DUCTILE COMPENSATION LAYER FOR BRITTLE COMPONENTS

• US 20140044549A1
• Filed: 08/09/2013
• Published: 02/13/2014
• Est. Priority Date: 08/10/2012
• Status: Active Grant

• Current Assignee: MTU Aero Engines AG (MTU)
• Original Assignee: MTU Aero Engines AG (MTU)
• Inventors: Steinhardt, Erich, Smarsly, Wilfried, Werner, Andr
• Granted Patent: US 9,551,231 B2
• Time in Patent Office: Days
• US Class Current: 416/219.R
• CPC Class Codes: F01D 5/02 Blade-carrying members, e.g. rotors rotors of non-bladed type F01D1/34; stators F01D9/00 ; selecting particular materials F01D5/28
• CPC Class Codes: F01D 5/12 Blades specially adapted for radial flow machines or engines F01D5/04; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02
• CPC Class Codes: F01D 5/3007 of axial insertion type
• CPC Class Codes: F01D 5/3092 Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers F01D5/288 takes precedence
• CPC Class Codes: F05D 2300/1723 Nickel-Copper alloy, e.g. Monel
• CPC Class Codes: F05D 2300/173 Aluminium alloys, e.g. AlCuMgPb
• CPC Class Codes: F05D 2300/174 Titanium alloys, e.g. TiAl
• CPC Class Codes: F05D 2300/501 Elasticity
• CPC Class Codes: F05D 2300/505 Shape memory behaviour
• CPC Class Codes: F05D 2300/514 Porosity
• CPC Class Codes: F05D 2300/518 Ductility
• CPC Class Codes: F05D 2300/702 Reinforcement
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

Disclosed is a blade element of a turbomachine, in particular of a gas turbine, which comprises a fastening element (10) with which the blade element is arranged in a receptacle (11) of the turbomachine. In the region of the fastening element, the blade element has a core region (18) and an envelope region (19) which at least partially envelops the core region. The core region is formed from a blade base material which is more brittle than the envelope material of the envelope region, and the envelope region is formed by a coating. The envelope material is a blade base material which has been modified to achieve a higher ductility or is a pseudoelastic or superelastic material.

Claims

1. A blade element of a turbomachine, wherein the blade element comprises a fastening element with which the blade element is arranged in a receptacle of the turbomachine and comprises, in a region of the fastening element, a core region and an envelope region which at least partially envelops the core region, the core region being formed of a blade base material which is more brittle than an envelope material of the envelope region and the envelope region being formed by a coating, and wherein the envelope material is a blade base material which has been modified to achieve a higher ductility or is a pseudoelastic or superelastic material.

2. The blade element of claim 1, wherein the envelope material is formed by a pseudoelastic or superelastic alloy based on Co—

Ni—

Al, Co—

Ni—

Ga, Al—

Ni—

Co or Ni—

Mn—

Ga.

3. The blade element of claim 2, wherein the envelope material is formed by Al35Ni20Co20 or Ni₂MnGa.

4. The blade element of claim 1, wherein a wear-resistant layer is applied to the envelope region.

5. The blade element of claim 4, wherein the wear-resistant layer is formed by a pseudoelastic or superelastic alloy or by a material based on quasi-crystals.

6. The blade element of claim 4, wherein the wear-resistant layer comprises Ti60(Mn,Fe,Cr)25Si5O10, Ti45Zr38Ni17 or Al35Ni20Co20.

7. The blade element of claim 1, wherein the envelope region has a porous from.

8. The blade element of claim 1, wherein the envelope region has a compact form.

9. The blade element of claim 1, wherein the fastening element is a blade root and the receptacle is a blade root receptacle.

10. The blade element of claim 1, wherein the blade base material is a TiAl material.

11. A turbomachine, wherein the turbomachine comprises a blade element and a receptacle in which the blade element is arranged, the blade element comprising a fastening element with which the blade element is arranged in the receptacle of the turbomachine, and the blade element comprising a blade base material in a region of the fastening element, and wherein in a region of a contact surface with the fastening element, the receptacle comprises a receptacle surface which is formed from a receptacle surface material that has a higher ductility than the blade base material.

12. The turbomachine of claim 11, wherein the receptacle surface is formed by a coating.

13. The turbomachine of claim 11, wherein the receptacle surface is formed by a blade base material which has been modified to achieve a higher ductility, an Ni-based alloy, a Co-based alloy or by a pseudoelastic or superelastic material.

14. The turbomachine of claim 11, wherein the receptacle surface is formed by a pseudoelastic or superelastic alloy based on Co—

Ni—

Al, Co—

Ni—

Ga, Al—

Ni—

Co or Ni—

Mn—

Ga.

15. The turbomachine of claim 11, wherein the receptacle surface is formed by Al35Ni20Co20 or Ni₂MnGa.

16. The turbomachine of claim 11, wherein the receptacle surface has a porous form.

17. The turbomachine of claim 11, wherein the receptacle surface has a compact form.

18. The turbomachine of claim 11, wherein the fastening element is a blade root and the receptacle is a blade root receptacle and/or the blade base material is a TiAl material.

19. A process for producing a turbomachine, which process comprises providing a receptacle in which a blade element can be arranged, the blade element comprising a fastening element with which the blade element is arranged in the receptacle of the turbomachine and the blade element comprising a blade base material in a region of the fastening element, and further comprises coating by kinetic cold gas spraying, a thermal spraying process or by vapor deposition the receptacle in a region of a contact surface with the fastening element with a receptacle surface material that has a higher ductility than the blade base material.

20. A process for producing a blade element of a turbomachine, wherein the process comprises providing a blade main body comprising a fastening element with which the blade element can be arranged in a receptacle of the turbomachine, the blade main body being formed from a blade base material, an envelope region being arranged on the blade main body by coating, which envelope region comprises an envelope material having a higher ductility than the blade base material of the blade main body and being a blade base material which has been modified to achieve a higher ductility or being a pseudoelastic or superelastic material, which envelope material is applied by kinetic cold gas spraying, a thermal spraying process or by vapor deposition.