Aircraft Turbomachine Labyrinth Seal With Circumferential Gas Cavities
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Solution Overview
Problem
Current labyrinth sealing joints in turbomachines, particularly in aircraft, face limitations in achieving optimal sealing efficiency due to the reliance on multiple annular lips and abradable elements, which can lead to wear and suboptimal gas stream turbulence for effective sealing.
Innovation Solution
The introduction of a labyrinth sealing joint design featuring two annular lips with circumferentially arranged gas passage cavities interconnected by axial partitions, where at least one lip has axial gas passage openings, allowing for enhanced turbulence and sealing performance with fewer lips compared to traditional designs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple annular lips are used in traditional labyrinth sealing joints, then sealing efficiency is improved through increased turbulence, but device complexity and the number of components increase
Solution Approach 1:
The invention divides the sealing function into multiple gas passage cavities arranged circumferentially between two lips. Each cavity acts as an independent turbulence-generating element, replacing the need for multiple annular lips while maintaining effective sealing through distributed disturbance points in the gas stream
Solution Approach 2:
The invention transitions from multiple annular lips arranged axially to multiple gas passage cavities arranged circumferentially between two lips. This dimensional reorganization allows the same sealing function to be achieved with fewer components by utilizing the circumferential dimension for cavity arrangement
2Reliability
If multiple annular lips are used to increase turbulence, then sealing performance improves, but wear on lips and abradable elements increases
Solution Approach 1:
The sealing function is segmented into multiple cavities that distribute the turbulence-generating action across different circumferential locations rather than requiring multiple annular lips. This reduces the wear burden on each individual lip-abradable element interface while maintaining overall sealing effectiveness
Solution Approach 2:
The gas passage cavities act as intermediary structures that generate turbulence and improve sealing without requiring direct contact between lips and abradable elements. The cavities create pressure drops and flow disturbances that enhance sealing performance while minimizing mechanical wear
3Device complexity
If fewer lips are used to simplify the design, then device complexity is reduced, but sealing efficiency deteriorates due to insufficient turbulence
Solution Approach 1:
The invention compensates for using fewer lips by utilizing the circumferential dimension to arrange multiple gas passage cavities. This allows two lips to perform the sealing function of multiple lips by creating multiple disturbance points around the circumference, maintaining sealing efficiency while simplifying the axial structure
Solution Approach 2:
The invention changes the geometric parameters of the sealing structure by introducing cavities with specific dimensions, shapes, and circumferential arrangements. These parameter changes enable the cavities to generate sufficient turbulence and pressure drops to maintain sealing efficiency with fewer lips
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 significantly improves sealing efficiency by creating multiple disturbance points for the gas stream, increasing turbulence and pressure drops, thereby enhancing the overall sealing performance of the joint while reducing the number of lips required.
Implementation Method 1
This creates turbulence in the gas stream which generates pressure drops and thus improves the sealing of the sealing joint
Data Source
AI summary
A labyrinth sealing joint for a turbomachine, for example of an aircraft, includes a rotor element extending about an axis (A), and a stator element extending around the rotor element, the rotor element having two annular lips extending radially outwards and surrounded by at least one abradable element carried by the stator element. A plurality of gas passage cavities are arranged circumferentially next to one another between the two lips which are interconnected by connecting partitions, wherein at least one of the lips has at least one axial gas passage opening that leads into at least some of the cavities, wherein the partitions extend substantially axially between the lips and define sectors of gas passage spaces between them, the sectors of spaces being divided by separation walls for forming the cavities.