Guide Blade Axial Extraction Device for Turbomachine Maintenance
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Solution Overview
Problem
The existing guide vane arrangements in turbomachines face challenges during disassembly due to high temperatures and forces, which can lead to damage to the airfoil thermal barrier coating and deformation, especially when large axial forces are required to remove vanes for maintenance.
Innovation Solution
An extraction device with an axially extending trigger passage and internal thread is introduced, allowing for the application of high axial forces outside the flow profile, using a threaded pull-off tool that interacts with the internal thread to safely remove vanes without damaging the airfoil or thermal protection layer.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If large axial forces are introduced into the guide vane for disassembly, then the vane can be removed from the carrier, but the airfoil thermal barrier coating may be damaged or the airfoil may be deformed
Solution Approach 1:
A separate trigger pin is introduced as an intermediary component between the extraction tool and the guide vane. The trigger pin with its axial bore receives the extraction tool, which applies force to the trigger pin rather than directly to the guide vane airfoil. This intermediary structure allows high extraction forces to be applied through the platform to the locking sections without directly loading the airfoil, thus preventing damage to the thermal barrier coating and airfoil deformation while enabling effective disassembly
2Adaptability or versatility
If the plug-in attachment is used for fastening guide vanes to the carrier, then individual vanes can be assembled and disassembled without disassembling the entire carrier, but the attachment becomes sluggish or blocked due to high temperatures and forces
Solution Approach 1:
The attachment system is segmented into multiple independent locking sections distributed around the circumferential direction, each with its own tongue and groove structure. This segmentation allows individual vanes to be attached and detached independently from the carrier without affecting other vanes. The distributed locking sections provide multiple attachment points that share the mechanical loads, improving reliability under high temperature and force conditions while maintaining the capability for individual vane maintenance
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This solution enables the safe and efficient disassembly of guide vanes by applying high pull-off forces without risking deformation or damage to the airfoil or thermal protection, simplifying the maintenance process while maintaining the structural integrity of the turbomachine components.
Implementation Method 1
The trigger passage opening is provided with an internal thread. In addition, the vane support is provided with an abutment zone axially opposite to said drain passage opening. To strip a vane from the vane carrier, a stripping tool, which is externally threaded, is inserted into the strip through hole and screwed into the internal thread.
Implementation Method 2
Further threading of the trigger tool into the trigger port introduces axial compressive forces into the vane. Since the extraction tool interacts with the internal thread of the extraction passage opening, an axially oriented tensile force is introduced into the vane in response to the extraction tool pressing against the guide vane carrier.
Data Source
Figure 1~2
Figure 3~4
Figure 5a~6
AI summary
The invention relates to a guide blade arrangement (1) of a non-positive-displacement machine (4), particularly of a gas turbine, comprising at least one guide blade support (2) and a number of guide blades (3), which are fastened to the guide blade support (2) and are adjacently arranged in a peripheral direction. The fastening between the guide blade support (2) and the respective guide blade (3) is provided in an axially insertable manner. In order to simplify the removal of an individual guide blade (3), at least one of the guide blades (3) is equipped with a pull-off device (35) that has at least one axially extending pull-off through opening (36). The respective pull-off through opening (36) is equipped with an internal thread (37). The guide blade support (2) is equipped with am abutment region (38) located opposite the pull-off through opening (36). The pull-off device (35) is designed for introducing axially oriented pull-off forces into the respective guide blade (3) by means of a pull-off tool, which is provided with an outer thread and which is placed in the pull-off through opening (36) and presses against the abutment region (38) in order to pull off the respective guide blade (3) from the guide blade support (2).