Aircraft Engine Rotor Damping Device Mounting
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Solution Overview
Problem
The existing rotor devices of aircraft engines face difficulties in mounting and dismounting due to the complexity of arranging damper elements between turbine blades, requiring special tools and procedures, which is time-consuming and can lead to adhesive residue issues affecting the service life.
Innovation Solution
The rotor device features recesses in the turbine blades that can fully receive the damping device, allowing for easy mounting and dismounting by completely countersinking the damping device, eliminating the need for adhesive or grease and reducing tool complexity, with a securing device to prevent unwanted movement.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If damper elements are fixed between turbine blades using grease or adhesive during mounting, then the damper elements are prevented from falling, but adhesive residue reduces the service life of the blade and disk
Solution Approach 1:
The harmful adhesive residue is extracted/removed from the system by replacing the adhesive-based fixation method with a mechanical retention method using the countersink geometry and securing device, eliminating the harmful substance while maintaining the retention function
Solution Approach 2:
The countersink cavity and securing device act as an intermediary mechanical structure that mediates between the damper element and the turbine blade, providing retention without requiring adhesive substances
2Ease of manufacture
If the complete blade set is inserted into the disk wheel in a spiral-like manner, then mounting is achieved, but the arrangement of damper elements inside the damper pockets becomes difficult and time-consuming
Solution Approach 1:
The damper elements are preliminarily placed in the countersink cavities before the turbine blades are fully inserted into the disk wheel, allowing for easier and quicker mounting without requiring complex spiral insertion procedures
Solution Approach 2:
The mounting process is segmented into distinct steps: first inserting blades slightly into retention slots, then placing damper elements in countersinks, and finally completing the insertion, which simplifies the overall mounting procedure
3Ease of operation
If turbine blades are inserted slightly into retention slots to allow movement, then damper elements can be arranged, but the procedure requires special tools and multiple disassembly operations
Solution Approach 1:
The countersink cavity and securing device structure enables the damper elements to be retained and secured through simple geometric features rather than requiring special tools or complex procedures, making the system self-sufficient for mounting operations
4Ease of repair
If multiple disassembly operations are performed for balancing and blade exchange, then maintenance is achieved, but the process becomes very time-consuming
Solution Approach 1:
The damper elements are preliminarily secured in the countersink cavities with the securing device before blade removal, allowing for quick disassembly and reassembly during maintenance operations without requiring multiple complex disassembly steps
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 design facilitates quicker and easier assembly and disassembly, reduces the need for special tools, and avoids adhesive residue issues, while allowing for improved damping and sealing effects and weight reduction.
Implementation Method 1
damping of blade vibrations is achieved by means of friction
Implementation Method 2
the respective guide surface extends radially in the direction of the disk wheel... wherein the respective recess extends in the circumferential direction from a boundary plane defined by the lateral edge area to a side surface that delimitates the guide surface towards the turbine blade center
Data Source
AI summary
A rotor of an aircraft engine includes a disk wheel and at least two turbine blades. A damping device is arranged below a blade platform and inside a cavity between the blades in the radial direction. The cavity is formed by a respective recess at adjoining blades, with respective recesses having an outer guide surface in the radial direction, acting together with the damping device during operation of the rotor. The guide surface extends radially, from the lateral edge area of the blade to the central area of the blade. The respective recess extends circumferentially from a boundary plane defined by the lateral edge area of the blade to a side surface that delimitates the guide surface towards the blade center. The recess of at least one of the adjacent blades completely receives the damping device.