Aircraft Engine Ring-Wall Sealing With S-Shaped Gas Passage
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing sealing systems in turbomachines with coaxially engaged cylindrical walls face inefficiencies due to significant radial displacement, which compromises the sealing effectiveness between rotating elements.
Innovation Solution
A sealing arrangement featuring U-shaped axial ends with S-shaped annular gas passages allows for the installation of seals on multiple branches, enabling effective sealing during radial displacement and accommodating axial movement, using labyrinth, brush, or carbon seal means strategically placed within the S-shaped passage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If labyrinth seals are used between two rotating elements, then sealing is provided, but radial clearance must be very open to accommodate manufacturing tolerances and displacements, which impairs sealing efficiency
Solution Approach 1:
The seal is divided into multiple independent sealing branches (first branch, second branch, third branch) arranged in different orientations. Each branch can independently accommodate displacement in different directions, allowing the seal to remain effective even when radial clearance varies due to manufacturing tolerances or operational displacements.
Solution Approach 2:
The sealing structure transitions from a single radial sealing plane to a three-dimensional multi-branch configuration. The branches are oriented at different angles (first branch axial, second branch radial, third branch oblique), creating sealing capability in multiple spatial dimensions simultaneously, thereby accommodating radial clearance variations without compromising sealing efficiency.
2Reliability
If multiple sealing branches are installed to accommodate radial displacement, then sealing efficiency is maintained, but device complexity increases
Solution Approach 1:
Multiple sealing branches are merged into a single integrated seal component that is mounted on one of the coaxial walls. The different branches share common mounting structures and sealing surfaces, reducing the number of separate parts while maintaining the multi-branch sealing configuration. This integration reduces assembly complexity while preserving the ability to accommodate radial displacements.
3Reliability
If axial extension of U-shaped ends is increased to accommodate axial displacements, then sealing is maintained during axial movement, but manufacturing complexity increases
Solution Approach 1:
The U-shaped ends are designed with sufficient axial extension to dynamically accommodate axial displacements between the coaxial walls. The length of the U-shaped ends is optimized to provide the necessary travel range for axial movement while maintaining sealing contact, allowing the seal to adapt to varying axial positions without requiring overly complex manufacturing.
Data Source
AI summary
A sealing arrangement is provided between inner and outer coaxial ring-shaped walls of an aircraft engine. The outer wall has an axial end with a U-shaped cross-section parallel to axis, the opening therein being oriented axially in a first direction. The inner wall has an axial end with a U-shaped cross-section parallel to axis, the opening therein being oriented axially in the opposite direction. The U-shaped end of the outer wall includes a ring-shaped free edge axially engaged in the opening in the axial end of the inner wall. The U-shaped end of the inner wall includes a ring-shaped free edge axially engaged in the opening in the axial end of the outer wall. The walls define therebetween a ring-shaped gas channel having a substantially S-shaped axial cross-section.