Gas Turbine Rotor Module Fixture for Faster Stage Disassembly
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Solution Overview
Problem
Existing methods for assembling and disassembling gas turbine engine modules, particularly those with a centre-bolt arrangement, require sequential assembly and disassembly of each rotor and stator stage, leading to complex and time-consuming processes.
Innovation Solution
A method involving a fixture and a sleeve with a radially extending land that provides compressive force across rotor stages, allowing for simultaneous handling and removal of multiple stages as a module, using a centre-bolt attachment and axial translation of the sleeve.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a centre-bolt arrangement is used to secure the turbine section to the rotor shaft, then the turbine section can be held together, but sequential assembly and disassembly of each rotor and stator stage is required, making the process complex and time-consuming
Solution Approach 1:
The invention divides the turbine section into modular stages (rotor and stator stages) that can be independently handled while maintaining their relative positioning through the centre-bolt arrangement. This segmentation allows the turbine section to be assembled and disassembled as a unified module rather than requiring sequential manipulation of individual components, thereby improving productivity while maintaining securing reliability
Solution Approach 2:
The centre-bolt acts as an intermediary element that connects the rotor and stator stages to the rotor shaft, enabling the entire turbine section to be handled as a single unit. This intermediary mechanism allows simultaneous handling of multiple stages without requiring sequential assembly/disassembly operations
2Reliability
If a multi-bolt arrangement is used to hold turbine rotors together, then the rotors can be secured both during assembly and operation, but the assembly and disassembly process becomes more complex
Solution Approach 1:
The invention extracts the complex multi-bolt arrangement and replaces it with a simplified centre-bolt arrangement that achieves the same rotor securing function. By removing the unnecessary multi-bolt configuration and retaining only the essential centre-bolt mechanism, the invention reduces assembly process complexity while maintaining rotor securing reliability
Solution Approach 2:
The centre-bolt arrangement serves multiple functions simultaneously: it secures the turbine section to the rotor shaft, maintains the relative positioning of rotor and stator stages, and enables unified handling of the entire module. This multi-functionality eliminates the need for separate securing mechanisms, thereby reducing device and process complexity
3Ease of manufacture
If sequential assembly method is used, then each stage can be assembled separately, but the assembly time and downtime increase significantly
Solution Approach 1:
The invention merges the assembly of multiple rotor and stator stages into a single unified operation. By using the centre-bolt arrangement to hold the entire turbine section together, all stages can be assembled and disassembled as one module rather than sequentially, dramatically reducing assembly and disassembly time while maintaining the capability for staged construction during manufacturing
4Ease of repair
If modular assembly method is used, then servicing is simplified and downtime is reduced, but the turbine section must be pre-assembled as a complete module
Solution Approach 1:
The invention creates a dynamic assembly system where the centre-bolt arrangement can be quickly engaged and disengaged to transform the turbine section between a disassembled state for manufacturing and a unified modular state for operation and servicing. This dynamic capability allows the system to adapt between pre-assembly requirements during manufacturing and simplified modular servicing during operation
Data Source
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AI summary
A method of disassembling a rotor module (30) of a gas turbine engine (10). The gas turbine engine (10) comprising a rotor output shaft (92). The rotor module (30) comprising a centre-bolt (84), a sleeve (90), at least one rotor stage (56, 58), at least one stator stage (48, 50), a casing (46) and an axis (26). The method comprising the steps: attaching a fixture (102) to the at least one rotor stage (56, 58), attaching the fixture (102) to the casing (46), detaching the centre-bolt (84) from the at least one rotor stage (56, 58), detaching the sleeve (90) from the output shaft (92), attaching the fixture (102) to the sleeve (90), and removing the rotor module (30) and fixture (102) from the rotor output shaft (92). There is also presented a method of assembling the rotor module to the gas turbine engine and the apparatus used for disassembly and assembly.