T-Shaped Interstage Seal Tooling for Spring-Loaded Ring Installation
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Solution Overview
Problem
Existing turbomachine installation methods face challenges with rotating components being forced out of slots due to radial forces from springs or loading mechanisms during partial rotational speed, leading to incomplete loading and potential damage.
Innovation Solution
A tooling assembly with an axial mounting portion and radial compression portion that removably couples to rotor blades, applying a radial force to counteract spring forces and facilitate the circumferential installation of T-fairing rings without damaging neighboring components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If springs or loading mechanisms are equipped on rotating components to maintain radial loading during partial rotational speed, then reliability of component loading is improved, but during installation the radial force from these springs forces the rotating component out of the window
Solution Approach 1:
The tooling assembly applies a preliminary radial force in the opposite direction to the spring force before installation is complete. The radial compression portion of the tooling assembly counteracts the outward radial force from the springs, allowing the mounting portion to be loaded into the attachment slot without being forced out by the spring loading mechanism.
Solution Approach 2:
The tooling assembly acts as an intermediary between the spring-loaded rotating component and the attachment slot. It provides a temporary radial constraint that mediates the conflict between the spring force and the installation process, enabling the component to be installed despite the presence of the spring loading mechanism.
2Ease of operation
If radial compression force is applied during installation to counteract spring forces, then installation ease is improved, but the tooling assembly must be designed with additional components to apply this force
Solution Approach 1:
The tooling assembly is segmented into distinct functional portions: an axial mounting portion for attaching to rotor blades and a radial compression portion for applying radial force. This segmentation allows each portion to be optimized for its specific function while keeping the overall design manageable and not excessively complex.
Solution Approach 2:
The tooling assembly is designed to be universally applicable to multiple rotor blades and can be used for installing T-fairing rings in various positions. The axial mounting portion can engage with different rotor blade configurations, and the radial compression portion can apply force at multiple locations, reducing the need for multiple specialized tools.
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
Enables secure and damage-free installation of T-fairing rings by counteracting spring forces, ensuring complete loading and reducing wear and misalignment issues during turbomachine operation.
Implementation Method 1
A tooling assembly with an axial mounting portion and radial compression portion that removably couples to rotor blades, applying a radial force to counteract spring forces and facilitate the circumferential installation of T-fairing rings
Data Source
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AI summary
A tooling assembly 100 for installation relative to a first and second turbomachine component 32, 50 is provided. The tooling assembly 100 includes an axial mounting portion 108 removably couplable to the first turbomachine component 32. The axial mounting portion 108 includes a first plate 110, a second plate 112 spaced apart from the first plate 110, and at least one turnbuckle assembly 114 that extends between, and is coupled to, the first plate 110 and the second plate 112. At least one of the first plate 110 and the second plate 112 include a radial compression portion 116. The radial compression portion 116 includes a compression bar 128 radially movable relative to the axial mounting portion 108 and configured to contact the second turbomachine component 50.