Turbine Intermediate Casing Centering with Segmented Support Sections
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Solution Overview
Problem
The use of ceramic fiber composite materials in turbine center frames poses challenges in creating narrow radial grooves without compromising component strength, which is necessary for effective centering and preventing radial opening and swinging.
Innovation Solution
The implementation of first and second support sections on each component, spaced apart in the circumferential direction, which act on the centering element from different sides to secure centering over the entire circumference, eliminating the need for continuous radial grooves and allowing production from ceramic fiber composite materials.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If narrow radial grooves are incorporated into ceramic fiber composite components for centering, then centering precision is improved, but component strength deteriorates
Solution Approach 1:
The patent divides the centering function into multiple discrete support sections (first support sections and second support sections) distributed around the circumference, rather than using a continuous narrow groove. Each support section provides localized centering contact with the centering element, achieving precise centering while maintaining component strength by avoiding continuous material removal.
2Weight of moving object
If ceramic fiber composite materials are used in turbine center frames, then weight is reduced and efficiency is improved, but ease of manufacture deteriorates due to difficulty in creating narrow grooves
Solution Approach 1:
The centering structure is segmented into multiple discrete support sections that can be manufactured as separate features on ceramic fiber composite components. This segmentation avoids the need for difficult continuous groove machining or molding operations, making the components more manufacturable while retaining the weight benefits of ceramic materials.
Solution Approach 2:
The patent transitions from a radial groove approach (one-dimensional feature) to a circumferentially distributed support section approach (two-dimensional arrangement). This dimensional change allows the centering function to be achieved through the component's existing circumferential structure rather than requiring difficult radial material removal or groove formation in the ceramic composite.
3Reliability
If continuous radial grooves are used for centering, then centering reliability is improved, but component strength deteriorates
Solution Approach 1:
The patent replaces the continuous radial groove with multiple discrete support sections distributed around the circumference. Each support section provides reliable centering contact independently, and their collective arrangement ensures stable centering throughout rotation without compromising the continuous integrity of the component structure.
Solution Approach 2:
The patent merges the centering function with the component's circumferential structure by distributing support sections around the entire circumference. This integration allows the component itself to provide centering support through its structured design rather than relying on separate groove features, maintaining both reliability and strength.
Data Source
Figure 1
Figure 2A~2C
AI summary
The invention relates to a turbine intermediate casing for a gas turbine, in particular an aircraft gas turbine, comprising several first components (12) and several second components (14) arranged alternately side by side in the circumferential direction (UR) and defining a hot gas flow channel (20) in the radial direction (RR), wherein the first components (12) each have two first overlap sections (22) and the second components (14) each have two second overlap sections (24), such that in a respective region (26) of the transition from a first component (12) to a second component (14) or vice versa, one of the first overlap sections (22) and one of the second overlap sections (24) are arranged overlapping, and comprising at least one centering element (30) on which the first components (12) and the second components (14) are supported along the circumferential direction (UR) and in the radial direction (RR), such thatthat the first components (12) and the second components (14) are arranged substantially centered with respect to a central axis of the turbine intermediate casing (10). According to the invention, it is proposed that the first components (12) and the second components (14) are made of a ceramic fiber composite material (CMC) and that at least one first support section (32) and at least one second support section (34) are provided on each first component (12) and on each second component (14), which are arranged at a distance (AB) from each other in the circumferential direction (UR), wherein the first support section (32) and the second support section (34) are designed such that they act on the centering element (30) in the radial direction (RR) from different sides.