EP1865258A1 - Composant blindé d'un moteur et turbine à gaz - Google Patents

Composant blindé d'un moteur et turbine à gaz Download PDF

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Publication number
EP1865258A1
EP1865258A1 EP06011629A EP06011629A EP1865258A1 EP 1865258 A1 EP1865258 A1 EP 1865258A1 EP 06011629 A EP06011629 A EP 06011629A EP 06011629 A EP06011629 A EP 06011629A EP 1865258 A1 EP1865258 A1 EP 1865258A1
Authority
EP
European Patent Office
Prior art keywords
armor
machine
machine component
gas turbine
segments
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Withdrawn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
EP06011629A
Other languages
German (de)
English (en)
Inventor
Birgit Grüger
Martin Stapper
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 EP06011629A priority Critical patent/EP1865258A1/fr
Priority to CN2007800212465A priority patent/CN101473171B/zh
Priority to AT07728485T priority patent/ATE451581T1/de
Priority to EP07728485A priority patent/EP2024684B1/fr
Priority to DE502007002275T priority patent/DE502007002275D1/de
Priority to RU2008152379/06A priority patent/RU2451241C2/ru
Priority to PCT/EP2007/054029 priority patent/WO2007141091A1/fr
Priority to US12/227,912 priority patent/US8091366B2/en
Publication of EP1865258A1 publication Critical patent/EP1865258A1/fr
Withdrawn legal-status Critical Current

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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
    • F23R3/005—Combined with pressure or heat exchangers
    • 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
    • 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
    • F23R3/002—Wall structures
    • 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

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 compared to the base material. It further relates to a gas turbine with a number of machine components of this type.
  • 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 adjacent components being coated with a protective coating, also referred to as armor ,
  • a protective coating also referred to as armor
  • Such an armor can be formed from an application material which has a greater mechanical hardness compared to the base material of the respective component, so that a contact-related wear can already be reduced by such a suitable choice of material.
  • the invention is therefore based on the object to provide a machine component of the type mentioned above, which is also particularly suitable for use in a thermally comparatively highly loaded area of a working machine. Furthermore, a gas turbine with a number of such machine components is to be specified.
  • this object is achieved according to the invention in that the armor is segmented and formed by a number of armor segments.
  • the invention is based on the consideration that the machine component should be provided with a suitable armor for a fundamental usability while maintaining wear-resistant working conditions.
  • the lateral extent of the armor should be kept particularly low.
  • individual zones of the armor should be executed decoupled from one another, in order thus to allow sufficient resilience to thermal deformation and the like. For this, the armor should be executed segment by segment.
  • 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 armor segments may be applied to an outer surface of the body so that the resulting contour has substantially a plurality of bulges provided by the armor segments on the surface of the rail component.
  • the armor segments are advantageously introduced or embedded respectively in associated recesses in the body.
  • an overall surface of the machine component that is virtually flat overall is advantageously achievable overall, with the outer surface of the armor segments in particular and the outer surface of the webs of the base body extending between the armor segments forming a continuous surface.
  • machine components of the type mentioned are used in a gas turbine, in particular as a flame tube of a combustion chamber, as a mixing housing of a burner and / or as an inner housing of a combustion chamber.
  • components or machine components positioned adjacent to one another can also be embodied in such an armored manner, wherein advantageously the armored subregion of the surface of a first machine component is arranged adjacent to the armored subregion of the surface of a second machine component.
  • the application material of the first machine component has a different hardness than the application material of the second machine component.
  • the advantages achieved by the invention are in particular that by the segmented design of the armor of the machine component even with only small tolerance ranges attaching the armor on the body is made possible in the first place, just with regard to the segmented execution of the armor distortion of the body can be largely avoided due to the high operating temperatures during build-up welding.
  • the segmented design of the armor also avoids cracking when applying the armor, which could occur with continuous welding of the armor.
  • a subsequent bending of the component is made possible without the order material would be too stressed.
  • deformations and joint welds are comparatively easy to perform during assembly and in operation, without any critical effects on the component to be feared.
  • the surface of the machine component can be homogenized in retrospect, with a possible supernatant after the deposition welding can also be subsequently removed. In this case, compliance with externally predetermined dimensions can be ensured in particular with adapted component geometry.
  • the segmented application of the armor also reduces the load on the component during manufacture, assembly and operation.
  • 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 or a working machine (not shown).
  • 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 annular in shape to form Guide vanes are attached to an inner housing 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 that forms the outer boundary of a hot gas channel for the working medium M flowing through the turbine 6.
  • 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.
  • 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.
  • each of the combustion chamber 4 is equipped with a so-called flame tube 30 in its inflow region, to which a number of unspecified supply lines for media such as fuel and combustion air are connected whose the combustion of the fuel takes place.
  • a number of unspecified supply lines for media such as fuel and combustion air are connected whose the combustion of the fuel takes place.
  • the flame tube 30 is connected on the output side to a mixing housing 34 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 a reliable media flow guidance of the flame tube 30 is ensured in the inner housing 36 of the combustion chamber 4.
  • the respectively nested tube ends are positioned as possible contact-free from each other while maintaining the predetermined dimensions and tolerances, so that wear due to in contact with each other components and rubbing components is avoided 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.
  • regular inspection and replacement of these components is required as part of maintenance and inspection work.
  • each of the machine components flame tube 30, transition piece 34 and inner housing 36 is constructed from a base body 40 made of base material, which in an illustrated in each of FIGS 3 to 6 portion of its surface with an armor 42nd is provided from a job material.
  • the application material is chosen such that it has a greater hardness 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 comprises a plurality of armor segments 44, wherein the dimensioning with regard to the dimensioning of the actual machine component and the materials used is chosen such that the laterally limited extent the respective armor segments 44 too great impairment of the body 40 by different thermal Expansion behavior and the like is avoided.
  • the armor segments 44 are each introduced into assigned recesses in the main 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 shown in Figures 3 to 6, carried out such that the outer surface of the armor segments 44 with the outer surface of extending between the outer armor segments 44 webs 46 of Base body 40 form a continuous and thus planar 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.
  • FIG. 4 shows that a bent cooling air ring 50 can also 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. Due to the shape of the wells, also referred to as pockets, in which the armor segments 44 are arranged, the desired geometry of the cooling air ring 50 can be maintained. Nevertheless, an almost even surface and a smooth transition to the base body 40 is created even when using the armor segments 44. This ensures increased wear reduction and improved bonding between the materials used.
  • the transition piece 34 and the flame tube 30 of the gas turbine 1 are embodied in their overlapping region as such armored machine components.
  • Armor 42 of these machine components are provided in each case on the facing surface segments.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Laser Beam Processing (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
  • Feeding, Discharge, Calcimining, Fusing, And Gas-Generation Devices (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP06011629A 2006-06-06 2006-06-06 Composant blindé d'un moteur et turbine à gaz Withdrawn EP1865258A1 (fr)

Priority Applications (8)

Application Number Priority Date Filing Date Title
EP06011629A EP1865258A1 (fr) 2006-06-06 2006-06-06 Composant blindé d'un moteur et turbine à gaz
CN2007800212465A CN101473171B (zh) 2006-06-06 2007-04-25 设有护甲的机器组件和燃气轮机
AT07728485T ATE451581T1 (de) 2006-06-06 2007-04-25 Gasturbine mit gepanzerten maschinenkomponenten
EP07728485A EP2024684B1 (fr) 2006-06-06 2007-04-25 Turbine à gaz avec composants de machine blindé
DE502007002275T DE502007002275D1 (de) 2006-06-06 2007-04-25 Gasturbine mit gepanzerten maschinenkomponenten
RU2008152379/06A RU2451241C2 (ru) 2006-06-06 2007-04-25 Бронированный машинный компонент и газовая турбина
PCT/EP2007/054029 WO2007141091A1 (fr) 2006-06-06 2007-04-25 Composant de machine blindé et turbine à gaz
US12/227,912 US8091366B2 (en) 2006-06-06 2007-04-25 Armor-plated machine components and gas turbines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06011629A EP1865258A1 (fr) 2006-06-06 2006-06-06 Composant blindé d'un moteur et turbine à gaz

Publications (1)

Publication Number Publication Date
EP1865258A1 true EP1865258A1 (fr) 2007-12-12

Family

ID=37560775

Family Applications (2)

Application Number Title Priority Date Filing Date
EP06011629A Withdrawn EP1865258A1 (fr) 2006-06-06 2006-06-06 Composant blindé d'un moteur et turbine à gaz
EP07728485A Active EP2024684B1 (fr) 2006-06-06 2007-04-25 Turbine à gaz avec composants de machine blindé

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP07728485A Active EP2024684B1 (fr) 2006-06-06 2007-04-25 Turbine à gaz avec composants de machine blindé

Country Status (7)

Country Link
US (1) US8091366B2 (fr)
EP (2) EP1865258A1 (fr)
CN (1) CN101473171B (fr)
AT (1) ATE451581T1 (fr)
DE (1) DE502007002275D1 (fr)
RU (1) RU2451241C2 (fr)
WO (1) WO2007141091A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2068082A1 (fr) * 2007-12-04 2009-06-10 Siemens Aktiengesellschaft Composants de machines et turbine à gaz

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2899464B1 (fr) * 2014-01-22 2017-01-11 Siemens Aktiengesellschaft Turbine à gaz avec une chambre de combustion de type silo
DE102017207392A1 (de) * 2017-05-03 2018-11-08 Siemens Aktiengesellschaft Silobrennkammer und Verfahren zum Umrüsten einer solchen

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1450894A (en) * 1972-11-01 1976-09-29 Lucas Industries Ltd Flame tubes
GB2061397A (en) * 1979-10-12 1981-05-13 Gen Electric Metal-ceramic turbine shroud
EP0181255A1 (fr) * 1984-10-30 1986-05-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Procédé de fabrication d'un anneau de turbine en céramique intégré à un support métallique annulaire
EP1283278A2 (fr) * 2001-08-02 2003-02-12 Siemens Westinghouse Power Corporation Revêtement de barrière thermique segmenté et procédé pour sa fabrication
DE10326541A1 (de) * 2003-06-12 2005-01-05 Mtu Aero Engines Gmbh Verfahren zur Schaufelspitzenpanzerung der Laufschaufeln eines Gasturbinentriebwerkes und Vorrichtung zur Durchführung des Verfahrens
DE102004001722A1 (de) * 2004-01-13 2005-08-04 Mtu Aero Engines Gmbh Turbomaschinenschaufel und Verfahren zur Herstellung einer Schaufelspitzenpanzerung an Turbomaschinenschaufeln

Family Cites Families (11)

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Publication number Priority date Publication date Assignee Title
US3476283A (en) * 1968-07-05 1969-11-04 Universal Oil Prod Co Internally insulated and lined pressure vessel
JPS55107310U (fr) * 1979-01-23 1980-07-26
US4688310A (en) * 1983-12-19 1987-08-25 General Electric Company Fabricated liner article and method
EP0224817B1 (fr) * 1985-12-02 1989-07-12 Siemens Aktiengesellschaft Ecran de protection contre la chaleur pour éléments structuraux d'une turbine à gaz
US4706453A (en) * 1986-11-12 1987-11-17 General Motors Corporation Support and seal assembly
US5024058A (en) * 1989-12-08 1991-06-18 Sundstrand Corporation Hot gas generator
UA27772C2 (uk) * 1990-11-29 2000-10-16 Сіменс Аг Теплозахисний екран на несучій структурі
DE4238369C2 (de) * 1992-11-13 1996-09-26 Mtu Muenchen Gmbh Bauteil aus einem metallischen Grundsubstrat mit keramischer Beschichtung
RU2088764C1 (ru) * 1993-12-02 1997-08-27 Яков Петрович Гохштейн Турбинная лопатка
US6190124B1 (en) * 1997-11-26 2001-02-20 United Technologies Corporation Columnar zirconium oxide abrasive coating for a gas turbine engine seal system
JP3801452B2 (ja) * 2001-02-28 2006-07-26 三菱重工業株式会社 耐摩耗性コーティング及びその施工方法

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1450894A (en) * 1972-11-01 1976-09-29 Lucas Industries Ltd Flame tubes
GB2061397A (en) * 1979-10-12 1981-05-13 Gen Electric Metal-ceramic turbine shroud
EP0181255A1 (fr) * 1984-10-30 1986-05-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Procédé de fabrication d'un anneau de turbine en céramique intégré à un support métallique annulaire
EP1283278A2 (fr) * 2001-08-02 2003-02-12 Siemens Westinghouse Power Corporation Revêtement de barrière thermique segmenté et procédé pour sa fabrication
DE10326541A1 (de) * 2003-06-12 2005-01-05 Mtu Aero Engines Gmbh Verfahren zur Schaufelspitzenpanzerung der Laufschaufeln eines Gasturbinentriebwerkes und Vorrichtung zur Durchführung des Verfahrens
DE102004001722A1 (de) * 2004-01-13 2005-08-04 Mtu Aero Engines Gmbh Turbomaschinenschaufel und Verfahren zur Herstellung einer Schaufelspitzenpanzerung an Turbomaschinenschaufeln

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2068082A1 (fr) * 2007-12-04 2009-06-10 Siemens Aktiengesellschaft Composants de machines et turbine à gaz
WO2009071395A1 (fr) * 2007-12-04 2009-06-11 Siemens Aktiengesellschaft Élément de machine et turbine à gaz
US9702561B2 (en) 2007-12-04 2017-07-11 Siemens Aktiengesellschaft Machine component and gas turbine

Also Published As

Publication number Publication date
EP2024684B1 (fr) 2009-12-09
ATE451581T1 (de) 2009-12-15
CN101473171B (zh) 2011-04-06
WO2007141091A1 (fr) 2007-12-13
US20090180873A1 (en) 2009-07-16
DE502007002275D1 (de) 2010-01-21
EP2024684A1 (fr) 2009-02-18
CN101473171A (zh) 2009-07-01
US8091366B2 (en) 2012-01-10
RU2451241C2 (ru) 2012-05-20
RU2008152379A (ru) 2010-07-20

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