Ceramic Matrix Composite Mid Turbine Frame Segmentation
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Solution Overview
Problem
Turbine center frames in gas turbines face challenges with high mechanical and thermal loads, leading to weight and load transmission issues, which conventional metallic components struggle to address effectively.
Innovation Solution
The use of ceramic fiber composite materials for outer and inner wall elements, along with strut cladding elements, which are coupled to different structural components to reduce load transfer, and the incorporation of sealing arrangements with deformable fillings to manage thermal and mechanical displacements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If metallic cladding elements are used to connect outer and inner wall elements, then structural strength is improved, but weight increases and load transfer to other components worsens
Solution Approach 1:
The patent applies composite materials by using ceramic matrix composite (CMC) materials for the cladding elements instead of conventional metallic materials. This substitution maintains the required structural strength while significantly reducing the weight of the turbine intermediate casing components.
Solution Approach 2:
The patent segments the cladding structure into separate outer wall elements and inner wall elements that are not directly connected. The CMC cladding elements connect these segmented parts, allowing each to be supported by different structural components (outer casing and support structure respectively), thereby reducing load transfer while maintaining structural integrity.
2Stability of the object's composition
If metallic cladding elements are used to connect outer and inner wall elements, then structural integrity is improved, but load transfer to outer casing worsens
Solution Approach 1:
The patent segments the cladding structure into separate outer wall elements and inner wall elements that are not directly connected. The CMC cladding elements connect these segmented parts, allowing each to be supported by different structural components (outer casing and support structure respectively), thereby reducing load transfer while maintaining structural integrity.
Solution Approach 2:
The CMC cladding elements act as intermediary components between the outer wall elements and inner wall elements. These intermediaries enable the connection of wall elements to different support structures while minimizing the direct transfer of mechanical and thermal loads between adjacent components.
3Weight of moving object
If CMC components are used, then weight is reduced, but usable strength decreases due to less favorable failure characteristics
Solution Approach 1:
The patent segments the cladding structure into separate outer wall elements and inner wall elements. This segmentation allows each CMC component to be optimized for its specific location and load conditions, maximizing the usable strength of each element while maintaining overall structural integrity.
Solution Approach 2:
The patent applies composite materials by using ceramic matrix composite (CMC) materials for the cladding elements instead of conventional metallic materials. This substitution maintains the required structural strength while significantly reducing the weight of the turbine intermediate casing components.
4Stability of the object's composition
If outer and inner wall elements are connected rigidly, then structural stability is improved, but thermal and mechanical load transfer worsens
Solution Approach 1:
The patent segments the cladding structure into separate outer wall elements and inner wall elements that are not directly connected. The CMC cladding elements connect these segmented parts, allowing each to be supported by different structural components (outer casing and support structure respectively), thereby reducing load transfer while maintaining structural integrity.
Solution Approach 2:
The patent changes the material parameter from conventional metallic materials to ceramic matrix composite (CMC) materials for the cladding elements. This material parameter change enables the structure to better withstand thermal and mechanical stresses while reducing the transfer of these loads between components.
Data Source
Figure 1
Figure 2
Figure 3~4
AI summary
The invention relates to a turbine intermediate casing (10) for a gas turbine, in particular an aviation gas turbine, comprising: several outer wall elements (22) arranged successively in the circumferential direction; several inner wall elements (24) arranged successively in the circumferential direction, wherein the outer wall elements (22) and the inner wall elements (24) define a flow channel (20) for exhaust gas by means of their mutually facing inner surfaces; several strut cladding elements (38) arranged in the radial direction (RR) between a respective outer wall element (22) and a respective inner wall element (24); an outer casing (14) surrounding the outer wall elements (22) and the inner wall elements (24); and an annular support structure (18) surrounding a bearing area of a shaft (12) of the gas turbine, in particular the shaft of the high-pressure turbine, wherein the strut cladding elements (38) are designed such thatthat they have a receiving space (46) for receiving support elements (16) which extend from the annular retaining structure (18) in a substantially radial direction (RR) to the outer housing (14) through the flow channel (20), so that exhaust gas flowing through the flow channel (20) is guided around the support elements (16) by the strut cladding elements (38). According to the invention, it is proposed that the outer wall elements (22), the inner wall elements (24) and the strut cladding elements (38) are at least partially made of ceramic fiber composite materials (CMC), wherein the outer wall elements (22) are configured to be coupled to the outer housing (14), and wherein the inner wall elements (24) are configured to be coupled to the annular retaining structure (18).