Gas Turbine Disassembly Sequences for Maintenance Efficiency
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Solution Overview
Problem
The existing methods for assembling and disassembling gas turbines are inflexible and inefficient, leading to increased workload and costs due to a one-size-fits-all approach that does not adapt to various maintenance and replacement situations.
Innovation Solution
A methodical approach to disassembling and assembling the turbine section, involving sequential steps such as disassembling the upper turbine case, rear diffuser assembly, combustor assembly, vane assembly, and blade assembly, allowing for customized disassembly and reassembly processes based on specific circumstances.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If a fixed one-size-fits-all assembly and disassembly process is used for gas turbines, then the process is simple to implement, but work efficiency is reduced and workload increases
Solution Approach 1:
The patent applies dynamics by transitioning from a fixed, static assembly/disassembly process to a dynamic, flexible process that can be adapted based on specific maintenance needs. The method allows selection of different disassembly sequences (first through fifth embodiments) depending on the particular circumstances, enabling the process to respond dynamically to varying operational requirements and improve work efficiency.
Solution Approach 2:
The patent changes the parameter of process flexibility by introducing multiple disassembly embodiments with different sequences and scopes. Instead of a single fixed procedure, the method allows parameter changes in the disassembly approach (e.g., disassembling entire turbine section vs. selective component removal) to match specific maintenance scenarios, thereby improving productivity without excessive complexity.
2Adaptability or versatility
If a fixed assembly and disassembly process is used for all gas turbine maintenance, then the procedure is standardized and easy to follow, but it cannot adapt to various maintenance situations leading to increased time and cost
Solution Approach 1:
The patent applies segmentation by dividing the gas turbine disassembly process into distinct embodiments (first through fifth) with different levels of disassembly scope. Each embodiment segments the maintenance task appropriately - from complete turbine section disassembly to selective component removal - allowing adaptation to various maintenance situations and reducing unnecessary time expenditure on full disassembly when only specific components need attention.
Solution Approach 2:
The patent applies partial action by allowing maintenance personnel to perform only the necessary portion of disassembly based on the specific maintenance need. Instead of always disassembling the entire turbine section, the method enables partial disassembly (e.g., only combustor assembly or only specific blade assemblies) when that is sufficient, thereby adapting to various situations and reducing maintenance time and cost.
3Loss of time
If selective disassembly of specific components is performed, then maintenance time and cost are reduced, but the process becomes more complex and requires careful sequencing
Solution Approach 1:
The patent applies preliminary action by establishing predetermined disassembly sequences and embodiments before maintenance begins. The five different embodiments provide pre-planned approaches for different maintenance scenarios, allowing selective disassembly of specific components (combustor assembly, blade assemblies, diffuser assembly) without requiring complex on-the-spot decision-making. This pre-structured flexibility reduces maintenance time while managing process complexity through established procedures.
Data Source
AI summary
A method of assembling and disassembling a gas turbine, and a gas turbine assembled thereby, improves work efficiency and reduces time and cost by carrying out various disassembly and reassembly processes depending on circumstances. In one process, a turbine section is disassembled from a gas turbine by sequential steps of disassembling an upper turbine case; disassembling a rear diffuser assembly and a rear bearing assembly; disassembling a combustor assembly; disassembling a vane assembly; and disassembling a blade assembly. In another process, first-stage to fourth-stage blade assemblies and first-stage to fourth-stage vane assemblies in a turbine section are disassembled from the gas turbine by sequential steps of disassembling an upper turbine case; disassembling a combustor assembly; disassembling a vane assembly; and disassembling a blade assembly. The gas turbine includes a compressor section, a combustor section, and the turbine section assembled in a reverse order with respect to the disassembly method.