EP2971240B1 - Revêtement de barrière thermique hybride et son procédé de fabrication - Google Patents

Revêtement de barrière thermique hybride et son procédé de fabrication Download PDF

Info

Publication number
EP2971240B1
EP2971240B1 EP13878078.8A EP13878078A EP2971240B1 EP 2971240 B1 EP2971240 B1 EP 2971240B1 EP 13878078 A EP13878078 A EP 13878078A EP 2971240 B1 EP2971240 B1 EP 2971240B1
Authority
EP
European Patent Office
Prior art keywords
layer
barrier coating
thermal barrier
forming
porosity
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.)
Active
Application number
EP13878078.8A
Other languages
German (de)
English (en)
Other versions
EP2971240A4 (fr
EP2971240A1 (fr
Inventor
Brian T HAZEL
David A. Litton
Michael J. Maloney
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RTX Corp
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Publication of EP2971240A1 publication Critical patent/EP2971240A1/fr
Publication of EP2971240A4 publication Critical patent/EP2971240A4/fr
Application granted granted Critical
Publication of EP2971240B1 publication Critical patent/EP2971240B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/134—Plasma spraying
    • 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
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/04—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings of inorganic non-metallic material
    • C23C28/042—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings of inorganic non-metallic material including a refractory ceramic layer, e.g. refractory metal oxides, ZrO2, rare earth oxides
    • 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
    • C23C4/11—Oxides

Definitions

  • the present disclosure relates to a thermal barrier coating for use on a turbine engine component and to a process of making the thermal barrier coating.
  • a thermal barrier coating (TBC) is created to meet one or more performance requirements including, but not liited to, spallation life, calcia-magnesia-alumina-silicate (CMAS) resistance, foreign object damage (FOD) resistance, erosion, and low conductivity.
  • CMAS calcia-magnesia-alumina-silicate
  • FOD foreign object damage
  • a turbine barrier coating is applied to a turbine engine component, such as a turbine blade/vane, to help the component withstand the relatively high temperatures of its operational environment.
  • TBCs are often formed using a singular coating process such as an electron beam physical vapor deposition (EB-PVD) process.
  • EB-PVD electron beam physical vapor deposition
  • a TBC may be formed from two separate EB-PVD layers formed from two different materials, such as 7 wt% yttria stabilized zirconia and gadolinia stabilized zirconia in order to improve the thermal conductivity properties of the coating.
  • the strain-tolerant columnar structure of an EB-PVD coating helps to increase the TBC spallation life.
  • a more porous TBC however may minimize the TBC thermal conductivity and possibly the thermal radiation through the coating.
  • TBC there is a porous outer layer over a more dense inner layer made by an EB-PVD process.
  • the two layers have different porosity levels.
  • Such a structure can be formed by changing the coating temperature. More power equals more density but also more temperature. It is also known to form a dense vertically cracked microstructure for the TBC where the deposition is conducted at a two inch stand-off for the dense layer and a six inch stand-off for the porous layer.
  • EP 2 341 166 discloses a TBC on a substrate, the TBC comprising a bond coat, a ceramic coating, and a ceramic layer.
  • US 2011/244216 A1 discloses a combination of SPS and APS methods for deposition of multilayer thermal barrier coatings on turbine components.
  • the applied materials comprise partially or fully YSZ as well as pyrochlores.
  • EP 2 336 381 A1 discloses a thermal barrier coating deposited by APS, consisting of a first 7YSZ layer and a second gadolinia stabilized zirconia layer with a porosity of 5-20 vol.%.
  • EP 2 450 465 A1 discloses a multilayer ceramic TBC deposited by APS, comprising an inner YSZ layer of low porosity, an intermediate YSZ layer with higher porosity than the inner layer and an outer porous layer of gadolinium zirconate.
  • the second layer has a porosity in the range of from 10 to 40%.
  • the first layer forming step comprises suspending a powder feedstock in a liquid suspension and injecting the powder feedstock and the suspension into a plasma jet under conditions where the first layer is formed with the strain-tolerant columnar microstructure.
  • the second layer forming step comprises changing spray parameters so as to form the porous and radiation thermally resistant second layer.
  • the second layer forming step comprises forming the second layer so as to have a porosity of from 10 to 40%.
  • the first and second layer forming steps comprise using a powdered feedstock having a particle size in the range of from 10nm to 10 micrometers
  • the first and second layer forming steps comprises using a powdered feedstock having a particle size in the range of from 10nm to 2.0 micrometers.
  • the turbine engine component may be any component which requires a thermal barrier coating such as a blade/vane.
  • the turbine engine component 10 may have a substrate 12 formed from any suitable material known in the art including, but not limited to, a nickel based alloy, a cobalt based alloy, a titanium based alloy, a ceramic material, and an organo-matrix composite material.
  • a thermal barrier coating 14 is deposited on the substrate 12.
  • the thermal barrier coating 14 has a first layer 16 which interfaces with the surface 18 of the substrate 12 and an outer second layer 20.
  • the first layer 16 is formed so as to have a strain-tolerant columnar microstructure at the interface with the surface 18 of the substrate.
  • the second layer 20 is formed to have a porous thermal conduction and radiant heat transfer resistant microstructure at an outer surface 22 of the thermal barrier coating.
  • the first layer 16 and the second layer 20 is formed from a material having the same composition.
  • Each of the layers 16 and 20 is formed from a 7 wt% yttria stabilized zirconia (7YSZ).
  • each of the layers 16 and 20 is formed using suspension plasma spray (SPS) technique such as that shown in FIG. 2 .
  • SPS suspension plasma spray
  • a powdered feedstock is suspended in a liquid suspension 30.
  • the powdered feedstock may be 7YSZ which may be suspended in ethanol, water, or other alcohols such as methanol.
  • the powdered feedstock may have a particle size in the range of from 10 nm to 10 micrometers mean size diameter. In another non-limiting embodiment, the particles size may be in the range of from 10 nm to 2.0 micrometers.
  • the powdered feedstock in the suspension is injected into a plasma jet 32 created by a plasma torch 34 and thus deposited onto the substrate 12.
  • the spray conditions are such that the first layer 16 is formed to have the desired strain tolerant columnar microstructure.
  • the deposition technique may have a short stand off (similar to that used in dense vertically cracked coatings) and high power/enthalpy plasma conditions.
  • the spray conditions may be changed so as to form the second layer 20 with the porous thermal conduction and radiant heat transfer resistant microstructure.
  • porosity (1) the angle of the spray nozzle could be changed from normal relative to the surface on which the layer 20 is being deposited; (2) the stand off may be increased; and/or (3) the plasma power/enthalpy may be reduced. More porosity in the second layer 20 than in the first layer 16 creates a reduction in thermal conductivity.
  • the second layer 20 may have a reduction of at least 10% in thermal conductivity. This may come purely from a porosity increase or a change in the structure from columnar to more splat like. An increase in porosity increases the erosion rate. A useful limit may be 10 to 40% porosity in the second layer 20.
  • the columnar structure SPS gives a thermal cyclic spallation resistance similar to EB-PVD (much higher than APS and higher than dense vertically cracked). Erosion is a function of porosity content and can be greater or less than EB-PVD (generally higher than APS and more like dense vertically cracked). Thermal conductivity, as discussed above, follows the porosity content.
  • the spray conditions are discreetly or incrementally changed throughout the spray run.
  • the spray conditions are changed so that a continuously graded microstructure is formed where there is the strain-tolerant columnar microstructure at the interface with the substrate 12 for thermal barrier coating spallation resistance and a porous thermal conduction and radiation thermally resistant layer at the outer surface 22.
  • thermal barrier coating can be formed using a single piece of equipment and in a single coating.
  • Another advantage is that one can easily change the composition of the second layer 20 so that it is different than the composition of the first layer 16. This can easily be done by changing the composition of the feedstock being injected into the plasma jet.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Ceramic Engineering (AREA)
  • Inorganic Chemistry (AREA)
  • Coating By Spraying Or Casting (AREA)

Claims (8)

  1. Revêtement de barrière thermique (14) appliqué à un composant de moteur à turbine (10) ayant un substrat (2), ledit revêtement comprenant :
    une première couche (16) qui a une microstructure en colonne tolérante à la contrainte au niveau d'une interface avec le substrat pour résistance à la spallation ; et
    une seconde couche (20) qui est poreuse, thermiquement résistante au rayonnement et à la conduction au niveau d'une surface extérieure du revêtement de barrière thermique ;
    dans lequel il y a une microstructure échelonnée en continu de l'interface vers la surface extérieure ;
    dans lequel lesdites première et seconde couches sont formées à partir du même matériau ;
    dans lequel chacune desdites première et seconde couches est formée à partir de 7 % en poids de zircone stabilisée par de l'oxyde d'yttrium ; et
    dans lequel ladite première couche a une première conductibilité thermique et ladite seconde couche a une seconde conductibilité thermique qui est au moins 10 % inférieure à la première conductibilité thermique.
  2. Revêtement de barrière thermique selon la revendication 1, dans lequel ladite seconde couche présente une porosité dans la plage de 10 à 40 %.
  3. Procédé pour appliquer un revêtement de barrière thermique (14) à un composant de moteur à turbine (10) comprenant :
    la formation d'une première couche (16) qui a une microstructure en colonne tolérante à la contrainte au niveau d'une interface de la première couche et d'un substrat en utilisation une technique de pulvérisation de plasma en suspension ;
    la formation d'une seconde couche (20) qui est poreuse et thermiquement résistante au rayonnement au niveau d'une surface extérieure du revêtement de barrière thermique en utilisant ladite technique de pulvérisation de plasma en suspension ;
    la formation d'une microstructure échelonnée en continu de ladite interface vers ladite surface extérieure ;
    dans lequel lesdites étapes de formation de première et seconde couches comprennent la formation desdites couches à partir du même matériau ;
    dans lequel chacune desdites première et seconde couches est formée à partir de 7 % en poids de zircone stabilisée par de l'oxyde d'yttrium ; et
    dans lequel ladite étape de formation de seconde couche comprend la formation de ladite seconde couche avec plus de porosité que la première couche de manière à ce qu'elle ait une conductibilité thermique qui est au moins 10 % inférieure à une conductibilité thermique de ladite première couche.
  4. Procédé selon la revendication 3, dans lequel ladite étape de formation de première couche comprend la suspension d'une charge de poudre dans une suspension liquide et l'injection de ladite charge de poudre et de ladite suspension dans un jet de plasma dans des conditions où ladite première couche est formée avec ladite microstructure en colonne tolérante à la contrainte.
  5. Procédé selon la revendication 4, dans lequel ladite étape de formation de seconde couche comprend le changement de paramètres de pulvérisation de manière à former ladite seconde couche poreuse et thermiquement résistante au rayonnement.
  6. Procédé selon la revendication 3, dans lequel ladite étape de formation de seconde couche comprend la formation de ladite seconde couche de manière à avoir une porosité de 10 à 40 %.
  7. Procédé selon la revendication 3, dans lequel lesdites étapes de formation de première et seconde couches comprennent l'utilisation d'une charge de poudre ayant une taille de particule dans la plage de 10 nm à 10 micromètres.
  8. Procédé selon la revendication 7, dans lequel lesdites étapes de formation de première et seconde couches comprennent l'utilisation d'une charge de poudre ayant une taille de particule dans la plage de 10 nm à 2 micromètres.
EP13878078.8A 2013-03-14 2013-12-30 Revêtement de barrière thermique hybride et son procédé de fabrication Active EP2971240B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201361781656P 2013-03-14 2013-03-14
PCT/US2013/078186 WO2014143363A1 (fr) 2013-03-14 2013-12-30 Revêtement de barrière thermique hybride et son procédé de fabrication

Publications (3)

Publication Number Publication Date
EP2971240A1 EP2971240A1 (fr) 2016-01-20
EP2971240A4 EP2971240A4 (fr) 2016-12-21
EP2971240B1 true EP2971240B1 (fr) 2018-11-21

Family

ID=51537485

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13878078.8A Active EP2971240B1 (fr) 2013-03-14 2013-12-30 Revêtement de barrière thermique hybride et son procédé de fabrication

Country Status (3)

Country Link
US (2) US20160017475A1 (fr)
EP (1) EP2971240B1 (fr)
WO (1) WO2014143363A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4534512A1 (fr) * 2023-10-06 2025-04-09 RTX Corporation Système de revêtement de barrière thermique et radiatif multiphase

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3043411B1 (fr) * 2015-11-09 2017-12-22 Commissariat Energie Atomique Revetement ceramique multicouche de protection thermique a haute temperature, notamment pour application aeronautique, et son procede de fabrication
US10436042B2 (en) 2015-12-01 2019-10-08 United Technologies Corporation Thermal barrier coatings and methods
JP6908973B2 (ja) * 2016-06-08 2021-07-28 三菱重工業株式会社 遮熱コーティング、タービン部材、ガスタービン、ならびに遮熱コーティングの製造方法

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3872632B2 (ja) * 2000-06-09 2007-01-24 三菱重工業株式会社 遮熱コーティング材、それを適用したガスタービン部材およびガスタービン
US20090110953A1 (en) * 2007-10-29 2009-04-30 General Electric Company Method of treating a thermal barrier coating and related articles
DE102008007870A1 (de) * 2008-02-06 2009-08-13 Forschungszentrum Jülich GmbH Wärmedämmschichtsystem sowie Verfahren zu seiner Herstellung
US20110143043A1 (en) * 2009-12-15 2011-06-16 United Technologies Corporation Plasma application of thermal barrier coatings with reduced thermal conductivity on combustor hardware
US20110151219A1 (en) * 2009-12-21 2011-06-23 Bangalore Nagaraj Coating Systems for Protection of Substrates Exposed to Hot and Harsh Environments and Coated Articles
EP2341166A1 (fr) 2009-12-29 2011-07-06 Siemens Aktiengesellschaft Barrière thermique ceramique nano- et microstructurée
JP2010255121A (ja) * 2010-07-20 2010-11-11 Mitsubishi Heavy Ind Ltd 皮膜材料
EP2450465A1 (fr) * 2010-11-09 2012-05-09 Siemens Aktiengesellschaft Système de couche poreux doté d'une couche intérieure poreuse
US9017792B2 (en) * 2011-04-30 2015-04-28 Chromalloy Gas Turbine Llc Tri-barrier ceramic coating
US20130260132A1 (en) * 2012-04-02 2013-10-03 United Technologies Corporation Hybrid thermal barrier coating

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4534512A1 (fr) * 2023-10-06 2025-04-09 RTX Corporation Système de revêtement de barrière thermique et radiatif multiphase

Also Published As

Publication number Publication date
WO2014143363A1 (fr) 2014-09-18
US20180282853A1 (en) 2018-10-04
US20160017475A1 (en) 2016-01-21
EP2971240A4 (fr) 2016-12-21
EP2971240A1 (fr) 2016-01-20

Similar Documents

Publication Publication Date Title
Aghasibeig et al. A review on suspension thermal spray patented technology evolution
Mauer et al. Coatings with columnar microstructures for thermal barrier applications
EP3074546B1 (fr) Revêtements composites modifiés formant une barrière thermique
EP3107673B1 (fr) Méthode d'application d'un revêtement de barrière thermique
EP2893148B1 (fr) Revêtement de barrière thermique pour composants de moteur à turbine à gaz
US7833586B2 (en) Alumina-based protective coatings for thermal barrier coatings
Karthikeyan et al. Developing empirical relationships to estimate porosity and microhardness of plasma-sprayed YSZ coatings
EP2193217B1 (fr) Conférer des caractéristiques fonctionnelles à des parties de moteur
US20130260132A1 (en) Hybrid thermal barrier coating
JP2008045211A (ja) タービンエンジンコンポーネント及びタービンエンジンコンポーネントのコーティング方法
JP2019533090A (ja) セラミック化合物を含む層を有する固体基材の表面をコーティングする方法、及び該方法で得られたコーティング基材
US20180282853A1 (en) Hybrid Thermal Barrier Coating and Process of Making Same
CN107699840A (zh) 多孔氧化锆热障涂层的制备方法
EP3453779B1 (fr) Revêtement de barrière thermique résistant cmas multicouches
CN102423935A (zh) 一种热障涂层系统
EP2322686B1 (fr) Procédé de pulvérisation thermique pour produire des revêtements de barrière thermique à segmentation verticale
US20140193760A1 (en) Coated article, process of coating an article, and method of using a coated article
Refke et al. LPPS thin film: A hybrid coating technology between thermal spray and PVD for functional thin coatings and large area applications
JP2019099921A (ja) 多孔質遮熱コーティングを形成する方法
Tang et al. Novel thermal barrier coatings produced by axial suspension plasma spray
EP3283667A1 (fr) Revêtement dvc contenant du zircone partiellement et totalement stabilisé
JP2018003103A (ja) 遮熱コーティング法及び遮熱コーティング膜並びにタービン部材
Lima et al. Thermal and environmental barrier coatings (TBCs/EBCs) for turbine engines
EP3170918A1 (fr) Revêtement dvc avec du zircone entièrement et partiellement stabilisé
CN103572210A (zh) 一种高温抗氧化铱基纳米晶复合涂层及其制备方法

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20151007

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

DAX Request for extension of the european patent (deleted)
RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: UNITED TECHNOLOGIES CORPORATION

A4 Supplementary search report drawn up and despatched

Effective date: 20161117

RIC1 Information provided on ipc code assigned before grant

Ipc: C23C 4/11 20160101ALI20161111BHEP

Ipc: C23C 28/04 20060101ALI20161111BHEP

Ipc: C23C 4/134 20160101ALI20161111BHEP

Ipc: C23C 28/00 20060101AFI20161111BHEP

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20170804

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20180508

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAJ Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR1

GRAL Information related to payment of fee for publishing/printing deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR3

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

GRAR Information related to intention to grant a patent recorded

Free format text: ORIGINAL CODE: EPIDOSNIGR71

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

INTC Intention to grant announced (deleted)
AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

INTG Intention to grant announced

Effective date: 20181016

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602013047297

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1067614

Country of ref document: AT

Kind code of ref document: T

Effective date: 20181215

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20181121

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1067614

Country of ref document: AT

Kind code of ref document: T

Effective date: 20181121

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190221

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190221

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181121

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181121

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181121

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181121

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190321

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181121

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181121

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190321

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190222

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181121

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181121

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181121

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181121

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181121

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181121

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181121

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181121

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602013047297

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181121

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181230

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181121

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181121

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181121

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181121

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20181231

Ref country code: IE

Ref legal event code: MM4A

26N No opposition filed

Effective date: 20190822

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181121

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181230

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181231

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181231

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181231

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181230

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181121

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20181121

Ref country code: MK

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181121

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20131230

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 602013047297

Country of ref document: DE

Owner name: RAYTHEON TECHNOLOGIES CORPORATION (N.D.GES.D.S, US

Free format text: FORMER OWNER: UNITED TECHNOLOGIES CORP., FARMINGTON, CONN., US

Ref country code: DE

Ref legal event code: R081

Ref document number: 602013047297

Country of ref document: DE

Owner name: RTX CORPORATION (N.D.GES.D. STAATES DELAWARE),, US

Free format text: FORMER OWNER: UNITED TECHNOLOGIES CORP., FARMINGTON, CONN., US

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230520

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 602013047297

Country of ref document: DE

Owner name: RTX CORPORATION (N.D.GES.D. STAATES DELAWARE),, US

Free format text: FORMER OWNER: RAYTHEON TECHNOLOGIES CORPORATION (N.D.GES.D.STAATES DELAWARE), ARLINGTON, VA, US

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20251126

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20251120

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20251120

Year of fee payment: 13