Spacer-Mounted Blade Damping for Turbomachine Vibration Grounding
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Solution Overview
Problem
Current vibration damping methods for turbomachine blades, such as single-blade, blade-to-blade, and blade-to-rotor disk approaches, face challenges including corrosion, complexity in installation, and reduced effectiveness due to lack of grounding, which compromises the ability to manage vibrational stresses effectively.
Innovation Solution
A vibration-damping system that includes a spacer with a damping element coupler positioned adjacent to the blade platform, featuring a vibration-damping element that engages the radially inner surface of the blade platform to frictionally dampen vibrations, providing both blade-to-blade and blade-to-ground damping without altering the blade configuration.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a damper is attached to an external surface of the airfoil, then vibration damping is provided, but the damper is exposed to corrosion and may separate from the airfoil
Solution Approach 1:
The patent introduces a spacer as an intermediary component positioned between the blade airfoil and the damper. The spacer includes a damper support that holds the damper, isolating it from the corrosive environment while maintaining damping effectiveness. This mediator approach protects the damper from direct exposure to corrosive gases while still allowing it to function on the blade.
Solution Approach 2:
The patent moves the damper from a traditional external surface attachment on the airfoil to a different spatial location using the spacer structure. The damper is repositioned in a different dimensional space (on the spacer rather than directly on the airfoil surface), which removes it from the corrosive environment while maintaining its functional relationship with the blade.
2Reliability
If blade-to-rotor disk damping approach is used, then vibration grounding is achieved, but the installation and repair become very complicated
Solution Approach 1:
The patent divides the damping system into separate modular components: the spacer (which can be installed on the rotor disk), the damper support, and the damper itself. This segmentation allows each component to be manufactured and prepared separately, then assembled together, greatly simplifying installation and repair procedures compared to integrated blade-to-rotor disk approaches.
Solution Approach 2:
The spacer acts as an intermediary component that simplifies the connection between the rotor disk and the damper. Instead of directly engaging complex blade-to-rotor disk structures, the spacer provides a simplified interface that maintains vibration grounding while reducing installation and repair complexity.
3Strength
If blade structure is altered to reinforce against vibrations, then vibration resistance is improved, but aerodynamic performance changes and weight/length increase
Solution Approach 1:
The patent uses the spacer and damper support as intermediary components to provide vibration damping without modifying the blade structure itself. This external damping approach avoids adding weight to the moving blade while still achieving vibration resistance through the separately positioned damping mechanism.
Solution Approach 2:
The patent changes the approach from modifying blade structural parameters (which would increase weight) to introducing external damping parameters through the spacer and damper assembly. This parameter change allows vibration resistance to be achieved without altering the blade's weight or aerodynamic characteristics.
4Reliability
If multiple damping approaches are combined, then comprehensive vibration control is achieved, but device complexity increases
Solution Approach 1:
The patent merges multiple damping functions (blade-to-blade damping and blade-to-ground damping) into a single integrated spacer assembly. The spacer simultaneously provides support for dampers that can damp vibrations between adjacent blades and also provide grounding to the rotor disk, reducing overall system complexity while achieving comprehensive vibration control.
Solution Approach 2:
The spacer is designed as a universal component that performs multiple functions: it positions dampers for blade-to-blade damping, provides blade-to-ground damping through rotor disk engagement, and serves as a structural support element. This multi-functionality reduces the need for separate components for each damping function, simplifying the overall system.
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
The system effectively reduces blade vibrations through frictional damping, grounding vibrations for both in-phase and out-of-phase responses, and allows for simple installation and customization, enhancing damage tolerance and reducing vibratory stress.
Implementation Method 1
a vibration-damping element configured to couple to the damping element coupler, wherein the vibration-damping element and the damping element coupler are disposed to cause the vibration-damping element to engage the radially inner surface of the platform of the at least one turbomachine blade to dampen vibration of the at least one turbomachine blade
Data Source
AI summary
A vibration-damping system for turbomachine blade(s) in a turbomachine is provided. Each turbomachine blade includes a platform having a radially inner surface. The system includes a spacer axially adjacent the platform of at least one turbomachine blade in the turbomachine, e.g., adjacent a turbomachine blade stage. The spacer includes a body. A damping element coupler is on the body of the spacer, and a vibration-damping element is configured to couple to the damping element coupler. The vibration-damping element and the damping element coupler are disposed to cause the vibration-damping element to engage the radially inner surface of the platform of the turbomachine blade(s) to dampen vibration of the turbomachine blade(s), e.g., during operation of the turbomachine.