Flow element and method for coating a flow element

Patent metadata

Field	Value
Publication number	US-10488045-B2
Application number	US-201716081046-A
Country	US
Kind code	B2
Filing date	Feb 27, 2017
Priority date	Mar 1, 2016
Publication date	Nov 26, 2019
Grant date	Nov 26, 2019

Abstract

A flow element for fluidic contact with a hot gas flow inside an aircraft engine includes: a base material, which has a hot gas surface that faces the gas flow and a remote surface that is remote from the gas flow, the base material being completely surrounded by a chroming layer on the hot gas surface and on the remote surface; an adhesive layer on the chroming layer in first portions; an alitising layer, the alitising layer being arranged on the adhesive layer in the first portions; and a thermal barrier layer being arranged on the alitising layer in the first portions. The alitising layer is arranged on the chroming layer in second portions that do not have an adhesive layer, the chroming layer and the alitising layer forming a chroming-alitising layer in the second portions.

First claim

The invention claimed is:

1. A flow element for fluidic contact with a hot gas flow inside an aircraft engine, the flow element comprising:
a base material that comprises a hot gas surface that faces the hot gas flow, and a remote surface that is remote from the hot gas flow, the base material being completely surrounded by a chroming layer on the hot gas surface and on the remote surface;
an adhesive layer on the chroming layer in first portions;
an alitising layer, the alitising layer being arranged on the adhesive layer in the first portions; and
a thermal barrier layer being arranged on the alitising layer in the first portions,
wherein the alitising layer is arranged on the chroming layer in second portions comprising no said adhesive layer, the chroming layer and the alitising layer forming a chroming-alitising layer in the second portions;
wherein the first portions are at the hot gas surface and the second portions are at the remote surface.

2. The flow element according to claim 1 , wherein, in the chroming-alitising layer, a Cr content is higher than an Al content.

3. The flow element according to claim 1 , wherein, in the chroming-alitising layer, an Al content is less than 20 wt. %.

4. A method for coating a flow element for an aircraft engine, the flow element comprising a base material, the method comprising:
the base material comprises a hot gas surface that faces a hot gas flow, and a remote surface that is remote from the hot gas flow, the base material being completely surrounded by a chroming layer on the hot gas surface and on the remote surface;
in a first method step, the base material of the flow element is completely coated with the chroming layer;
in a second method step, the chroming layer is coated in part with an adhesive layer in first portions; and
in a third method step, the chroming layer and the adhesive layer are completely coated with an alitising layer;
wherein the alitising layer is arranged on the chroming layer in second portions comprising no said adhesive layer, the chroming layer and the alitising layer forming a chroming-alitising layer in the second portions;
wherein the first portions are at the hot gas surface and the second portions are at the remote surface.

5. The method according to claim 4 , further comprising, in a fourth method step, partial coating with a thermal barrier layer is carried out.

6. The method according to claim 5 , wherein the coating of the second method step and of the fourth method step is carried out in the first portions.

7. The method according to claim 4 , wherein the first method step is carried out using chemical vapour deposition.

8. The method according to claim 4 , wherein the second method step is carried out using thermal spraying.

9. The method according to claim 4 , wherein the third method step is carried out using chemical vapour deposition.

10. The method according to claim 5 , wherein the fourth method step is carried out using thermal spraying or using physical vapour deposition using an electron beam.

Assignees

• Lufthansa Technik Ag

Inventors

• Peters Jan Oke
• Gartner Thomas
• Winter Oliver
• Kuntzagk Stefan
• Luebcke Tim

Classifications

• F23M2900/05004

  Special materials for walls or lining · CPC title

• F23R3/002 Primary

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F23M5/00

  Casings; Linings; Walls · CPC title

• F16L59/029

  layered · CPC title

• F01D5/288

  Protective coatings for blades · CPC title