Gas turbine engine article with serpentine groove for coating interlock

Patent metadata

Field	Value
Publication number	US-11828196-B2
Application number	US-202217587246-A
Country	US
Kind code	B2
Filing date	Jan 28, 2022
Priority date	Jan 28, 2022
Publication date	Nov 28, 2023
Grant date	Nov 28, 2023

Abstract

A gas turbine engine article includes a substrate that has a pre-bond surface that includes a serpentine groove. A coating is disposed on the pre-bond surface and mechanically interlocks with the serpentine groove.

First claim

What is claimed is:

1. A gas turbine engine article comprising:
a substrate including a pre-bond surface having a serpentine groove, the serpentine groove being of continuous length from a first groove end to a second groove end, the serpentine groove having a groove floor, and the groove floor includes dimples that are spaced apart from each other along the continuous length; and
a coating disposed on the surface and mechanically interlocking with the serpentine groove.

2. The gas turbine engine article as recited in claim 1 , wherein the serpentine groove is of continuous length from a first groove end to a second groove end.

3. The gas turbine engine article as recited in claim 2 , wherein the serpentine groove includes a plurality of bends of at least 180 degrees.

4. The gas turbine engine article as recited in claim 3 , wherein the plurality of bends has at least 20 bends.

5. The gas turbine engine article as recited in claim 2 , wherein the serpentine groove is of uniform width over the continuous length.

6. The gas turbine engine article as recited in claim 5 , wherein the serpentine groove is of uniform depth over the continuous length.

7. The gas turbine engine article as recited in claim 6 , wherein a ratio of the uniform depth to the uniform width is 2:1 or less.

8. The gas turbine engine article as recited in claim 5 , wherein the serpentine groove defines coils, and the coils are uniformly spaced apart by a pitch distance.

9. The gas turbine engine article as recited in claim 8 , wherein the pitch distance is substantially equal to the uniform width.

10. The gas turbine engine article as recited in claim 5 , wherein the uniform width is from 10 micrometers to 200 micrometers.

11. The gas turbine engine article as recited in claim 5 , wherein the uniform width is from 20 micrometers to 100 micrometers.

12. The gas turbine engine article as recited in claim 1 , wherein the serpentine groove has a sine wave profile.

13. The gas turbine engine article as recited in claim 1 , wherein the coating includes an intermetallic layer and a ceramic layer.

14. The gas turbine engine article as recited in claim 1 , where the pre-bond surface has a Young's contact angle θ Y of approximately 60° and a fraction of the pre-bond surface wetted versus unwetted is at least 0.7.

15. A gas turbine engine comprising:
a compressor section;
a combustor in fluid communication with the compressor section; and
a turbine section in fluid communication with the combustor, the turbine section including articles that each comprise:
a substrate including a pre-bond surface having a serpentine groove, the serpentine groove having a sine wave profile, and
a coating disposed on the pre-bond surface and mechanically interlocking with the serpentine groove.

16. The gas turbine engine as recited in claim 15 , wherein the serpentine groove is of continuous length from a first groove end to a second groove end, the serpentine groove includes a plurality of bends of at least 180 degrees, and the plurality of bends has at least 20 bends.

17. The gas turbine engine as recited in claim 16 , wherein the serpentine groove is of uniform width and of uniform depth over the continuous length, and a ratio of the uniform depth to the uniform width is 2:1 or less.

18. The gas turbine engine as recited in claim 17 , wherein the serpentine groove defines coils, the coils are uniformly spaced apart by a pitch distance, and the pitch distance is substantially equal to the uniform width.

19. The gas turbine engine as recited in claim 15 , wherein the serpentine groove has a groove floor, and the groove floor includes dimples that are spaced apart from each other along the continuous length.

20. A gas turbine engine article comprising:
a substrate including a pre-bond surface having a serpentine groove, the pre-bond surface having a Young's contact angle θ Y of approximately 60° and a fraction of the pre-bond surface wetted versus unwetted is at least 0.7; and
a coating disposed on the surface and mechanically interlocking with the serpentine groove.

Assignees

• Raytheon Tech Corp
• Rtx Corp

Inventors

• Wang Zhigang
• El-Wardany Tahany
• Tang Xia
• Srinivasan Gajawalli V
• Ruglio Anthony G
• Fang Xiaomei

Classifications

• F01D5/288 Primary

  Protective coatings for blades · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F05D2250/184

  sinusoidal · CPC title

• F05D2250/185

  serpentine-like · CPC title

• F05D2300/611

  Coating · CPC title