Rotor Blade Removal Tooling for Collision-Free Disk Extraction
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing methods for removing rotor blades from a turbomachine rotor disk risk damaging neighboring blades due to their complex geometric contours, making individual blade removal impossible without collision.
Innovation Solution
A tooling assembly comprising a first and second plate with extending members and blocks arranged in rows, allowing partial sliding of rotor blades into corresponding openings to facilitate safe removal without collision.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If rotor blades are removed individually from a complete ring, then the removal process becomes simple, but the complex geometric curvature of the airfoil causes collision with neighboring airfoils resulting in damage
Solution Approach 1:
The rotor blade removal process is segmented into multiple stages: first removing a continuous circumferential portion of multiple airfoils together using a specialized tool, then separately removing individual airfoils. This segmentation allows the complex geometric airfoils to be removed as a group without collision, eliminating the damage risk while maintaining operational simplicity.
Solution Approach 2:
A specialized removal tool acts as an intermediary between the rotor blades and the removal process. This tool includes a body with a circumferential removal portion that engages multiple rotor blades simultaneously, providing a controlled mechanism that prevents airfoil collision while enabling safe extraction of individual blades from the complete ring.
2Object-affected harmful factors
If multiple rotor blades are removed simultaneously, then collision damage is prevented, but the device complexity and operational difficulty increase
Solution Approach 1:
The removal tool is designed with universal functionality to perform multiple operations: it can remove a continuous circumferential portion of multiple airfoils simultaneously, and also facilitate subsequent individual airfoil removal. This multi-functionality reduces the need for multiple specialized tools, thereby managing device complexity while preventing collision damage.
Solution Approach 2:
The tool performs a preliminary action by removing a continuous circumferential portion of multiple airfoils before individual airfoil extraction. This preliminary removal creates space and prevents collision, simplifying the subsequent individual blade removal process and reducing overall operational difficulty despite the initial tool complexity.
3Productivity
If individual rotor blades are extracted without support structures, then the extraction process is fast, but the complex geometric contour causes instability and potential damage
Solution Approach 1:
The removal tool provides beforehand cushioning and support structures that engage the rotor blades during the removal process. These support structures stabilize the complex geometric airfoils throughout extraction, preventing instability and potential damage while maintaining efficient extraction speed through the integrated tool design.
Solution Approach 2:
The tool body is designed with a nested structure where the circumferential removal portion is integrated within the main tool body. This nesting allows the support structures to be compact yet effective, providing stability during extraction without excessive device complexity, thereby maintaining both productivity and reliability.
Data Source
Figure 1
Figure 2~3
Figure 4~5
AI summary
A tooling assembly (100) for removal of a rotor blade (32) from a rotor disk (198) of a turbomachine. The tooling assembly (100) includes a first plate (158) and a second plate (160) spaced apart from the first plate (158). The tooling assembly (100) further includes one or more members (162) extending between the first plate (158) and the second plate (160). The tooling assembly (100) further includes a plurality of blocks (164) mounted to the one or more members (162) and arranged in one or more rows between the first plate (158) and the second plate (160). At least one block (164) in the plurality of blocks (164) defines an opening (210) that corresponds with an exterior shape of a mounting portion of the rotor blade (32).