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WO1998005949A1 - Procede et dispositif de controle du delaminage de revetements appliques sur des substrats, notamment de revetements appliques par projection de plasma sous vide sur des pales de turbines a gaz - Google Patents

Procede et dispositif de controle du delaminage de revetements appliques sur des substrats, notamment de revetements appliques par projection de plasma sous vide sur des pales de turbines a gaz Download PDF

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Publication number
WO1998005949A1
WO1998005949A1 PCT/DE1997/001615 DE9701615W WO9805949A1 WO 1998005949 A1 WO1998005949 A1 WO 1998005949A1 DE 9701615 W DE9701615 W DE 9701615W WO 9805949 A1 WO9805949 A1 WO 9805949A1
Authority
WO
WIPO (PCT)
Prior art keywords
examined
coatings
coating area
flash
temperature
Prior art date
Application number
PCT/DE1997/001615
Other languages
German (de)
English (en)
Inventor
Erich Becker
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO1998005949A1 publication Critical patent/WO1998005949A1/fr

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Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N25/00—Investigating or analyzing materials by the use of thermal means
    • G01N25/72—Investigating presence of flaws

Definitions

  • the invention relates to a method and a device for delamination testing in coatings on substrates, in particular in VPS coatings on gas turbine blades.
  • gas turbine blades which are generally made of Ni-based cast iron alloys, for example of types IN 939, IN 738 LC or PWA 1483 SX
  • the composition of these super alloys is designed for the strength of the blade material, which reduces the corrosion resistance .
  • VPS vacuum plasma sprayed
  • Such coatings can now pose problems on the one hand during the actual blade manufacture and, on the other hand, during continuous operation in that so-called delaminations occur - that is, places where the adhesion between coating and substrate is interrupted.
  • delaminations are particularly tricky if they cannot be recognized by a visual inspection of the coating, that is to say they do not yet show up as spalling or bulging of the coating. If such hidden delaminations remain undetected during the quality check after the manufacture of the turbine blade or during a corresponding revision check after a certain operating time, this can lead to serious impairments of the turbine function.
  • the object of the invention is to provide a method and a device for non-destructive delamination testing of coatings on substrates, in particular VPS coatings on gas turbine blades, with which delaminations which cannot be detected by visual inspection can also be reliably detected.
  • the method is based on the effect that the latent delaminations lead to a heat build-up on the surface due to the separation of the coating from the underlying substrate, as a result of which this location cools more slowly.
  • the areas with hidden delaminations underneath show up as areas that are temporarily warmer than the surface environment.
  • Temperature differences in the order of magnitude of 2 ° C to 10 ° C and more occur with delaminations with a gap width of ⁇ 1 ⁇ m, which is shown in the diagrams of the Temperature curve in the form of infrared thermography images are easily recognizable.
  • thermography test method offers a rational possibility, which can be carried out in a short time, for the non-destructive checking of substrate coatings for delaminations.
  • This thermography test method is particularly suitable for checking VPS coatings on newly manufactured gas turbine blades that are also under revision.
  • the device for carrying out the test method according to the invention further specified in the claims has a control unit for controlling the process sequence, a gradually rechargeable flash lamp unit for pulse-like heating of the coating area to be examined, an infrared thermography camera for recording the temporal change in the temperature distribution on the surface of the coating area and an evaluation and display unit for temporally and locally resolved representation of the temperature profile on the top of the coating area to be examined.
  • thermography test stand 1 is a schematic perspective view of a thermography test stand
  • thermographic image 3 shows a black-and-white reproduction of a thermographic image obtained in the delamination test.
  • thermography test stand shown in FIG. 1 has a flash lamp unit 1, an infrared thermography camera 2, a test part holder 3 and a control unit 4 as the core pieces.
  • the entire test bench is housed in a chamber 5, which is air-conditioned via fans 6.
  • test stand components roughly outlined above are used to carry out a pulse video thermography method to be explained later.
  • test stand In order to simultaneously make the test stand suitable for transmission-related ographic measuring methods, it also has a hot air tank 7 and a cold air tank 8, which can be connected to the test part receptacle 3 via a feed line 9.
  • Capacitor blocks 10 are provided for the energy supply of the flash lamp unit.
  • a temperature control device 11 for the test bench is also indicated schematically.
  • the flash lamp unit 1 has four flash lamps 13 arranged in a square and suspended from a frame 12, each of which emits a light energy of up to 6.4 kJ per light flash emitted.
  • the pulse duration of the flashes is approximately 5 milliseconds.
  • the frame 12 is the Flash lamp unit 1 can be moved transversely to the shooting direction A of the camera 2 on a guide 14 in order to be able to completely remove the flash lamp unit 1 from the shooting area of the camera 2. This is advantageous, for example, for the transmission thermographic measurement methods mentioned above, in which the flash lamp unit 1 is not required.
  • the infrared thermography camera 2 works in a temperature range from 0 ° C to 200 ° C with a resolution of up to 0.05 ° C. It is mounted on a cross slide-like manipulator 16, with which the camera 2 along the three spatial axes x , y and z in FIG. 1 can be maneuvered via the control unit 4. Together with the arrangement of the test part holder 3 on a turntable 17, an automatic positioning of the camera 2 and the gas turbine blade 15 to be tested is possible with respect to one another via the control unit 4.
  • This control unit 4 is a first computer of the overall system, which also carries out the temperature and voltage regulation and controls the triggering of the camera 2 and the flash lamp unit 1.
  • the personal computer of the control unit 4 is therefore the actual control computer for the system components.
  • thermography camera 2 has an infrared detector with a resolution of 768 x 600 lines, which leads to a local resolution of approximately 0.3 mm when the thermographic image of the test part is recorded.
  • the recording frequency is 25 Hz, so it can be every 40 milliseconds
  • Thermographic image of the test part 15 are recorded. In total, for example, 30 images are recorded at the specified time interval, which leads to a measuring time of 1.2 seconds.
  • thermographic images are obtained after the gas turbine blade 15 has been heated added.
  • a delamination test can thus be carried out in a manner to be explained in more detail.
  • hot air from the hot air tank 7 can be applied to it briefly, that is to say in a pulsed manner, after which the course of the cooling of the test part in turn is repeated with the infrared Thermography camera 2 recorded and corresponding conclusions can be drawn from it.
  • a coupling adapter 18 is provided for coupling the gas turbine blade 15 to the hot air supply line 9.
  • control unit 4 includes a personal computer 19 with a color monitor 20, color printer 21 and external data memory 22.
  • the personal computer 19 serves to enter the test and control parameters which are transferred to the control computer 4 by the system link between the personal computer 19 and the control computer 4. With these input values, the control unit 4 then - as discussed - carries out the actual control, with appropriate drivers for the drives of the manipulator 16 and the turntable 17 for automatically positioning the camera 2 and the gas turbine blade 15 being addressed via respective control lines 23 .
  • the personal computer 19 is also used to evaluate and display the thermographic images recorded by the camera 2.
  • thermography test stand to blacken the test part (gas turbine blade 15) with a paint spray gun 24, the arrows 25 schematically indicating warm air for quick drying of the paint (FIG. 2A).
  • An ultrasonic bath 26 is provided for cleaning the test part after the thermography measurement, in which the blackening is removed again (FIG. 2C).
  • the blade to be tested is first blackened with the paint spray gun 24 and then placed on the test part receptacle 3 of the turntable 17 via the coupling adapter 18 (FIG. 2A). Then, as shown in FIG. 2B, the blade 15 is brought into a rotary position by input on the personal computer 19 and further processing by the control unit 4, in which the surface area to be checked faces the flash lamp unit 1 and the thermography camera 2.
  • the manipulator 16 brings the camera 2 into the appropriate shooting position with the corresponding x, y and z coordinates and puts it in readiness for shooting.
  • the flash lamps 13 simultaneously generate a flash of energy of up to 6.4 kJ in a time of 5 milliseconds.
  • the coating area to be examined suddenly heats up due to this irradiation, after which its surface cools down again due to the heat diffusion. The process takes place depending on
  • thermographic images obtained therefrom represent a temporally and spatially resolved representation of the temperature profile of the surface of the irradiated coating area, as z. B. is shown in Fig. 3.
  • Such a thermographic image can be improved in its informative value by known image processing methods, such as averaging from or integration over several images, etc.
  • thermographic image shown in FIG. 3 shows an approximately triangular location D in the lower left area, which has an elevated temperature compared to the surface environment during the measuring time of the camera 2. This point, the surface of which appears intact, represents a delamination, that is to say a layer detachment of the VPS coating from the blade substrate. This was verified by subsequent destructive testing of the blade.

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  • Physics & Mathematics (AREA)
  • Health & Medical Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Chemical & Material Sciences (AREA)
  • Analytical Chemistry (AREA)
  • Biochemistry (AREA)
  • General Health & Medical Sciences (AREA)
  • General Physics & Mathematics (AREA)
  • Immunology (AREA)
  • Pathology (AREA)
  • Investigating Or Analyzing Materials Using Thermal Means (AREA)
  • Radiation Pyrometers (AREA)

Abstract

L'invention concerne un procédé et un dispositif conçu de façon appropriée, pour contrôler le délaminage de revêtements appliqués sur des substrats, notamment de revêtements appliqués par projection de plasma sous vide sur des pales de turbines à gaz (15). Ledit procédé consiste à chauffer la zone revêtue à examiner, par exposition à des éclairs lumineux, à enregistrer les variations temporelles de la répartition de la température sur la surface de la zone revêtue à examiner, au moyen d'une caméra de thermographie infrarouge (2), et à effectuer une représentation à résolution temporelle et spatiale des variations de température sur la surface de la zone revêtue. Ceci permet de détecter des zones présentant temporairement une température supérieure à celle de la région autour de la surface. Ces zones représentent un délaminage du revêtement appliqué sur le substrat, non visible à l'oeil nu.
PCT/DE1997/001615 1996-07-31 1997-07-30 Procede et dispositif de controle du delaminage de revetements appliques sur des substrats, notamment de revetements appliques par projection de plasma sous vide sur des pales de turbines a gaz WO1998005949A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19630988.3 1996-07-31
DE19630988 1996-07-31

Publications (1)

Publication Number Publication Date
WO1998005949A1 true WO1998005949A1 (fr) 1998-02-12

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PCT/DE1997/001615 WO1998005949A1 (fr) 1996-07-31 1997-07-30 Procede et dispositif de controle du delaminage de revetements appliques sur des substrats, notamment de revetements appliques par projection de plasma sous vide sur des pales de turbines a gaz

Country Status (1)

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WO (1) WO1998005949A1 (fr)

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999044011A1 (fr) * 1998-02-28 1999-09-02 Ramseier Rubigen Ag Appareil de mesure a infrarouges pour mesurer l'epaisseur d'une couche
US6367969B1 (en) 1999-07-21 2002-04-09 General Electric Company Synthetic reference thermal imaging method
US6367968B1 (en) 1999-07-21 2002-04-09 General Electric Company Thermal resonance imaging method
US6394646B1 (en) 1999-04-16 2002-05-28 General Electric Company Method and apparatus for quantitative nondestructive evaluation of metal airfoils using high resolution transient thermography
GB2372316A (en) * 2000-09-15 2002-08-21 Univ Warwick Non-destructive detection of damage sites
WO2003062807A3 (fr) * 2002-01-23 2003-12-31 Fraunhofer Ges Forschung Procede permettant de verifier l'adhesion de revetements sur un substrat
US6690685B1 (en) 1999-09-29 2004-02-10 Corning O.T.I., Spa Method for producing a fiber laser
WO2006037359A1 (fr) * 2004-10-04 2006-04-13 Siemens Aktiengesellschaft Procede pour determiner des parametres materiels d'un objet a partir de donnees temperature-contre-temps
EP1681562A1 (fr) * 2005-01-17 2006-07-19 Lufthansa Technik AG Méthode pour l'inspection non-destrucitve des structures multicouche quant aux irrégularités
EP1852697A1 (fr) * 2004-10-04 2007-11-07 Siemens Aktiengesellschaft Procédé pour déterminer les paramètres matériaux d'un objet à partir de données de température en fonction du temps (t-t)
GB2442744A (en) * 2006-10-12 2008-04-16 Rolls Royce Plc Method and apparatus for highlighting test pieces
US7409313B2 (en) 2005-12-16 2008-08-05 General Electric Company Method and apparatus for nondestructive evaluation of insulative coating
WO2011131263A1 (fr) * 2010-04-23 2011-10-27 Siemens Aktiengesellschaft Système de contrôle pour l'inspection d'aubes de turbines
WO2011137547A2 (fr) 2010-05-03 2011-11-10 Winterthur Instruments Gmbh Dispositif de contrôle non destructif et sans contact de surfaces
DE102013003760A1 (de) * 2013-03-06 2014-09-11 MTU Aero Engines AG Verfahren und Vorrichtung zur Qualitätsbeurteilung eines mittels eines generativen Lasersinter- und/oder Laserschmelzverfahrens hergestellten Bauteils
DE102010053766B4 (de) * 2010-12-08 2019-05-23 Acculogic Corporation Vorrichtung zum thermischen Testen von Platinen
CN113567492A (zh) * 2021-07-26 2021-10-29 北京航空航天大学 一种基于红外热耗散的涡轮叶片热障涂层无损检测方法和检测装置
CN113959729A (zh) * 2021-10-20 2022-01-21 中国科学院工程热物理研究所 一种基于温降热成像的涡轮叶片表面传热系数测试方法

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GB943559A (en) * 1960-05-16 1963-12-04 United States Steel Corp Apparatus for visually inspecting strip travelling at high speed
GB2220065A (en) * 1988-06-07 1989-12-28 Atomic Energy Authority Uk Coating inspection

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GB943559A (en) * 1960-05-16 1963-12-04 United States Steel Corp Apparatus for visually inspecting strip travelling at high speed
GB2220065A (en) * 1988-06-07 1989-12-28 Atomic Energy Authority Uk Coating inspection

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
J. W. MACLACHLAN SPICER: "MEASUREMENT OF COATING PHYSICAL PROPERTIES AND DETECTION OF COATING DISBONDS BY TIME-RESOLVED INFRARED RADIOMETRY", JOURNAL OF NONDESTRUCTIVE EVALUATION, vol. 8, no. 2, 1989, NEW YORK, US, pages 107 - 120, XP000162096 *
S. K. LAU: "TRANSIENT THERMAL WAVE TECHNIQUES FOR THE EVALUATION OF SURFACE COATINGS", JOURNAL OF PHYSICS D: APPLIED PHYSICS, vol. 24, no. 14, 1991, BRISTOL, GB, pages 428 - 436, XP000225369 *

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999044011A1 (fr) * 1998-02-28 1999-09-02 Ramseier Rubigen Ag Appareil de mesure a infrarouges pour mesurer l'epaisseur d'une couche
US6394646B1 (en) 1999-04-16 2002-05-28 General Electric Company Method and apparatus for quantitative nondestructive evaluation of metal airfoils using high resolution transient thermography
US6367969B1 (en) 1999-07-21 2002-04-09 General Electric Company Synthetic reference thermal imaging method
US6367968B1 (en) 1999-07-21 2002-04-09 General Electric Company Thermal resonance imaging method
US6690685B1 (en) 1999-09-29 2004-02-10 Corning O.T.I., Spa Method for producing a fiber laser
GB2372316A (en) * 2000-09-15 2002-08-21 Univ Warwick Non-destructive detection of damage sites
WO2003062807A3 (fr) * 2002-01-23 2003-12-31 Fraunhofer Ges Forschung Procede permettant de verifier l'adhesion de revetements sur un substrat
WO2006037359A1 (fr) * 2004-10-04 2006-04-13 Siemens Aktiengesellschaft Procede pour determiner des parametres materiels d'un objet a partir de donnees temperature-contre-temps
EP1852697A1 (fr) * 2004-10-04 2007-11-07 Siemens Aktiengesellschaft Procédé pour déterminer les paramètres matériaux d'un objet à partir de données de température en fonction du temps (t-t)
EP1681562A1 (fr) * 2005-01-17 2006-07-19 Lufthansa Technik AG Méthode pour l'inspection non-destrucitve des structures multicouche quant aux irrégularités
US7409313B2 (en) 2005-12-16 2008-08-05 General Electric Company Method and apparatus for nondestructive evaluation of insulative coating
GB2442744B (en) * 2006-10-12 2009-07-08 Rolls Royce Plc A test apparatus and method
US7656517B2 (en) 2006-10-12 2010-02-02 Rolls-Royce Plc Test apparatus and method
GB2442744A (en) * 2006-10-12 2008-04-16 Rolls Royce Plc Method and apparatus for highlighting test pieces
US9151698B2 (en) 2010-04-23 2015-10-06 Siemens Aktiengesellschaft Testing system for examining turbine blades
WO2011131263A1 (fr) * 2010-04-23 2011-10-27 Siemens Aktiengesellschaft Système de contrôle pour l'inspection d'aubes de turbines
CN102869973A (zh) * 2010-04-23 2013-01-09 西门子公司 用于检查涡轮叶片的检验系统
WO2011137547A2 (fr) 2010-05-03 2011-11-10 Winterthur Instruments Gmbh Dispositif de contrôle non destructif et sans contact de surfaces
DE102010053766B4 (de) * 2010-12-08 2019-05-23 Acculogic Corporation Vorrichtung zum thermischen Testen von Platinen
DE102013003760A1 (de) * 2013-03-06 2014-09-11 MTU Aero Engines AG Verfahren und Vorrichtung zur Qualitätsbeurteilung eines mittels eines generativen Lasersinter- und/oder Laserschmelzverfahrens hergestellten Bauteils
EP2964449B1 (fr) 2013-03-06 2018-05-30 MTU Aero Engines GmbH Procédé et dispositif pour évaluer la qualité d'un composant fabriqué au moyen d'un procédé génératif de frittage au laser et/ou de fusion au laser
US10520427B2 (en) 2013-03-06 2019-12-31 MTU Aero Engines AG Method and device for evaluating the quality of a component produced by means of an additive laser sintering and/or laser melting method
US10900890B2 (en) 2013-03-06 2021-01-26 MTU Aero Engines AG Method and device for evaluating the quality of a component produced by means of an additive laser sintering and/or laser melting method
US11931955B2 (en) 2013-03-06 2024-03-19 MTU Aero Engines AG Method for evaluating the quality of a component produced by an additive sintering and/or melting method
CN113567492A (zh) * 2021-07-26 2021-10-29 北京航空航天大学 一种基于红外热耗散的涡轮叶片热障涂层无损检测方法和检测装置
CN113959729A (zh) * 2021-10-20 2022-01-21 中国科学院工程热物理研究所 一种基于温降热成像的涡轮叶片表面传热系数测试方法
CN113959729B (zh) * 2021-10-20 2023-12-05 中国科学院工程热物理研究所 一种基于温降热成像的涡轮叶片表面传热系数测试方法

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