Method and device for estimating a thickness of a ceramic thermal barrier coating

• US 10,445,434 B2
• Filed: 12/21/2012
• Issued: 10/15/2019
• Est. Priority Date: 12/23/2011
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Safran Aircraft Engine Company
• Inventors: Boheas, Marie-Ange, Hamadi, Sarah, Malie, Andre, Pasquet, Annie
• Primary Examiner(s): Jones, Hugh M
• Application Number:
  US14/368,127
• Publication Number:
  US 20150310133A1
• Time in Patent Office: 2,489 Days
• Field of Search: 703 1
• CPC Class Codes: G06F 17/10 Complex mathematical operations function generation by table look-up G06F1/03; evaluation of elementary functions by calculation G06F7/544
• CPC Class Codes: G06F 30/00 Computer-aided design [CAD]
• CPC Class Codes: G06F 30/23 using finite element methods [FEM] or finite difference methods [FDM]

Abstract

An estimation method for estimating thickness of a ceramic thermal barrier coating that is to be deposited by physical vapor deposition from at least one target and onto a gas turbine hot part mounted on a support tooling, the method including: digitally modeling a geometrical shape of the hot part and its movements relative to the target; representing the modeled hot part as a surface mesh; and estimating, for at least one mesh element of the hot part exposed to the radiation from the target during deposition of the coating, a coating thickness to be deposited on the mesh element at a given instant by using a radiation model modeling radiation from the target and taking account of the position of the mesh element at that given instant relative to the target.

Claims

1. An estimation method for estimating thickness of a ceramic thermal barrier coating that is to be deposited by physical vapor deposition from at least one target and onto a gas turbine hot part mounted on support tooling, the method comprising:

digitally modeling, by a processor, a geometrical shape of the hot part and movements of the hot part relative to the at least one target;

representing, by the processor, the hot part as digitally modeled as a surface mesh;

digitally modeling, by the processor, a geometrical shape of the at least one target;

representing, by the processor, the at least one target as digitally modeled as a surface mesh;

digitally modeling, by the processor, a geometrical shape and a movement of the support tooling for supporting the hot part;

representing, by the processor, the support tooling as digitally modeled as a surface mesh; and

estimating, by the processor, for at least one mesh element of the hot part exposed to radiation from the at least one target during deposition of the coating, a coating thickness to be deposited on the at least one mesh element of the hot part at a given instant by using a radiation model modeling radiation from the at least one target and taking account of a position of the at least one mesh element of the hot part at that given instant relative to the at least one target, the radiation model being defined for a mesh element of the at least one target by;

I(θ

)=I₀[cos(θ

)]ⁿ

wherein;

I(θ

) designates intensity of a ray emitted by the mesh element of the at least one target in a direction at an angle θ

relative to the normal to the mesh element of the at least one target; and

n and I₀ designate predetermined constants.

2. The method according to claim 1, further comprising:

digitally modeling at least one mask configured to prevent a zone of the hot part being exposed to the radiation from the at least one target; and

representing the at least one mask as a surface mesh; and

wherein the mesh elements of the hot part that are taken into consideration during the estimating comprise mesh elements that are not masked at the given instant from the at least one target by mesh elements of the at least one mask during deposition of the coating.

3. The method according to claim 2, wherein the at least one mask comes from an element of the support tooling for supporting the hot part.

4. The method according to claim 3, wherein fineness of the surface mesh varies between at least two among the hot part, the target, the mask, and the support tooling.

5. The method according to claim 1, wherein during the estimating, account is also taken of a loss factor corresponding to rays that are emitted by the at least one target during deposition but that do not reach the hot part.

6. The method according to claim 1, wherein during the surface meshing the modeled hot part, the part is subjected to nonuniform surface meshing.

7. A non-transitory computer-readable data medium storing a computer program including instructions for executing the estimation method according to claim 1.

8. The method according to claim 1, wherein the hot part is a rotor blade of a gas turbine.

9. The method according to claim 1, wherein the hot part is a stator blade of a gas turbine.

10. A device for estimating thickness of a ceramic thermal barrier coating that is to be deposited by physical vapor deposition from at least one target and onto a gas turbine hot part mounted on support tooling, the device comprising:

a processor configured to;

digitally model a geometrical shape of the hot part and movements of the hot part relative to the at least one target;

represent the hot part as digitally modeled as a surface mesh;

digitally model a geometrical shape of the at least one target;

represent the at least one target as digitally modeled as a surface mesh;

digitally model a geometrical shape and a movement of the support tooling for supporting the hot part;

represent the support tooling as digitally modeled as a surface mesh; and

estimate, for at least one mesh element of the hot part exposed to the radiation from the at least one target during deposition of the coating, a coating thickness to be deposited on the at least one mesh element of the hot part at a given instant by using a radiation model modeling radiation from the at least one target and taking account of a position of the at least one mesh element of the hot part at that given instant relative to the at least one target, the radiation model being defined for a mesh element of the at least one target by;

I(θ

)=I₀[cos(θ

)]ⁿ

wherein;

I(θ

) designates intensity of a ray emitted by the mesh element of the at least one target in a direction at an angle θ

relative to the normal to the mesh element of the at least one target; and

n and I₀ designate predetermined constants.

11. An estimation method for estimating thickness of a ceramic thermal barrier coating that is to be deposited by physical vapor deposition from at least one target and onto a gas turbine hot part mounted on support tooling, the method comprising:

digitally modeling, by a processor, a geometrical shape of the hot part and movements of the hot part relative to the at least one target;

representing, by the processor, the hot part as digitally modeled as a surface mesh;

digitally modeling, by the processor, a geometrical shape of the at least one target;

representing, by the processor, the at least one target as digitally modeled as a surface mesh;

digitally modeling, by the processor, at least one mask suitable for preventing a zone of the hot part being exposed to radiation from the at least one target at a given instant;

representing, by the processor, the at least one mask as digitally modeled as a surface mesh, wherein fineness of the surface mesh varies between at least two among the hot part, the target, and the at least one mask; and

estimating, by the processor, for at least one mesh element of the hot part exposed to radiation from the at least one target during deposition of the coating, a coating thickness to be deposited on the at least one mesh element of the hot part at the given instant by using a radiation model modeling radiation from the at least one target and taking account of a position of the at least one mesh element of the hot part at that given instant relative to the at least one target, the radiation model being defined for a mesh element of the at least one target by;

I(θ

)=I₀[cos(θ

)]ⁿ

wherein;

I(θ

) designates intensity of a ray emitted by the mesh element of the at least one target in a direction at an angle θ

relative to the normal to the mesh element of the at least one target; and

n and I₀ designate predetermined constants.

12. The method according to claim 11,

wherein the mesh elements of the hot part that are taken into consideration during the estimating comprise mesh elements that are not masked at the given instant from the at least one target by mesh elements of the at least one mask during deposition of the coating.

13. The method according to claim 11, wherein the at least one mask comes from an element of the support tooling for supporting the hot part.

14. The method according to claim 11, wherein during the estimating, account is also taken of a loss factor corresponding to rays that are emitted by the at least one target during deposition but that do not reach the hot part.

15. The method according to claim 11, wherein during the surface meshing the modeled hot part, the part is subjected to nonuniform surface meshing.

16. A non-transitory computer-readable data medium storing a computer program including instructions for executing the estimation method according to claim 11.

17. The method according to claim 11, wherein the hot part is a rotor blade of a gas turbine.

18. The method according to claim 11, wherein the hot part is a stator blade of a gas turbine.

19. The method according to claim 11, further comprising:

digitally modeling, by the processor, a geometrical shape and a movement of the support tooling for supporting the hot part; and

representing, by the processor, the support tooling as digitally modeled as a surface mesh.

20. A device for estimating thickness of a ceramic thermal barrier coating that is to be deposited by physical vapor deposition from at least one target and onto a gas turbine hot part mounted on support tooling, the device comprising:

a processor configured to;

digitally model a geometrical shape of the hot part and movements of the hot part relative to the at least one target;

represent the hot part as digitally modeled as a surface mesh;

digitally model a geometrical shape of the at least one target;

represent the at least one target as digitally modeled as a surface mesh;

digitally model at least one mask suitable for preventing a zone of the hot part being exposed to radiation from the at least one target at a given instant;

represent the at least one mask as digitally modeled as a surface mesh, wherein fineness of the surface mesh varies between at least two among the hot part, the target, and the at least one mask; and

estimate, for at least one mesh element of the hot part exposed to the radiation from the at least one target during deposition of the coating, a coating thickness to be deposited on the at least one mesh element of the hot part at the given instant by using a radiation model modeling radiation from the at least one target and taking account of a position of the at least one mesh element of the hot part at that given instant relative to the at least one target, the radiation model being defined for a mesh element of the at least one target by;

I(θ

)=I₀[cos(θ

)]ⁿ

wherein;

I(θ

) designates intensity of a ray emitted by the mesh element of the at least one target in a direction at an angle θ

relative to the normal to the mesh element of the at least one target; and

n and I₀ designate predetermined constants.