represented By The Secretary Of The Air Force Segmented cell wall liner for a combustion chamber
RU2088764C1 (ru) 1993-12-02 1997-08-27 Яков Петрович Гохштейн Турбинная лопатка
WO1996004511A1 (fr) * 1994-08-05 1996-02-15 Yanovsky, Ilya Yakovlevich Chambre a combustion a tube a feu en ceramique
US6190124B1 (en) 1997-11-26 2001-02-20 United Technologies Corporation Columnar zirconium oxide abrasive coating for a gas turbine engine seal system
EP1247941A1 (fr) 2001-04-03 2002-10-09 Siemens Aktiengesellschaft Aube de turbine à gaz
US6846574B2 (en) * 2001-05-16 2005-01-25 Siemens Westinghouse Power Corporation Honeycomb structure thermal barrier coating
US6703137B2 (en) 2001-08-02 2004-03-09 Siemens Westinghouse Power Corporation Segmented thermal barrier coating and method of manufacturing the same
CN2625695Y (zh) * 2003-07-23 2004-07-14 刘堪金 一种铠装的耐火隔热管
DE102004001722A1 (de) * 2004-01-13 2005-08-04 Mtu Aero Engines Gmbh Turbomaschinenschaufel und Verfahren zur Herstellung einer Schaufelspitzenpanzerung an Turbomaschinenschaufeln
EP1715249A1 (fr) * 2005-04-19 2006-10-25 Siemens Aktiengesellschaft Elément de bouclier thermique et chambre de combustion avec un bouclier thermique
EP1865258A1 (fr) * 2006-06-06 2007-12-12 Siemens Aktiengesellschaft Composant blindé d'un moteur et turbine à gaz

Also Published As

Publication number Publication date
HUE029774T2 (en) 2017-04-28
CN101889173B (zh) 2015-05-13
CN101889173A (zh) 2010-11-17
RU2492327C2 (ru) 2013-09-10
US9702561B2 (en) 2017-07-11
WO2009071395A1 (fr) 2009-06-11
US20100269510A1 (en) 2010-10-28
RU2010127346A (ru) 2012-01-10
EP2215405A1 (fr) 2010-08-11
EP2068082A1 (fr) 2009-06-10

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