Classifications

• • G—PHYSICS
  • G01—MEASURING; TESTING
  • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
  • G01B11/00—Measuring arrangements characterised by the use of optical techniques
  • G01B11/02—Measuring arrangements characterised by the use of optical techniques for measuring length, width or thickness
  • G01B11/06—Measuring arrangements characterised by the use of optical techniques for measuring length, width or thickness for measuring thickness ; e.g. of sheet material
• • G—PHYSICS
  • G01—MEASURING; TESTING
  • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
  • G01B11/00—Measuring arrangements characterised by the use of optical techniques
  • G01B11/02—Measuring arrangements characterised by the use of optical techniques for measuring length, width or thickness
  • G01B11/06—Measuring arrangements characterised by the use of optical techniques for measuring length, width or thickness for measuring thickness ; e.g. of sheet material
  • G01B11/0616—Measuring arrangements characterised by the use of optical techniques for measuring length, width or thickness for measuring thickness ; e.g. of sheet material of coating
• • G—PHYSICS
  • G01—MEASURING; TESTING
  • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
  • G01B11/00—Measuring arrangements characterised by the use of optical techniques
  • G01B11/02—Measuring arrangements characterised by the use of optical techniques for measuring length, width or thickness
  • G01B11/06—Measuring arrangements characterised by the use of optical techniques for measuring length, width or thickness for measuring thickness ; e.g. of sheet material
  • G01B11/0616—Measuring arrangements characterised by the use of optical techniques for measuring length, width or thickness for measuring thickness ; e.g. of sheet material of coating
  • G01B11/0683—Measuring arrangements characterised by the use of optical techniques for measuring length, width or thickness for measuring thickness ; e.g. of sheet material of coating measurement during deposition or removal of the layer

Definitions

• the invention relates to a method and a device for measuring layer thickness by means of laser triangulation.
• a destructive test precludes the subsequent use of the component and can only be used for parameter optimization.
• the object is achieved by a method according to claim 1 and a device according to claim 1 or 9.
• FIG. 3 shows a schematic representation of the sequence of the method
• FIG. 4 positions of the layer thickness measurement
• FIG. 5 shows a gas turbine
• FIG. 6 shows a turbine blade
• Figure 7 is a combustion chamber
• Figure 8 is a list of superalloys.
• FIG. 1 shows a turbine blade 120, 130 as a component 1 used as an example.
• the turbine blade or vane 120, 130 may be a new part or a ent harshetes component 120, 130 (from the refurbishment), which was already in use, and for example, has a wall thickness ⁇ dilution by the stripping process.
• the blade 120, 130 is measured at each position 13 ', 13' '(FIG. 4) at which a review of the layer thickness seems sensible (I in FIG. 3). , This can be done locally at one or more points or globally over the entire area to be coated.
• the measurement by means of laser triangulation can preferably also take place during the coating (II).
• the data obtained therefrom before and after or during the coating can be compared with one another by means of a computer (IV in FIG. 3) and thus the layer thickness can be determined at each desired position (FIG. 4) and preferably compared with desired values.
• Layer thickness determined at each desired position 13 ', 13''( Figure 4) (V in Figure 3).
• the layer thickness can be produced for metallic and ceramic Schich ⁇ th and by means of APS, VPS, PVP, CVD ⁇ be true.
• the measurements are carried out before and after in the same holder, preferably without installation and removal of the component 120, 130.
• the measurement is carried out only before and after the coating, because the technical structure is somewhat simpler.
• the component is a large surface area, in the case of a turbine blade 120, 130 the turbine blade and the blade platform ⁇ scanned over a large area as set, different layer thicknesses particularly in ge ⁇ curved surfaces.
• a reference point on the component 1, 120, 139, 155 in particular in the case of a blade 120, 130, this is preferably a point at the point which does not distort itself, such as, for example, FIG . B. on the blade root - because it is very solid - or on the holder, the delay of the component 1, 120, 130, 155, in particular of the much thinner part of the
• Coating material application means in general: local, like a blade of a turbine blade coating local loading on the blade or complete Beschich ⁇ th, but also welding application method.
• FIG. 5 shows by way of example a gas turbine 100 in a longitudinal partial section.
• the gas turbine 100 has a rotatably mounted about a rotational axis 102 ⁇ rotor 103 with a shaft, which is also referred to as the turbine rotor.
• a compressor 105 for example, a torus-like
• Combustion chamber 110 in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
• the annular combustion chamber 110 communicates with an annular annular hot gas channel 111, for example.
• annular annular hot gas channel 111 for example.
• turbine stages 112 connected in series form the turbine 108.
• Each turbine stage 112 is formed, for example, from two blade rings . As seen in the direction of flow of a working medium 113, in the hot gas channel 111 of a row of guide vanes 115, a series 125 formed of rotor blades 120 follows.
• the guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the moving blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example.
• Coupled to the rotor 103 is a generator or work machine (not shown).
• air 135 is sucked by the compressor 105 through the intake housing and ver ⁇ seals.
• the 105 ⁇ be compressed air provided at the turbine end of the compressor is ge ⁇ leads to the burners 107, where it is mixed with a fuel.
• the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
• the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
• the working medium 113 expands in a pulse-transmitting manner so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
• the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
• the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the flow direction of the working medium 113, are subjected to the greatest thermal stress in addition to the heat shield elements lining the annular combustion chamber 110.
• substrates of the components may have a directional structure, i. they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
• the components in particular for the turbine blade ⁇ 120, 130 and components of the combustion chamber 110, for example, iron-, nickel- or cobalt-based superalloys are used.
• Such superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949.
• the guide vane 130 has an inner housing 138 of the turbine 108 facing guide vane root (not Darge here provides ⁇ ) and a side opposite the guide-blade root vane root.
• the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.
• FIG. 6 shows a perspective view of a rotor 120 or guide vane 130 of a turbomachine that extends along a longitudinal axis 121.
• the turbomachine may be a gas turbine of an aircraft or a power plant for electricity generation, a steam turbine or a compressor.
• the blade 120, 130 has along the longitudinal axis 121 to each other, a securing region 400, an thereto adjacent blade platform 403 and an airfoil 406 and a blade tip 415.
• the blade 130 may have at its blade tip ⁇ 415 another platform (not shown).
• a blade root 183 is formed, which serves for attachment of the blades 120, 130 to a shaft or a disc (not shown).
• the blade root 183 is, for example, as a hammerhead out staltet ⁇ .
• Other designs as Christmas tree or Schwalbenschwanzfuß are possible.
• the blade 120, 130 has for a medium which flows past the scene ⁇ felblatt 406, a leading edge 409 and a trailing edge 412.
• Such superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949.
• the blade 120, 130 can be made by a casting process, also by directional solidification, by a forging process, by a milling process or combinations thereof.
• Workpieces with a monocrystalline structure or structures are used as components for machines which are exposed to high mechanical, thermal and / or chemical stresses during operation.
• Stem-crystal structures which probably have longitudinally extending grain boundaries, but no transverse grain boundaries. These second-mentioned crystalline structures are also known as directionally solidified structures.
• M is at least one element of the group iron (Fe), cobalt (Co),
• Nickel (Ni) is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare earths, or hafnium (Hf)).
• Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1.
• the density is preferably 95% of the theoretical
• the layer composition comprises Co-30Ni-28Cr-8A1-0, 6Y-0, 7Si or Co-28Ni-24Cr-10Al-0, 6Y.
• nickel-based protective layers such as Ni-10Cr-12Al-0.6Y-3Re or Ni-12Co-21Cr-IIAl-O, 4Y-2Re or Ni-25Co-17Cr-10A1-0, 4Y-1 are also preferably used , 5Re.
• thermal barrier coating which is preferably the outermost layer, and consists for example of Zr0 2 , Y2Ü3-Zr02, ie it is not, partially ⁇ or fully stabilized by yttria
• the thermal barrier coating covers the entire MCrAlX layer.
• Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
• the heat insulating layer can ⁇ ner to have better thermal shock resistance porous, micro- or macro-cracked pERSonal.
• the thermal barrier coating is therefore preferably more porous than the
• the blade 120, 130 may be hollow or solid. If the blade 120, 130 is to be cooled, it is hollow and also has, if necessary, film cooling holes 418 (indicated by dashed lines) on.
• FIG. 7 shows a combustion chamber 110 of the gas turbine 100.
• the combustion chamber 110 is configured, for example, as so-called an annular combustion chamber, in which a plurality of in the circumferential direction about an axis of rotation 102 arranged burners 107 open into a common combustion chamber space 154 and generate flames 156th
• the combustion chamber 110 is configured in its entirety as an annular structure, which is positioned around the axis of rotation 102 around.
• the combustion chamber 110 is designed for a comparatively high temperature of the working medium M of about 1000 ° C to 1600 ° C.
• the combustion chamber wall 153 is provided on its side facing the working medium M facing side with a formed from heat shield elements 155. liner. Due to the high temperatures inside the combustion chamber
• the 110 may also be provided for the heat shield elements 155 and for their holding elements, a cooling system.
• the heat shield elements 155 are then, for example, hollow and possibly still have cooling holes (not shown) which open into the combustion chamber space 154.
• Each heat shield element 155 made of an alloy is equipped on the working fluid side with a particularly heat-resistant protective layer (MCrAlX layer and / or ceramic coating) or is made of high-temperature-resistant material (solid ceramic blocks).
• M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or
• a ceramic Wär ⁇ medämm Anlagen be present and consists for example of ZrÜ2, Y203 ⁇ Zr02, ie it is not, partially or fully ⁇ dig stabilized by yttrium and / or calcium oxide and / or magnesium oxide.
• Suitable coating processes such as electron beam evaporation (EB-PVD), produce stalk-shaped grains in the thermal barrier coating.
• Other coating methods are conceivable, for example atmospheric plasma spraying (APS), LPPS, VPS or CVD.
• APS atmospheric plasma spraying
• LPPS LPPS
• VPS VPS
• CVD chemical vapor deposition
• the heat insulation layer may have ⁇ porous, micro- or macro-cracked compatible grains for better thermal shock resistance.
• Reprocessing means that turbines ⁇ blades 120, 130, heat shield elements have to be removed from 155, after ⁇ A set of protective layers (for example by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products.
• cracks in the turbine blade 120, 130 or the heat shield element 155 are also repaired. This is followed by a re-coating of the turbine blades 120, 130, heat shield elements 155 and a renewed use of the turbine blades 120, 130 or the heat shield elements 155.

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• Physics & Mathematics (AREA)
• General Physics & Mathematics (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Length Measuring Devices By Optical Means (AREA)

Priority Applications (5)

Applications Claiming Priority (2)

Publications (1)

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Family Applications (1)

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Cited By (1)

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Citations (5)

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• 2009
  • 2009-10-19 EP EP09013170A patent/EP2312267A1/de not_active Withdrawn
• 2010
  • 2010-06-21 WO PCT/EP2010/058722 patent/WO2011047890A1/de not_active Ceased
  • 2010-06-21 US US13/502,381 patent/US20120263866A1/en not_active Abandoned
  • 2010-06-21 KR KR1020127009905A patent/KR20120098632A/ko not_active Ceased
  • 2010-06-21 JP JP2012534593A patent/JP2013508696A/ja active Pending
  • 2010-06-21 RU RU2012120660/28A patent/RU2541440C2/ru not_active IP Right Cessation
  • 2010-06-21 EP EP10728168A patent/EP2491338A1/de not_active Withdrawn
  • 2010-06-21 CN CN2010800472248A patent/CN102575927A/zh active Pending

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