EP2024684A1 - Gepanzerte maschinenkomponente und gasturbine - Google Patents
Gepanzerte maschinenkomponente und gasturbineInfo
- Publication number
- EP2024684A1 EP2024684A1 EP07728485A EP07728485A EP2024684A1 EP 2024684 A1 EP2024684 A1 EP 2024684A1 EP 07728485 A EP07728485 A EP 07728485A EP 07728485 A EP07728485 A EP 07728485A EP 2024684 A1 EP2024684 A1 EP 2024684A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- armor
- machine
- machine component
- segments
- base body
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000000463 material Substances 0.000 claims abstract description 32
- 238000003466 welding Methods 0.000 claims abstract description 8
- 238000007747 plating Methods 0.000 claims abstract 7
- 238000002485 combustion reaction Methods 0.000 claims description 20
- 238000002156 mixing Methods 0.000 claims description 4
- 230000008021 deposition Effects 0.000 claims description 2
- 235000019589 hardness Nutrition 0.000 description 8
- 230000007704 transition Effects 0.000 description 8
- 238000001816 cooling Methods 0.000 description 6
- 239000000446 fuel Substances 0.000 description 6
- 239000011248 coating agent Substances 0.000 description 4
- 238000000576 coating method Methods 0.000 description 4
- 238000005253 cladding Methods 0.000 description 3
- 238000007689 inspection Methods 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 230000006735 deficit Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008646 thermal stress Effects 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 235000008694 Humulus lupulus Nutrition 0.000 description 1
- 244000025221 Humulus lupulus Species 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- KXKPYJOVDUMHGS-OSRGNVMNSA-N chondroitin sulfate Chemical compound CC(=O)N[C@H]1[C@H](O)O[C@H](OS(O)(=O)=O)[C@H](O)[C@@H]1O[C@H]1[C@H](O)[C@@H](O)[C@H](O)[C@@H](C(O)=O)O1 KXKPYJOVDUMHGS-OSRGNVMNSA-N 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000000227 grinding Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 239000000047 product Substances 0.000 description 1
- 239000011253 protective coating Substances 0.000 description 1
- 108090000623 proteins and genes Proteins 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 239000006228 supernatant Substances 0.000 description 1
- 238000007514 turning Methods 0.000 description 1
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 hardness greater than the Grundmate ⁇ rial. 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 combusted in a combustion chamber, fed by an air compressor, compressed air is ⁇ leads.
- 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 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 avoid contact between adjacent machine components or components. To minimize parts with each other, so as to keep wear of the affected components particularly low. Nevertheless, it may in the operation of the turbine, for example, ⁇ follow thermal expansions or due to operationally caused vibrations occurring or the like, coming back to actually unwanted contact between such components, so that a certain amount of wear of such components occurs. For example, as derar ⁇ term machine components in the combustion chamber of the gas turbine usually a so-called flame tube, a
- the machine components can be made in so-called armored embodiment, the regions most affected by the expected wear or the expected contacts with neighboring components tion with as Panze ⁇ protective coating designated are coated.
- Such armor may consist of a coating material ge ⁇ forms its having a greater than the basic material of the component JE - thermal hardness so that a contact occurring due to wear can be reduced by such a suitable choice of material already.
- a Maschi nenkomponente ⁇ indicate the type mentioned above, which is particularly suitable for use in a thermally relatively highly belaste- th area of a work machine. Furthermore, a gas turbine with a number of such machine components is to be specified.
- segmented armor leads out ⁇ and is formed from a number of cladding segments.
- the invention is based on the consideration that the machine-component should be provided for a fundamental applicability un ⁇ ter compliance with low-wear working conditions with a suitable armor.
- 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.
- the armor should be executed segment by segment.
- the armor segments may be applied by suitable techniques on the base 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 base body and thus a high stability of the machine component as a whole he ⁇ is enough.
- the armor segments can be applied to an outer surface of the base body, so that the resulting entste ⁇ rising contour has a plurality of given by the armor segments bulges on the surface of the rail component substantially.
- the armor segments are vorteilhaf ⁇ tate introduced or embedded in associated recesses in the body.
- a virtually even overall surface of the machine component can advantageously be achieved 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.
- come machine components of the said type in a gas turbine in particular a flame tube of a combustion chamber as a mixing housing a burner and / or as in ⁇ nengeratiuse a combustor used.
- a flame tube of a combustion chamber as a mixing housing a burner and / or as in ⁇ nengeratiuse a combustor used.
- the reinforced portion advantageously the upper ⁇ surface of a first machine component adjacent to Gepan ⁇ zerten portion of the surface of a second machine component is arranged.
- the coating material of the first Maschi ⁇ nenkomponente a different hardness than the coating material of the second machine component.
- the advantages achieved by the invention are in particular that the segmented design of the Panze ⁇ tion of the machine component even with only small tolerance ranges attaching the armor on the body in the first place is possible, especially with regard to the segmented execution of the armor a distortion of the body due to the high operating temperatures during buildup welding can be largely avoided.
- the segmented design of the armor also crack ⁇ education in the application of armor is avoided, 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 connection welds during installation and operation are comparatively easy to carry out, 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.
- the compliance with externally-giving ⁇ ner dimensions can be ensured particularly for matched component geometry.
- the segmented application of the armor also reduces the load on the component during manufacture, assembly and operation.
- FIG 2 shows a section through a combustion chamber in gas ⁇ turbines according to FIG 1,
- the gas turbine 1 comprises a compressor 2 for combustion air, a combustion chamber 4 and a turbine 6 to drive the compressor 2 and a Gene ⁇ rators not shown or a work machine.
- the Turbi ⁇ are ne 6 and the compressor 2 arranged on a common, also referred to as the turbine rotor turbine shaft 8, is connected to the generator or the driven machine, and which is mounted rotatably about its central axis.
- the combustion chamber 4 is equipped with a number of burners 10 for 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 runners 12 are arranged in a ring shape on the turbine shaft 8 and thus form a number of blade rows.
- the turbine 6 comprises a number of fixed Leit ⁇ blades 14, which also wreath-shaped 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 tur ⁇ bine 6 flowing through the working medium M.
- the vanes 14, however, serve to flow 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 plate ⁇ form 18 is a thermally comparatively heavily belas ⁇ tetes component that forms the outer boundary of a hot gas channel for the turbine 6 flowing through the working medium M.
- 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 ⁇ rings 21 is also the hot, exposed through the turbine 6 ⁇ flowing working medium M, and in the radial direction from the outer end 22 of the opposite him running blades 12 of a rotor blade row by a gap 24th
- each of the combustion chamber 4 is in its inflow area to which a number of unspecified supply lines for media, such as fuel and combustion air is ⁇ included are equipped in its interior with a so-called flame tube 30 within which the combustion of the fuel takes place.
- a so-called flame tube 30 within which 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 réellegenosu ⁇ se 36 are connected in the nature of nested tubes with ⁇ each other, so that a reliable media flow management is ensured by the flame tube 30 in the inner housing 36 of the combustion chamber 4.
- the respectively inserted tube ends are thereby positio ⁇ niert as possible contact-free from each other in compliance with the predetermined dimensions and tolerances, so that wear due to coming in contact with each other components and rubbing together components as possible avoided.
- it can drive caused during operation of the gas turbine 1, a constantly recurring ⁇ contact of these components do not avoid each other, so that in any case likely to be a residual wear ⁇ . 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 of a base body 40 made of base material, which in an in each case in Figures 3 to 6 Darge ⁇ presented 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 he he ⁇ 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 is executed segmented the respective machine component.
- the armor 42 comprises a plurality of armor segments 44, wherein the dimensioning with respect 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 large impairment ⁇ tion of the base body 40 through different thermal expansion behavior and the like is avoided.
- FIG 3 which are approximately Panze ⁇ segments 44 each in associated recesses in the base body 40 is introduced.
- the recesses may have been introduced by suitable machining methods, such as by milling, turning or grinding.
- the dimensions can in principle be carried out in such a way here that the cladding segments 44 are applied to a planar surface of the base body 40 and corresponding ⁇ speaking their thickness corresponding recesses are formed 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 Panzerssegmen ⁇ th 44 which are incorporated into corresponding recesses of the cooling air ring 50 forming body 40.
- cooling air channels 52 are additionally provided, which are formed by corresponding holes.
- FIG 5 it is shown that components such as armored machines ⁇ particular, the transition piece 34 and the flame tube 30 of the gas turbine 1 in their overlapping area are executed.
- Armor 42 of these machine components are provided in each case on the facing surface segments.
- the material for the armor 42 of the flame tube 30 of ge ⁇ ringerer hardness to choose as the material for the Panze ⁇ tion 42 of the transition piece 34th
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)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Feeding, Discharge, Calcimining, Fusing, And Gas-Generation Devices (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Description
Claims
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP07728485A EP2024684B1 (de) | 2006-06-06 | 2007-04-25 | Gasturbine mit gepanzerten maschinenkomponenten |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP06011629A EP1865258A1 (de) | 2006-06-06 | 2006-06-06 | Gepanzerte Maschinenkomponente und Gasturbine |
EP07728485A EP2024684B1 (de) | 2006-06-06 | 2007-04-25 | Gasturbine mit gepanzerten maschinenkomponenten |
PCT/EP2007/054029 WO2007141091A1 (de) | 2006-06-06 | 2007-04-25 | Gepanzerte maschinenkomponente und gasturbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2024684A1 true EP2024684A1 (de) | 2009-02-18 |
EP2024684B1 EP2024684B1 (de) | 2009-12-09 |
Family
ID=37560775
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP06011629A Withdrawn EP1865258A1 (de) | 2006-06-06 | 2006-06-06 | Gepanzerte Maschinenkomponente und Gasturbine |
EP07728485A Active EP2024684B1 (de) | 2006-06-06 | 2007-04-25 | Gasturbine mit gepanzerten maschinenkomponenten |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP06011629A Withdrawn EP1865258A1 (de) | 2006-06-06 | 2006-06-06 | Gepanzerte Maschinenkomponente und Gasturbine |
Country Status (7)
Country | Link |
---|---|
US (1) | US8091366B2 (de) |
EP (2) | EP1865258A1 (de) |
CN (1) | CN101473171B (de) |
AT (1) | ATE451581T1 (de) |
DE (1) | DE502007002275D1 (de) |
RU (1) | RU2451241C2 (de) |
WO (1) | WO2007141091A1 (de) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2068082A1 (de) * | 2007-12-04 | 2009-06-10 | Siemens Aktiengesellschaft | Maschinenkomponente und Gasturbine |
EP2899464B1 (de) * | 2014-01-22 | 2017-01-11 | Siemens Aktiengesellschaft | Silobrennkammer für eine Gasturbine |
DE102017207392A1 (de) * | 2017-05-03 | 2018-11-08 | Siemens Aktiengesellschaft | Silobrennkammer und Verfahren zum Umrüsten einer solchen |
Family Cites Families (17)
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 |
GB1450894A (en) * | 1972-11-01 | 1976-09-29 | Lucas Industries Ltd | Flame tubes |
JPS55107310U (de) * | 1979-01-23 | 1980-07-26 | ||
US4289447A (en) * | 1979-10-12 | 1981-09-15 | General Electric Company | Metal-ceramic turbine shroud and method of making the same |
US4688310A (en) * | 1983-12-19 | 1987-08-25 | General Electric Company | Fabricated liner article and method |
FR2572394B1 (fr) * | 1984-10-30 | 1986-12-19 | Snecma | Procede de fabrication d'un anneau de turbine en ceramique integre a un support metallique annulaire |
DE3664374D1 (en) * | 1985-12-02 | 1989-08-17 | Siemens Ag | Heat shield arrangement, especially for the structural components of a gas turbine plant |
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 |
EP0558540B1 (de) * | 1990-11-29 | 1995-06-14 | Siemens Aktiengesellschaft | Keramischer hitzeschild an einer tragstruktur |
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 |
US6703137B2 (en) * | 2001-08-02 | 2004-03-09 | Siemens Westinghouse Power Corporation | Segmented thermal barrier coating and method of manufacturing the same |
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 |
-
2006
- 2006-06-06 EP EP06011629A patent/EP1865258A1/de not_active Withdrawn
-
2007
- 2007-04-25 DE DE502007002275T patent/DE502007002275D1/de active Active
- 2007-04-25 RU RU2008152379/06A patent/RU2451241C2/ru active
- 2007-04-25 EP EP07728485A patent/EP2024684B1/de active Active
- 2007-04-25 AT AT07728485T patent/ATE451581T1/de active
- 2007-04-25 US US12/227,912 patent/US8091366B2/en active Active
- 2007-04-25 WO PCT/EP2007/054029 patent/WO2007141091A1/de active Application Filing
- 2007-04-25 CN CN2007800212465A patent/CN101473171B/zh active Active
Non-Patent Citations (1)
Title |
---|
See references of WO2007141091A1 * |
Also Published As
Publication number | Publication date |
---|---|
CN101473171B (zh) | 2011-04-06 |
US8091366B2 (en) | 2012-01-10 |
ATE451581T1 (de) | 2009-12-15 |
EP2024684B1 (de) | 2009-12-09 |
WO2007141091A1 (de) | 2007-12-13 |
CN101473171A (zh) | 2009-07-01 |
EP1865258A1 (de) | 2007-12-12 |
US20090180873A1 (en) | 2009-07-16 |
DE502007002275D1 (de) | 2010-01-21 |
RU2008152379A (ru) | 2010-07-20 |
RU2451241C2 (ru) | 2012-05-20 |
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