Blade or vane for turbomachine with different diffusion protective coatings and method for manufacture thereof

Patent metadata

Field	Value
Publication number	US-10914181-B2
Application number	US-201816051927-A
Country	US
Kind code	B2
Filing date	Aug 1, 2018
Priority date	Aug 4, 2017
Publication date	Feb 9, 2021
Grant date	Feb 9, 2021

Abstract

The present invention relates to a blade or vane for a turbomachine, particularly for an aircraft engine, with a blade element for interacting with the flow medium, wherein the blade has different diffusion protective coatings in various regions on its surface for protection against corrosion and/or oxidation, wherein the diffusion protective coatings are produced by chromizing and/or aluminizing, wherein the blade element is divided into two regions along the longitudinal axis of the blade element, wherein the first region extends over 80 to 95% of the length of the blade element, and the second region extends over the remainder of the length of the blade element, and wherein in both regions, an AlCr diffusion protective coating is applied, and wherein in one of the regions, the AlCr diffusion protective coating has a higher Cr content.

First claim

What is claimed is:

1. A blade or vane for a turbomachine, comprising:
a blade element for interacting with a flow medium, wherein the blade or vane has different diffusion protective coatings in various regions on its surface for protection against corrosion and/or oxidation, wherein the diffusion protective coatings are produced by chromizing and/or aluminizing;
wherein the blade element is divided into two regions along the longitudinal axis of the blade element, wherein the first region extends over 80 to 95% of the length of the blade element, and the second region extends over the remainder of the length of the blade element, and wherein in both regions, an AlCr diffusion protective coating is applied, and wherein in one of the regions, the AlCr diffusion protective coating has a higher Cr content, and
wherein at one end of the blade element, the blade or vane has a shroud, which has the same diffusion protective coating as the adjacent region of the blade element.

2. The blade or vane according to claim 1 , wherein the blade or vane has a blade root for arrangement in a disc of the turbomachine, a blade platform between blade root and blade element for covering the blade root, and a blade neck between blade root and blade element, in the region of which is arranged on the blade platform, wherein an AlCr diffusion protective coating with a Cr percentage that is higher than in the AlCr diffusion protective coatings of the first and second regions of the blade element is formed on the blade platform, whereas Cr diffusion protective coatings are applied in the region of the blade root and the blade neck.

3. The blade or vane according to claim 2 , wherein the blade or vane is a rotating blade and the shroud is arranged at the blade tip at the end of the blade element that faces away from the blade root.

4. The blade or vane according claim 2 , wherein the AlCr diffusion protective coating, on the blade platform, has an Al percentage of greater than or equal to 5 wt. % and a Cr percentage of 35 to 85 wt. %, wherein the ratio of chromium to aluminum lies in the range of greater than or equal to 3.

5. The blade or vane according to claim 2 , wherein the Cr diffusion protective coating has a thickness in the range of 0.015 to 0.03 mm at the blade root.

6. The blade or vane according to claim 1 , wherein the first region extends over 90% of the length of the blade element and is arranged adjacent to the shroud.

7. The blade or vane according to claim 1 , wherein, in the second region of the blade element, the AlCr diffusion protective coating has a higher Cr percentage than in the first region of the blade element.

8. The blade or vane according to claim 1 , wherein the AlCr diffusion protective coating, in the first region of the blade element, has an Al percentage of 16 to 28 wt. % and a Cr percentage of at least 5 wt. %, wherein the ratio of chromium to aluminum lies in the range of less than or equal to 2, particularly in the range of less than or equal to 1.5.

9. The blade or vane according to claim 1 , wherein the AlCr diffusion protective coating, in the second region of the blade element, has an Al percentage of 12 to 28 wt. % and a Cr percentage of 24 to 85 wt. %, wherein the ratio of chromium to aluminum lies in the range of greater than or equal to 1.3 to less than or equal to 4.4.

10. The blade or vane according to claim 1 , wherein the different diffusion protective coatings have as remainder, in addition to Cr and/or Al, constituents of a base alloy.

11. The blade or vane according to claim 1 , wherein the different diffusion protective coatings have a thickness in the range of 0.015 to 0.1 mm and the AlCr diffusion protective coatings have a thickness in the range of 0.04 to 0.1 mm.

12. The blade or vane according to claim 1 , wherein the blade or vane is a semi-finished blade that is chromized and/or aluminized.

Assignees

• MTU Aero Engines AG

Inventors

• Stanka Rudolf
• Dopfer Manfred

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2300/132

  Chromium · CPC title

• F05D2260/95

  Preventing corrosion · CPC title

• F05D2300/121

  Aluminium · CPC title

• F05D2230/90

  Coating; Surface treatment · CPC title