Shroud Housing Supported by Segmented Vane Ring
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Solution Overview
Problem
In gas turbine engines, controlling rotor tip clearance is challenging due to the long structural path between the shroud and its point of attachment, especially when using circumferentially segmented vane rings to accommodate thermal expansion, which affects turbine performance.
Innovation Solution
A shroud housing arrangement that includes a circumferentially segmented vane ring with vane segments jointly supporting the shroud housing, axially restrained by a retaining ring, minimizing the structural path and reducing shroud bending impact on tip clearance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If circumferentially segmented vane rings are used to accommodate thermal expansion, then adaptability to thermal growth is improved, but the structural path between the shroud and engine structure becomes longer, worsening tip clearance control
Solution Approach 1:
The vane ring is divided into multiple circumferential segments that can independently expand and contract axially in response to thermal changes. This segmentation allows each segment to accommodate thermal growth independently while maintaining a relatively short structural path to the shroud, thus resolving the contradiction between thermal adaptability and tip clearance control.
2Strength
If the shroud is supported from an axially remote location by the turbine support case, then structural support is provided, but the structural path length increases, making tip clearance control challenging
Solution Approach 1:
The support structure transitions from purely axial support at a remote location to include radial support components. The segmented vane ring structure provides radial support closer to the shroud while maintaining axial support capabilities, effectively shortening the structural path in the critical radial direction and improving tip clearance control.
Data Source
AI summary
A shroud mounting arrangement comprises a shroud housing and a shroud mounted to the shroud housing. The shroud is configured to surround a stage of rotor blades of a gas turbine engine. A circumferentially segmented vane ring is disposed axially adjacent to the stage of rotor blades. The circumferentially segmented vane ring comprises a plurality of vane segments. The vane segments jointly support the shroud housing.