Compressor Vane Ring Assembly Between Integrally Bladed Rotor Rows
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Solution Overview
Problem
The assembly of high compressor sections in direct-drive gas turbine engines with multi-row integrally bladed rotor drums poses challenges due to interference between blades and vanes, limiting the use of traditional axial assembly methods.
Innovation Solution
The method involves using split vane assemblies with overlapping or sealed joints, variable vanes that can be slid, pivoted, or axially assembled onto a multi-row rotor drum, and a continuous hoop vane ring design to facilitate assembly without mechanical joints, ensuring alignment and sealing while avoiding interference.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If traditional axial assembly methods are used, then assembly simplicity is maintained, but blade-vane interference occurs preventing successful assembly
Solution Approach 1:
The vane assembly is divided into multiple arc segments that can be assembled separately and then joined together to form a complete circular arrangement. This segmentation allows the vanes to be installed without interfering with the rotor blades, as each segment can be positioned and secured independently before being connected to adjacent segments.
2Ease of operation
If vane assemblies are split into multiple segments, then assembly feasibility is improved, but joint sealing and alignment complexity increases
Solution Approach 1:
Multiple arc segments are joined together to form a complete circular vane assembly that functions as a unified structure. The segments are connected through overlapping joints with sealing elements that integrate the individual segments into a cohesive assembly, eliminating gaps and ensuring proper sealing while maintaining the benefits of segmented assembly.
3Reliability
If overlapping joints with sealing elements are used, then sealing performance is improved, but manufacturing complexity increases
Solution Approach 1:
Sealing elements are introduced as intermediary components between the arc segments to ensure proper sealing at the joints. These sealing elements facilitate the connection between segments by providing a dedicated sealing interface, which simplifies the overall manufacturing process compared to attempting to create sealed joints directly through complex machining or fitting operations.
Data Source
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AI summary
A method for assembling a section of a gas turbine engine (20) involves a plurality of vane arc segments (70a, 70b) that together form a full vane ring (70), and a multi-row rotor drum (60) that is formed of a single-piece body that has at least two rows of blades (40a, 40b) about a central axis (A). The method includes inserting the plurality of vane arc segments (70a, 70b) in a radial direction into an assembled position that is axially between the two rows of blades (40a, 40b).