Blade for a turbomachine including blade tip armor and an erosion protection layer, and method for manufacturing same

Patent metadata

Field	Value
Publication number	US-12359573-B2
Application number	US-202117925703-A
Country	US
Kind code	B2
Filing date	Apr 28, 2021
Priority date	May 18, 2020
Publication date	Jul 15, 2025
Grant date	Jul 15, 2025

Abstract

A blade for a turbomachine is provided. The blade at its blade tip ( 4 ) includes blade tip armor ( 5 ), and an erosion protection layer ( 11 ) above the blade tip armor. For the blade, the erosion protection layer in the area of the blade tip has a layer thickness in the range of 5 μm to 100 μm, in particular 10 μm to 50 μm.

First claim

The invention claimed is:

1. A blade for a turbomachine, the blade comprising:
a blade tip including blade tip armor,
wherein the blade tip armor includes a nickel layer with embedded hard material particles or an MCrAlY layer with embedded hard material particles, where M of the MCrAlY layer is a metal; the embedded hard material particles protruding from a surface of the nickel or MCrAlY layer;
an erosion protection layer on the surface of the blade tip and having a layer thickness in the range of 10 μm to 50 μm so that a portion of the hard material particles protrudes beyond the erosion protection layer;
wherein the erosion protection layer includes at least one metal layer and a ceramic layer; and
wherein the erosion protection layer includes multiple repeated, layer sequences of the metal layer and the ceramic layer.

2. The blade as recited in claim 1 wherein the layer thickness is in the range of 15 μm to 35 μm.

3. The blade as recited in claim 1 wherein the blade includes an airfoil, the erosion protection layer, but no blade tip armor, being in the area of the airfoil.

4. The blade as recited in claim 1 wherein the blade tip armor has the MCrAlY layer and M is nickel, cobalt, or iron, and the embedded hard material particles include oxides or carbides or boron nitride.

5. The blade as recited in claim 4 wherein the embedded hard material particles include cubic boron nitride or aluminum oxide.

6. The blade as recited in claim 1 wherein the metal layer of the erosion protection layer includes titanium, platinum, palladium, tungsten, chromium, nickel, or cobalt.

7. The blade as recited in claim 1 wherein the ceramic layer of the erosion protection layer includes at least one oxide, nitride, carbide, or boride of at least one metal of the metal layer.

8. The blade as recited in claim 1 wherein the blade includes a Cr-containing steel, a nickel-based superalloy, an iron-based superalloy, a titanium-based alloy, or a cobalt-based superalloy.

9. A method for manufacturing the blade as recited in claim 1 , the method comprising initially applying the blade tip armor at the blade tip, and subsequently applying the erosion protection layer above the blade tip armor, wherein the application of the blade tip armor takes place via a process from the group including electroplating, soldering, applying a slip layer, physical and chemical vapor deposition, and spraying.

10. The method as recited in claim 9 wherein the process is spraying.

11. The method as recited in claim 10 wherein the spraying is thermal spraying.

12. The method as recited in claim 10 wherein the spraying is plasma-assisted-spraying.

13. The method as recited in claim 9 wherein the blade tip armor includes the MCrAlY layer with embedded hard material particles, where M of the MCrAlY layer is a metal.

Assignees

• MTU Aero Engines AG

Inventors

• Uihlein Thomas
• Stolle Ralf

Classifications

• F01D5/288

  Protective coatings for blades · CPC title

• F01D5/282

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title

• C25D15/00

  Electrolytic or electrophoretic production of coatings containing embedded materials, e.g. particles, whiskers, wires · CPC title

• C25D3/12

  of nickel or cobalt · CPC title

• C23C14/542

  Controlling the film thickness or evaporation rate · CPC title