Turbine Cladding Element Reinforcement Geometry
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Solution Overview
Problem
Existing cladding elements for turbine center frames face challenges in achieving sufficient rigidity with minimal material usage while minimizing thermally induced stresses, which are often high due to the connection of stiffening ribs to edge sections.
Innovation Solution
A cladding element design featuring a reinforcement element with a straight first section and an inclined or curved second section, arranged within the outer surface, avoiding direct connection to the connection and edge portions, thereby reducing thermal stresses and optimizing material usage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If stiffening ribs are connected to edge sections of the cladding element, then component stiffness is improved, but thermally induced stresses increase
Solution Approach 1:
The harmful connection points between stiffening ribs and edge sections are extracted/removed from the design. The reinforcing element is positioned entirely within the central section, eliminating direct connections to edge sections and connection sections, thereby removing the source of high thermally induced stresses while maintaining structural stiffness through the distributed reinforcement geometry
Solution Approach 2:
The reinforcing element acts as an intermediary structure that provides stiffness without directly connecting to the edge sections. By positioning the reinforcement within the central section and allowing it to terminate smoothly at the outer surface, the design mediates between the need for stiffness and the need to avoid thermal stress concentration at connections
2Stability of the object's composition
If stiffening ribs extend along the entire component, then component stiffness is improved, but material consumption increases
Solution Approach 1:
The reinforcing element is positioned locally within the central section where it is most effective for maintaining stiffness, rather than extending along the entire component. The geometry is optimized to provide maximum structural benefit with minimum material, concentrating the reinforcement where needed while avoiding unnecessary material in other areas
Solution Approach 2:
The reinforcing element is segmented into multiple sections (first reinforcing section extending axially, second reinforcing section extending radially) that work together to provide stiffness. This segmentation allows the structure to achieve the required rigidity through geometric configuration rather than through continuous material extension
Data Source
Figure 1~2
Figure 3~4
AI summary
The invention relates to a cladding element for a hot gas-carrying channel of a turbine intermediate casing of a gas turbine, in particular an aircraft gas turbine, comprising a first axially forward connection section (12; 112), a second axially rear connection section (14; 114), a central section (16; 116) which is connected to the first connection section (12; 112) and the second connection section (14; 114) and is arranged in the axial direction (AR) between them, wherein the central section (16; 116) has an outer surface (20; 120) facing away from the channel, and wherein the first connection section (12; 112) can be coupled to axially forward components of the turbine intermediate casing or the gas turbine and the second connection section (14; 114) can be coupled to axially rear components of the turbine intermediate casing or the gas turbine.According to the invention, it is proposed that the central section (16; 116) has at least one first reinforcing section (24; 124) projecting away from the channel, which extends substantially in a straight line between an axially forward end (28) and an axially rear end, wherein a second reinforcing section (26; 126) projecting away from the channel is connected to at least one of the two axial ends, which is inclined or curved relative to the straight course of the first reinforcing section (24; 124), wherein the first reinforcing section (24; 124) and the second reinforcing section (26; 126) together form a reinforcing element (22; 122), wherein the entire reinforcing element (22; 122) is arranged within the outer surface (20; 120) of the central section (16; 116), in particular such that the reinforcing element (22; 122) is connected to the first connecting section (12; 112) and has a distance to the second connecting section (14; 114).