Turbine Vane Segment Securing Ribs
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Solution Overview
Problem
The existing guide vane segments for gas turbines require additional components and complex assembly steps for securement, such as pin-type elements or soldered securing elements, which complicate the installation and manufacturing process.
Innovation Solution
The introduction of two securing ribs on the trailing end face of the guide vane segment, with a tapering intermediate space between them, allows for secure peripheral locking without the need for additional components, optimizing structural rigidity and assembly by adapting to the guide vane's structural requirements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If pin-type elements or soldered securing elements are used to secure guide vane segments, then reliable peripheral securing is achieved, but device complexity and assembly complexity increase due to additional components and working steps
Solution Approach 1:
The patent merges the securing function directly into the guide vane segment structure by forming two securing ribs that extend from the trailing end face. This integration eliminates the need for separate pin-type elements or soldered securing elements, as the ribs themselves perform the peripheral securing function when received in corresponding grooves of the housing, thereby reducing device complexity while maintaining reliable securing.
Solution Approach 2:
The guide vane segment is designed to be self-securing through its own structural features. The two securing ribs formed as integral parts of the guide vane segment automatically engage with housing grooves during assembly, eliminating the need for additional securing components or complex assembly steps. The structure serves its own securing function without external assistance.
2Reliability
If additional securing elements are used, then secure peripheral locking is achieved, but manufacturing complexity and production time increase
Solution Approach 1:
The securing ribs are formed as integral parts of the guide vane segment, merging the securing function into the main component. This eliminates the need to manufacture separate securing elements and perform additional assembly operations such as pin insertion or soldering, thereby simplifying the manufacturing process while achieving reliable peripheral locking.
Solution Approach 2:
The securing function is segmented into two distinct ribs formed on the trailing end face of the guide vane segment. This segmentation allows each rib to be optimally shaped and positioned for engagement with corresponding housing grooves, improving manufacturing efficiency by allowing the ribs to be formed directly during guide vane segment production without requiring separate securing elements.
Data Source
AI summary
The invention relates to a guide vane segment for an aircraft gas turbine, comprising at least a radially outer shroud and a radially inner shroud, which extend along a respective circular arc and together form a ring segment, wherein, in the radial direction, between the outer shroud and the inner shroud, a plurality of guide vanes are arranged next to one another in the peripheral direction (UR), the vanes being materially joined with the inner shroud and the outer shroud, in particular joined in one piece. At least two securing ribs are arranged next to one another are formed on the trailing end face for at least one guide vane, wherein an intermediate space delimited by the two securing ribs in the peripheral direction (UR) is formed, this space tapering from radially outside to radially inside.