Ductile compensation layer for brittle components
US-9551231-B2 · Jan 24, 2017 · US
Ductile compensation layer for brittle components
US10267167B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-10267167-B2 |
| Application number | US-201715401483-A |
| Country | US |
| Kind code | B2 |
| Filing date | Jan 9, 2017 |
| Priority date | Aug 10, 2012 |
| Publication date | Apr 23, 2019 |
| Grant date | Apr 23, 2019 |
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- Title
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Abstract
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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.
First claim
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What is claimed is: 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 the 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 Ni 2 MnGa. 4. The blade element of claim 3 , wherein a wear-resistant layer is applied to the envelope region. 5. The blade element of claim 4 , wherein the wear-resistant layer comprises Ti60(Mn,Fe,Cr)25Si5O10. 6. The blade element of claim 4 , wherein the wear-resistant layer comprises Ti45Zr38Ni17. 7. The blade element of claim 4 , wherein the wear-resistant layer comprises Al35Ni20Co20. 8. The blade element of 2 , wherein the envelope material is formed by Al35Ni20Co20. 9. The blade element of claim 8 , wherein a wear-resistant layer is applied to the envelope region. 10. The blade element of claim 9 , wherein the wear-resistant layer comprises Ti60(Mn,Fe,Cr)25Si5O10. 11. The blade element of claim 9 , wherein the wear-resistant layer comprises Ti45Zr38Ni17. 12. The blade element of claim 9 , wherein the wear-resistant layer comprises Al35Ni20Co20. 13. The blade element of claim 1 , wherein a wear-resistant layer is applied to the envelope region. 14. The blade element of claim 13 , wherein the wear-resistant layer is formed by a pseudoelastic or superelastic alloy or by a material based on quasi-crystals. 15. The blade element of claim 13 , wherein the wear-resistant layer comprises Ti60(Mn,Fe,Cr)25Si5O10. 16. The blade element of claim 13 , wherein the wear-resistant layer comprises Ti45Zr38Ni17. 17. The blade element of claim 13 , wherein the wear-resistant layer comprises Al35Ni20Co20. 18. The blade element of claim 1 , wherein the envelope region has a porous form. 19. The blade element of claim 1 , wherein the envelope region has a compact form. 20. The blade element of claim 1 , wherein the fastening element is a blade root and the receptacle is a blade root receptacle.
Assignees
Inventors
Classifications
Ductility · CPC title
- F01D5/3092Primary
Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers (F01D5/288 takes precedence) · CPC title
Shape memory behaviour · CPC title
Nickel-Copper alloy, e.g. Monel · CPC title
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 title
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- What does patent US10267167B2 cover?
- 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 …
- Who is the assignee on this patent?
- MTU Aero Engines AG
- What technology area does this patent fall under?
- Primary CPC classification F01D5/3092. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Apr 23 2019 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 2 related publications on this page (citations in our corpus or others sharing the same primary CPC).