WO2005019370A2 - Heat-insulation material and arrangement of a heat-insulation layer containing said heat-insulation material - Google Patents

Heat-insulation material and arrangement of a heat-insulation layer containing said heat-insulation material Download PDF

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Publication number
WO2005019370A2
WO2005019370A2 PCT/EP2004/051632 EP2004051632W WO2005019370A2 WO 2005019370 A2 WO2005019370 A2 WO 2005019370A2 EP 2004051632 W EP2004051632 W EP 2004051632W WO 2005019370 A2 WO2005019370 A2 WO 2005019370A2
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WO
WIPO (PCT)
Prior art keywords
heat
heat insulating
phosphor
insulating material
carrier body
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Application number
PCT/EP2004/051632
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German (de)
French (fr)
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WO2005019370A3 (en
Inventor
Ulrich Bast
Wolfgang Rossner
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Siemens Aktiengesellschaft
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Filing date
Publication date
Priority to DE10337287 priority Critical
Priority to DE10337287.3 priority
Application filed by Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2005019370A2 publication Critical patent/WO2005019370A2/en
Publication of WO2005019370A3 publication Critical patent/WO2005019370A3/en

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    • GPHYSICS
    • G01MEASURING; TESTING
    • G01KMEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K11/00Measuring temperature based upon physical or chemical changes not covered by groups G01K3/00, G01K5/00, G01K7/00 or G01K9/00
    • G01K11/20Measuring temperature based upon physical or chemical changes not covered by groups G01K3/00, G01K5/00, G01K7/00 or G01K9/00 using thermoluminescent materials
    • CCHEMISTRY; METALLURGY
    • C23COATING 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
    • C23CCOATING 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
    • C23C4/00Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • CCHEMISTRY; METALLURGY
    • C23COATING 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
    • C23CCOATING 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
    • C23C4/00Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/02Pretreatment of the material to be coated, e.g. for coating on selected surface areas
    • CCHEMISTRY; METALLURGY
    • C23COATING 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
    • C23CCOATING 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
    • C23C4/00Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/18After-treatment

Abstract

Said invention relates to a heat-insulation material for a heat-insulation layer (3) for a carrier body (2) for preventing heat transfer between said carrier body and a surrounding area (7) therearound comprising at least one luminous substance which is excitable for emitting luminescent light having a defined emission wavelength and comprises at least one type of metal oxide containing at least one trivalent metal (A). Said invention also relates to an arrangement of at least one heat-insulation layer which contains said heat-insulation material and is applied to the carrier body. The inventive heat-insulation material is characterised in that the metal oxide is embodied in the form of a mixed oxide selected in a perovskite group of total formula AA'O3, and/or of pyrochlore of total formula A2B2O7, wherein A' is the trivalent metal and B is a tetravalent metal. Said heat-insulation layer containing said heat-insulation material is preferably used for a gas turbine.

Description

description

Thermal insulation and arrangement of a thermal barrier coating with the Wärmedammstof £

The invention relates to a heat insulating material for a thermal barrier coating of a carrier body to contain a heat transfer between the support body and a surrounding area of ​​the carrier body, wherein the heat insulating material comprises at least one phosphor that can be excited to emit luminescent light having a certain emission wavelength and the phosphor, at least one metal oxide having at least one trivalent metal a. In addition to the thermal insulation material, an arrangement of at least one Wärmdämmschicht with the heat insulation material is provided on a support body.

Such a heat insulating material and such an arrangement are known 1105550 Bl, EP. The carrier body is a component of a gas turbine. The carrier body is made of metal. Due to occur in a gas turbine high temperature of over 1200 'C in the vicinity of the device may cause damage to the metal of the component. To prevent this, a heat insulating layer (thermal barrier coating, TBC) is applied to the component. The

Thermal barrier layer ensures that a reduced heat exchange between the support body of the metal and the environment takes place. Thus, a metal surface of the component is heated to a lesser extent. occurs at the metal surface of the component a

Surface temperature, which is lower than the temperature in the vicinity of the component.

The heat insulating material forms a base material of the thermal barrier coating. The mechanical and thermal

Properties of the thermal barrier coating depend essentially on the properties of the insulation product. The base material of known thermal barrier coating is a metal oxide. The metal oxide is, for example, an yttrium stabilized zirconia (YSZ). A thermal conductivity of this heat insulating material is between 1 W / mK and 3 W / mK. In order to ensure an efficient protection of the carrier body, a layer thickness of the thermal barrier layer is about 250 microns. As an alternative to yttrium stabilized zirconium oxide, a metal oxide is given in the form of a Yttriumaluminiumgranats as heat insulation.

To connect the heat-insulating layer and the carrier body firmly, is applied on the surface of the component a metallic intermediate layer (bond coat) of a metal alloy. To improve the connection may be between the heat insulating layer and the component additionally a ceramic intermediate layer of a ceramic material such as alumina may be disposed.

In the thermal barrier coating a so-called thermo luminescence indicator is embedded. This indicator is a phosphor (luminophore), which can be excited by excitation with excitation light of a certain excitation wavelength to emit a luminescence light with a particular emission wavelength. The excitation light, for example UV light. The emission light, for example visible light. The phosphor used is a so-called Rekombinationsleuchtstoff. the light-emitting operation caused by electronic transitions between energy states of the activator. Such a phosphor consists for example of a

Solid state having a crystal lattice (host lattice), in which a so-called activator is embedded. The solid is doped with the activator. The activator is involved together with the total solids in the luminescence of the phosphor. In the known thermal barrier coating, the respective base material of the heat-insulating layer is doped with an activator. There is a thermal insulation layer of the phosphor. The activator used is each a rare earth element. In the case of yttrium stabilized zirconium oxide, the rare earth element, for example, europium. The thermal insulation material yttrium aluminum garnet doped with the rare earth elements dysprosium or terbium.

In the known thermal barrier coating, the fact is exploited that an emission characteristic of the luminescent light of the phosphor, for example, an emission intensity or emission decay time is dependent on the phosphor temperature of the phosphor. Because of this dependency is to the temperature of

closed thermal insulation layer with the phosphor. In order that this connection can be made is the W rmedämmschicht optically accessible to the excitation light in the UV range. At the same time it is ensured that the luminescence of the phosphor may be radiated by the heat-insulating layer and detected.

In order to ensure optical access, for example, is arranged on the supporting body, only a single heat-insulating layer with the phosphor. As an alternative solution to a further thermal barrier coating is applied to the thermal barrier coating, which is transparent to the excitation light and the luminescent light of the phosphor. The luminescence of the phosphor to pass through the additional thermal barrier coating.

A usability of a thermal barrier layer made of one of the said luminescent heat insulating materials is due to the specific material properties, for example, phase stability or susceptibility to sintering, to a

Operating temperature of about 1200 ° C limit. Therefore, these thermal insulation products are not suitable for future gas turbine generations in which to improve efficiency, the operating temperature increased uence.

Object of the present invention is therefore to provide a luminescent heat insulating material for a thermal barrier coating of a carrier body, which is stable over a temperature of 1200 ° C addition.

To achieve the object, a heat insulating material for a thermal barrier coating of a carrier body to contain a

Heat transfer between the support body and a surrounding area of ​​the support body specified, wherein said heat insulating material comprises a phosphor as a minimum the emission of

Luminescence light with a particular emission wavelength can be excited, and the fluorescent substance at least one

includes metal oxide containing at least one trivalent metal A. The heat insulating material is characterized in that the metal oxide and / or pyrochlore is selected from the group perovskite with the empirical formula AAO3 having the empirical formula A2B2O7 selected composite oxide, wherein A 'is a trivalent metal and B is a tetravalent metal.

To achieve the object, wherein the thermal insulation layer comprises the thermal insulation material described with the phosphor, an arrangement of at least one heat insulation layer on a support body to contain a heat transfer between the support body and a surrounding area of ​​the support body specified.

A thermal insulation layer of a perovskite and / or a pyrochlore (pyrochlore phase) is characterized by a high stability to temperatures in excess of 1200 ° C. These stable thermal barrier coatings have a phosphor. The thermal barrier coating may be present single-phase or multiphase. Single-phase means that a thermal insulation material formed by the ceramic phase of the thermal barrier coating consists essentially of only the phosphor. The heat insulation of W is rmedämmschicht the phosphor. In a multi-phase heat-insulating layer of thermal insulation material and the phosphor are different. In the heat insulation material phosphor particles contained in the phosphor. The ceramic phase is formed of different materials. Preferably, the phosphor particles are homogeneously distributed over the thermal barrier coating. Moreover, it is advantageous if the heat insulation material and the phosphor are made of a substantially similar type solid. The phosphor and heat insulation made of the same metal. Both substances differ only in their optical properties. For this, the phosphor is doped, for example.

The phosphor is a Rekombinationsleuchtstoff. The

Emission of the luminescent light is based preferably on the presence of an activator. With the aid of an activator or more activators, the emission characteristic of the phosphor, for example, the emission wavelength and the emission intensity can be relatively easily varied. In a particular embodiment, the phosphor to excite the emission of luminescence light to a selected from the group cerium and / or europium and / or dysprosium and / or terbium activator. Rare earth elements can be incorporated very well into the crystal lattice of perovskites and pyrochlores because of their ionic radii in general. Therefore, activators are generally in the form of rare earth elements. As a particularly good activators are enumerated rare earth elements have been found.

When using an activator whose proportion is selected in the phosphor such that the thermal and mechanical properties of the metal oxide of the phosphor are virtually unaffected. The mechanical and thermal properties of the metal are retained despite doping. In a particular embodiment, the activator in a proportion of up to 10 mol% in the phosphor is contained. the ratio is preferably below 2 mol%. For example, the proportion of 1 mol%. It has been shown that this low proportion of the activator sufficient to achieve a usable emission intensity of the phosphor. The thermal and mechanical stability of the

Thermal barrier coating phosphor produced is maintained.

In a particular embodiment, the trivalent metal A and / or the trivalent metal A 'is a rare earth element Re. The trivalent metal A and / or the trivalent metal A 'is in particular one selected from the group of lanthanum and / or gadolinium and / or samarium rare earth element. Other rare earth elements are also conceivable. By using a perovskite and / or a pyrochlore with rare earth elements, an activator can be very easily incorporated in the crystal lattice of the perovskite or pyrochlore in the form of a rare earth element due to the similar ionic radii.

One of the trivalent metals A and A "of the perovskite is a main group or sub-group element. The tetravalent metal B of the pyrochlore is also a main or sub-group element. In both cases, mixtures of different primary and secondary group elements may be provided. Due to the different ionic radii take the rare earth elements and the main or transition group elements is preferably a different places in the perovskite or pyrochlore crystal lattice. as a particularly advantageous has itself as trivalent main group element aluminum proven. Together with rare earth elements is aluminum, for example, a perovskite, which to a mechanically and thermally stable heat-insulating layer leads. In a particular embodiment the perovskite is therefore an Seltenerdalumina. the molecular formula is ReAlθ3, wherein Re represents a rare earth element. Preferably, the rare earth is gadolinium-lanthanum aluminate. the molecular formula is For example Gdg f 0 25 La, 75 Al0 3 • As tetravalent metal B of the pyrochlore particular the

Subgroup elements hafnium and / or titanium and / or

Zirconium used. The pyrochlore is therefore preferably selected from the group Seltenerdtitanat and / or Seitenerdhafnat and / or selected Seltenerdzirkonat. In particular, the

Seltenerdzirkonat from the group gadolinium and / or

Samariumzirkonat selected. The preferred sum formulas are Gd2Zr2θ 7 and Sm2Zr2θ7. The Seltenerdhafnat is preferred lanthanum hafnate. The molecular formula is La2Hf2O7.

The excitation of the luminescent material for emitting luminescent light by optical. The phosphor is irradiated with excitation light of a certain excitation wavelength. the fluorescent emission of luminescence is excited by absorption of the excitation light. The excitation light, for example UV light and the luminescent light niederenergetischeres, visible light.

The excitation of the phosphor by excitation light is suitable for checking a state of an optically accessible for the excitation light and the luminescent light thermal barrier coating with the phosphor. For this only the thermal barrier coating with the phosphor, for example, applied to the carrier body.

In a particular embodiment regarding the arrangement of insulating layer to the support body at least one further thermal barrier coating is provided which is substantially free of the phosphor. Essentially free here means that no usable luminescence light can be detected by a very small proportion of the phosphor. The additional heat insulation layer may be arranged between the carrier body and the thermal barrier layer with the phosphor. The outermost heat-insulating layer is formed by the heat-insulating layer with the phosphor. A transmission characteristic of the further insulating layer with respect to the luminescent light and / or the excitation light does not matter. The thermal barrier coating with the phosphor is optically accessible. Such a solution is advantageous, for example for a thermal barrier layer made of a pyrochlore. In order to achieve a firm connection between the heat insulation layer and a layer applied to the carrier body intermediate metallic layer is applied directly to the metallic intermediate layer, a further insulation layer of an yttrium stabilized zirconia. About this further thermal barrier coating the thermal barrier coating is applied to the phosphor.

but the more thermal barrier coating may also be transparent to the excitation light and the luminescence of the phosphor. The excitation light and the luminescent light can pass through the additional thermal barrier coating. In such a solution, the thermal insulation layer may be disposed between the further insulation layer and the support body. By the transmission property of the further insulation layer, the thermal barrier coating with the phosphor is constantly visually accessible. In this way, as in the cases in which either the heat insulating layer with the phosphor is present or forming the thermal barrier coating with the phosphor, the outermost insulation layer of a multilayer structure, a state of Wärmdämmschicht can be determined by observing the emission properties of the luminescent light. For example, to infer the temperature of the thermal barrier coating.

In a particular embodiment, the more

Heat-insulating layer for the excitation light to excite the emission of luminescence light of the phosphor and / or opaque to the luminescent light of the phosphor. The excitation light and / or the luminescent light can further insulating layer due to the transmission or

Absorption characteristics of the thermal barrier coating further does not pass or only to a small extent. In a particular embodiment, the heat-insulating layer between the carrier body and the additional heat insulation layer is arranged such that the excitation light of the phosphor and / or the luminescence of the phosphor in the can to reach the environment of the carrier body substantially only through openings of the further thermal barrier coating. Such openings are for example, cracks or gaps in the further thermal barrier coating. Also conceivable is an opening defined by erosion (ablation) is formed by further thermal insulation of the further thermal barrier coating. These openings can be easily visualized. Visualization is accomplished by illuminating the array with excitation light. At the points at which the UV light passes through the openings in the thermal barrier coating with the phosphor, the phosphor to emit the luminescent light is excited. The luminescent light again passes through the openings in the surroundings of the carrier body and can be detected there. Because of the openings a luminescence occurs that stands out clearly from the background.

In the described way the thermal barrier coating of a support body used in the device in a simple and secure manner can be checked during a pause in operation of a device. The device is for example a gas turbine. The support body is, for example, a turbine blade of the gas turbine. On the turbine blade, the multilayer structure is the thermal barrier coatings. By illuminating the turbine blade and observing the luminescence of the phosphor of those digits are visible to the other, the outermost heat insulating layer having openings.

It is also conceivable that a check of the state of the thermal barrier layer is performed during operation of the device. For this purpose, for example, a combustor of the gas turbine described above, in which the turbine blades are inserted, provided with a window through which the luminescence of the phosphor can be observed. The occurrence of luminescent light is an indication that the additional, outermost thermal insulation layer at least one turbine blade having a crack or gap and is eroded.

A further advantage of the arrangement described is that as a result of advanced erosion and heat insulating material is removed with the phosphor. In an exhaust gas of the gas turbine of the fluorescent can be detected by appropriate detectors. This is a sign that the erosion has progressed up to the thermal barrier layer with the phosphor.

In a particular embodiment, the carrier body is a component of an internal combustion engine. The internal combustion engine such as a diesel engine. In a particular embodiment, the internal combustion engine is a gas turbine. The carrier body can be a tile, with a combustion chamber of the gas turbine is lined. In particular, the support body is a turbine blade of the gas turbine. It is conceivable here is that the different carrier body are provided with heat-insulating layers containing phosphors that emit different luminescent light. So the component can be easily determined at which damage is present.

For applying the different layers, in particular the thermal insulation layer and said further insulation layer, any coating method may be performed. The coating process is especially a

Plasma spraying process. The coating process may be a vapor deposition process, such as PVD (physical vapor deposition) or CVD (Chemical Vapor Deposition). By the methods mentioned thermal barrier coatings with layer thicknesses of 50 microns to 600 microns and more are applied.

To sum up, with the invention, the following special advantages:

- The materials used are stable at temperatures above 1200 ° C. This makes them particularly suitable for use in internal combustion engines, for example in a gas turbine.

- The mixed oxides used are intentionally doped with activators. This thermally and mechanically stable thermal barrier coatings are obtained with luminescent phosphors even at temperatures of over 1200 ° C, with the help of the state of the thermal barrier coatings during operation or can however be reviewed during stoppages of the carrier body easily.

Reference to several embodiments and the accompanying

Figures The invention is explained in more detail below. The figures are schematic and are not true to scale.

Figures 1 to 3 each show a section of a lateral cross-section of an arrangement of a thermal barrier layer made of a heat insulation material with a phosphor from the side.

The arrangement 1 comprises a support body 2 on which a thermal insulation layer 3 is disposed (Figure 1). The carrier body 2 is a turbine blade of a gas turbine. The turbine blade is made of metal. In the combustor of the gas turbine, illustrating the vicinity 7 of the support body 2, temperatures in excess of 1200 ° C can occur during operation of the gas turbine. To an overheating of the surface 8 to prevent the carrier body 2, the thermal insulation layer 3 is present. The heat insulating layer 3 is used for the containment of a heat transfer between the support body 2 and the area 7 of the support body. 2

Between the heat-insulating layer 3 and the support body 2, a metallic intermediate layer 4 (bond coat) is applied from a metal alloy. The heat insulating layer 3, the intermediate layer 4 and optionally the additional heat-insulating layer 5 are applied with the aid of a plasma spraying method onto the surface 8 of the support body. 2

Example 1 :

The heat insulating material of the thermal barrier layer 3 is a metal oxide in the form of a Seltenerdaluminats having the empirical formula

Gdg 25 ^ a ^ 0 75 103rd In a first embodiment the rare earth with 1 mol% is offset Eu2O3. The

Rare earth has the activator to the europium in a proportion of 1 mol%. By exciting the phosphor with UV light, a red luminescence resulted with an emission maximum at about 610 nm. The excitation wavelength is for example 254 nm.

According to an alternative embodiment, the rare earth doped with 1 mol% of terbium. This results in a phosphor with green luminescence with an emission wavelength at 544 nm.

Example 2:

In contrast to the previous example is a

Multi-layer structure of the heat insulating layer 3 and a further

Heat-insulating layer 5 on the support body 2 from (figure 2). The

Thermal insulation layer 3 consists of a pyrochlore. The pyrochlore is a gadolinium zirconate with the empirical formula Gd2Zr2Ü7. To the

Producing the phosphor of the pyrochlore with 1 mol% of E is added 2O3. The gadolinium has the activator

Europium in a proportion of 1 mol%.

To improve the adhesion on the support body 2, a further heat-insulating layer 5 between the bond coat layer 4 and the heat insulating layer 3 having the phosphor is present. The additional heat-insulating layer 5 consists of zirconium oxide stabilized with yttrium.

Example 3:

It is also within a multi-layer structure before (Figure 3). In contrast to the preceding example, the thermal barrier layer 3 is arranged with the phosphor between the further heat-insulating layer 5 and the support body. 5 The more heat-insulating layer 5 is opaque to the excitation light and / or the luminescence of the phosphor. Only when the additional heat-insulating layer 5 has an opening 6, the luminescence of the phosphor can be detected in the vicinity of the carrier body.

Claims

claims
1. Heat insulating material for a thermal barrier coating (3) of a support body (2) to contain a heat transfer between the carrier body (2) and a region (7) of the carrier body (2), wherein the heat insulating material comprises at least one phosphor for emitting luminescence with a specific emission wavelength can be excited, and the phosphor comprises at least one metal oxide having at least one trivalent metal a, characterized in that the metal oxide and / or pyrochlore is selected from the group perovskite with the empirical formula AAO3 having the empirical formula A2B2O7 selected composite oxide, wherein a 'is a trivalent metal and B is a tetravalent metal.
2. Heat insulating material according to claim 1, wherein said luminescent material for excitation of the emission of luminescent light having a selected from the group cerium and / or europium and / or dysprosium and / or terbium activator.
3. The heat insulating material according to claim 2, wherein the activator is contained in an amount of up to 10 mol% in the phosphor.
4. Heat insulating material according to any one of claims 1 to 3, wherein the trivalent metal A and / or the trivalent metal A 'is a rare earth element Re.
5. The heat insulating material according to claim 4, wherein the trivalent metal A and / or the trivalent metal A 'is a selected from the group of lanthanum and / or gadolinium and / or samarium rare earth element.
6. The heat insulating material according to any one of claims 1 to 5, wherein the perovskite is a rare earth.
7. The heat insulating material according to claim 6, wherein the sum of the Formula 5 Seltenerdaluminats Gdn 25 La 0 75AIO3 is.
8. The heat insulating material according to any one of claims 1 to 5, wherein the pyrochlore from the group Selterdhafnat and / or Seltenerdtitanat and / or selected Seltenerdzirkonat
10.
9. The heat insulating material according to claim 8, wherein the Seltenerdzirkonat from the group gadolinium and / or Samariumzirkonat is selected.
15 10. The heat insulating material according to claim 8, wherein the Seltenerdhafnat is lanthanum hafnate.
11. The arrangement of at least one heat insulating layer (3) to 20 a support body (2) to contain a heat transfer between the carrier body (2) and an environment (7) of the support body (2), wherein the heat insulating layer a heat insulating material according to any one of claims 1 to 10 has. 25
12. An arrangement according to claim 11, wherein at least one further heat insulating layer (5) is present which is substantially free of the phosphor.
30 13. An arrangement according to claim 12, wherein the further thermal insulation layer (5) for the excitation light to excite the emission of luminescence light and / or opaque to the luminescence of the phosphor substantially.
35 14. Arrangement according to claim 13, wherein the heat insulating layer (3) is arranged between the carrier body (2) and the additional heat insulating layer (5) such that the luminescence of the phosphor substantially only through openings (6) of the further thermal insulation layer (5) in the region (7) of the carrier body (2) can pass.
15. An arrangement according to any one of claims 11 to 14, wherein the carrier body is a component of an internal combustion engine.
16. An arrangement according to claim 15, wherein the internal combustion engine is a gas turbine.
PCT/EP2004/051632 2003-08-13 2004-07-28 Heat-insulation material and arrangement of a heat-insulation layer containing said heat-insulation material WO2005019370A2 (en)

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EP20040766341 EP1664231A2 (en) 2003-08-13 2004-07-28 Heat-insulation material and arrangement of a heat-insulation layer containing said heat-insulation material

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GB2439389A (en) * 2006-06-22 2007-12-27 Southside Thermal Sciences Multi layer coatings
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US8034469B1 (en) 2007-05-07 2011-10-11 Siemens Aktiengesellschaft Two-level layer system with pyrochlore phase and oxides
US9045830B2 (en) 2005-08-24 2015-06-02 New Sts Limited Luminescent material compositions and structures incorporating the same
FR3030751A1 (en) * 2014-12-17 2016-06-24 Snecma method for controlling the state of a thermal barrier endoscopically
US9611551B2 (en) 2005-11-24 2017-04-04 Siemens Aktiengesellschaft Layer system comprising gadolinium solid solution pyrochlore phase
DE102016203251A1 (en) * 2016-02-29 2017-08-31 Siemens Aktiengesellschaft Coating with temperature sensor and thus coated component

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Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000006796A1 (en) * 1998-07-27 2000-02-10 Imperial College Of Science, Technology And Medicine Thermal barrier coating with thermoluminescent indicator material embedded therein
WO2002014580A2 (en) * 2000-08-17 2002-02-21 Siemens Westinghouse Power Corporation Thermal barrier coating having high phase stability
US20030056520A1 (en) * 2001-09-26 2003-03-27 Chris Campbell Catalyst element having a thermal barrier coating as the catalyst substrate
WO2003057941A1 (en) * 2002-01-11 2003-07-17 Forschungszentrum Jülich GmbH Production of a ceramic material for a heat-insulating layer and heat-insulating layer containing said material

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6117560A (en) * 1996-12-12 2000-09-12 United Technologies Corporation Thermal barrier coating systems and materials
US6177200B1 (en) * 1996-12-12 2001-01-23 United Technologies Corporation Thermal barrier coating systems and materials
JP2001521988A (en) * 1997-11-03 2001-11-13 シーメンス アクチエンゲゼルシヤフト Products, structural members of a gas turbine, in particular having a ceramic heat-insulating layer

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000006796A1 (en) * 1998-07-27 2000-02-10 Imperial College Of Science, Technology And Medicine Thermal barrier coating with thermoluminescent indicator material embedded therein
WO2002014580A2 (en) * 2000-08-17 2002-02-21 Siemens Westinghouse Power Corporation Thermal barrier coating having high phase stability
US20030056520A1 (en) * 2001-09-26 2003-03-27 Chris Campbell Catalyst element having a thermal barrier coating as the catalyst substrate
WO2003057941A1 (en) * 2002-01-11 2003-07-17 Forschungszentrum Jülich GmbH Production of a ceramic material for a heat-insulating layer and heat-insulating layer containing said material

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* Cited by examiner, † Cited by third party
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US9045830B2 (en) 2005-08-24 2015-06-02 New Sts Limited Luminescent material compositions and structures incorporating the same
GB2431932B (en) * 2005-11-04 2011-07-27 Siemens Ag Two-layer barrier system using pyrochlores
WO2007051695A1 (en) * 2005-11-04 2007-05-10 Siemens Aktiengesellschaft Two-layer thermal protective coating system with pyrochlore phase
EP1783248A1 (en) * 2005-11-04 2007-05-09 Siemens Aktiengesellschaft Two-layer thermal barrier coating system containing a pyrochlore phase
US9611551B2 (en) 2005-11-24 2017-04-04 Siemens Aktiengesellschaft Layer system comprising gadolinium solid solution pyrochlore phase
US8057924B2 (en) 2006-01-09 2011-11-15 Siemens Aktiengesellschaft Layer system comprising two pyrochlore phases
WO2007080041A1 (en) * 2006-01-09 2007-07-19 Siemens Aktiengesellschaft Layer system comprising two pyrochlore phases
WO2007090711A1 (en) * 2006-02-09 2007-08-16 Siemens Aktiengesellschaft Process for producing a layer comprising a thermographic phosphor and a layer system
EP1818424A1 (en) * 2006-02-09 2007-08-15 Siemens Aktiengesellschaft Method for Producing a Coating Containing Thermoluminescent Material and the Coating System
GB2439389A (en) * 2006-06-22 2007-12-27 Southside Thermal Sciences Multi layer coatings
EP1990329A1 (en) * 2007-05-07 2008-11-12 Siemens Aktiengesellschaft Two-layered system with pryochlorphases and oxides
US8034469B1 (en) 2007-05-07 2011-10-11 Siemens Aktiengesellschaft Two-level layer system with pyrochlore phase and oxides
US8084382B2 (en) 2007-05-07 2011-12-27 Siemens Aktiengesellschaft Ceramic powder, ceramic layer and layer system with pyrochlore phase and oxides
EP1990330A1 (en) * 2007-05-07 2008-11-12 Siemens Aktiengesellschaft Ceramic powder, ceramic layer and layer system with gadolinium pyrochlorphases and oxides
FR3030751A1 (en) * 2014-12-17 2016-06-24 Snecma method for controlling the state of a thermal barrier endoscopically
DE102016203251A1 (en) * 2016-02-29 2017-08-31 Siemens Aktiengesellschaft Coating with temperature sensor and thus coated component

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