IPC分类号：
B22F3/00 | B28B1/00 | B33Y80/00 | C04B35/76 | B22F10/60 | B22F10/64 | B28B23/02 | B22F5/00 | B22F5/12 | B22F10/28 | B22F10/80
国民经济行业分类号：
C3516 | C3252 | C3251 | C3393
当前申请(专利权)人：
SIEMENS ENERGY GLOBAL GMBH & CO. KG
原始申请(专利权)人：
SIEMENS AKTIENGESELLSCHAFT
摘要：
A Composite material (10) for an application in a turbo machine (100) is presented. The composite material (10) comprises a metallic lattice (1) and a ceramic matrix (2), wherein the metallic lattice (1) pervades the ceramic matrix (2), thereby mechanically reinforcing the ceramic matrix (2) against thermal and/or mechanical loads in an application of the composite material (10).
技术功效语段：
[0013]By these means, it may - with the aid of additive manufacturing technology - be achieved that particularly the metallic lattice holds together the whole composite material e.g. composed of the lattice and the matrix. This is e.g. achieved in a way such that a delamination, breakage or cracking of ceramic parts off the composite material is avoided. As a consequence, secondary damage of the turbine may be also prevented, e.g. damage of heat shields of the gas turbine.
[0016]In an embodiment, the metallic lattice is or comprises an irregular mesh-like structure which is configured such that it avoids peeling of parts from the composite material during thermal and/or mechanical loads in an operation of the composite material.
[0018]In an embodiment the coefficient of thermal expansion of the material of the metallic lattice and that one of the ceramic matrix is chosen to be similar, preferably approximately equal. A difference in thermal expansion coefficients of the metallic lattice on one side and the ceramic on the other side shall at least be comparably small. This embodiment allows for a design of the composite material, wherein the ceramic as well as the metallic lattice are awarded with similar thermal expansion behaviour.
[0020]The metallic lattice is - at least to a predetermined or certain extent - (freely) movable or slidable within the ceramic matrix, thus allowing some mutual movement, slide of freedom between the metallic lattice and the ceramic matrix, which may be necessary to compensate for different thermal expansion behavior of the mentioned materials. Said movement may relate to one, two or three independent spatial dimensions. This embodiment advantageously allows to provide a play of free spaces in which parts of the composite material may expand. This may, in turn, prevent the whole composite material from breakage or cracking, as stresses in the material may systematically be reduced.
权利要求：
1. Composite material (10) for application in a turbo machine (100), such as a gas turbine, the composite material (10) comprising a metallic lattice (1) and a ceramic matrix (2), wherein the metallic lattice (1) pervades the ceramic matrix (2), thereby mechanically reinforcing the ceramic matrix (2) against thermal and/or mechanical loads in an operation of the composite material (10), wherein the metallic lattice (1) is - to a predetermined extent - movable or slidable within or relative to the ceramic matrix (2), thus allowing some mutual movement of these components, e.g. due to different thermal expansion behaviour, characterized in that the composite material further comprises internal cavities (4) serving for providing spaces or play which receives a thermal expansion of parts of the composite material, preferably the ceramic matrix.
2. Composite material (10) according to claim 1, wherein the metallic lattice (1) comprises a regular mesh-like structure which is configured such that it avoids peeling of parts from the composite material (10) during thermal and/or mechanical loads in an operation of the composite material (10) .
3. Composite material (10) according to claim 1 or 2, wherein the metallic lattice (1) comprises an irregular mesh-like structure which is configured such that it avoids peeling of parts from the composite material (10) during thermal and/or mechanical loads in an operation of the composite material (10).
4. Composite material (10) according to one of the previous claims, wherein a coefficient of thermal expansion of the material of the metallic lattice (1) and that one of ceramic matrix (2) is chosen to be similar.
5. Composite material (10) according to one of the previous claims, wherein the metallic lattice (1) and the ceramic matrix (2) are joined by positive locking to one another.
6. Heat shield (20) for a turbo machine (100), particularly a part of a combustion chamber of a gas turbine, comprising the composite material (10) according to one of the previous claims.
7. Method to manufacture a composite material (10) according to one of claims 1 to 6, comprising the steps of: - a) additively manufacturing the metallic lattice (1), e.g. by selective laser melting or electron beam melting, - b) infiltrating the metallic lattice (1) by a ceramic base material such that an inside of the metallic lattice (1) is only partly filled such that cavities (4) in the composite material (10) remain which may - in an operation of the composite material (10) - receive thermal expansion of the lattice material (1), and - c) solidifying, such as sintering the infiltrated metallic lattice (1), wherein the ceramic base material is solidified and the composite material (10) is formed.