阅读说明：本技术 具有由钼-碳化钛复合材料制成的接合层的陶瓷材料复合体、部件、燃气涡轮机和方法 (Ceramic material composite body with a bonding layer made of a molybdenum-titanium carbide composite material, component, gas turbine and method ) 是由 J·D·延森 O·施蒂尔 G·温克勒 于 2019-01-14 设计创作，主要内容包括：本发明涉及材料复合体(1),其具有第一层(2)和布置在第一层(2)上的第二层(3),所述第一层至少由陶瓷第一材料形成,所述第二层至少由不同于第一材料的陶瓷第二材料形成。为了实现更高的可热负荷性和/或可机械负荷性,设置了布置在第一层(2)和第二层(3)之间并且至少部分由钼-碳化钛复合材料形成的接合层(4),通过该接合层将第一层(2)与第二层(3)接合。(The invention relates to a composite body (1) comprising a first layer (2) which is formed from at least a first ceramic material and a second layer (3) which is arranged on the first layer (2) and which is formed from at least a second ceramic material which is different from the first material. In order to achieve a higher thermal and/or mechanical load-bearing capacity, a bonding layer (4) which is arranged between the first layer (2) and the second layer (3) and is formed at least partially from a molybdenum/titanium carbide composite is provided, by means of which bonding layer the first layer (2) is bonded to the second layer (3).)

1. A material composite (1) comprising:

-a first layer (2) formed at least of a ceramic first material; and

-a second layer (3) arranged on the first layer (2) and formed at least of a ceramic second material different from the first material;

characterized by a bonding layer (4) arranged between the first layer (2) and the second layer (3) and formed at least in part of a molybdenum-titanium carbide composite, by means of which bonding layer the first layer (2) is bonded to the second layer (3).

2. The material composite (1) according to claim 1, characterized in that the joining layer (4) is in direct contact with both the first layer (2) and with the second layer (3).

3. The material composite (1) according to claim 1 or 2, characterised in that the joining layer (4) is joined to both the first layer (2) and the second layer (3) by at least one respective material-fit joining.

4. The material composite (1) according to claim 3, characterised in that the joining layer (4) is joined in a direct material-fit manner to the first layer (2) and/or to the second layer (3).

5. The material composite (1) according to one of the preceding claims, characterized in that a first diffusion barrier layer (5) is arranged between the first layer (2) and the joining layer (4) and/or a second diffusion barrier layer (6) is arranged between the second layer (3) and the joining layer (4).

6. The material composite (1) according to claim 5, characterised in that the first diffusion barrier layer (5) and/or the second diffusion barrier layer (6) are formed at least from aluminium oxide.

7. The material composite (1) according to claim 5 or 6, characterized in that the first diffusion barrier layer (5) is applied to the first layer (2) by means of atomic layer deposition and/or the second diffusion barrier layer (6) is applied to the bonding layer (4) by means of atomic layer deposition.

8. The material composite (1) according to one of the preceding claims, characterized in that the first material is a ceramic fiber composite, in particular formed at least by ceramic fibers (20) and a ceramic matrix (21) in which the fibers (20) are embedded.

9. The material composite (1) according to one of the preceding claims, characterized in that the second material has a higher heat and/or corrosion resistance than the first material.

10. The material composite (1) according to any one of the preceding claims, wherein the second material is formed from yttrium stabilized zirconia.

11. Component (11) formed at least from a material composite (1) according to one of the preceding claims.

12. Component (11) according to claim 11, characterized in that the component (11) has at least one carrier (7) which is at least partially equipped with the material composite (1) as a heat shield (13).

13. Component (11) according to claim 11 or 12, characterized in that the carrier (7) is formed of a third material, in particular a metallic material, which is different from the first and second materials.

14. Gas turbine (10) with a component (11) according to any of claims 11 to 13.

15. A method for producing a material composite (1), wherein at least a first layer (2) is produced from a first ceramic material and at least a second layer (3) arranged on the first layer (2) is produced from a second ceramic material different from the first material,

it is characterized in that

A bonding layer (4) which is at least partially formed from a molybdenum-titanium carbide composite is arranged between the first layer (2) and the second layer (3), by means of which bonding layer the first layer (2) is bonded to the second layer (3).