Compressor Shroud Socket Bonding for Axial Turbomachines
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Solution Overview
Problem
Existing fastening methods for shrouds in axial turbomachines, such as those used in compressors, face limitations in strength due to vibrations, leading to potential loss of cohesion and requiring complex manipulations or materials with limited adhesion.
Innovation Solution
The implementation of a fastening system that includes a blade with a guide surface and a socket, where the interface between the blade and socket features asperities and a bonding layer, enhancing anchoring through material engagement and shear strength, and allowing for easier replacement of components by using a thermoplastic fastening layer.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a material is applied between reinforcements and blades to connect them, then the shroud can be fastened to the blades, but the connection strength is limited and loss of cohesion can occur due to vibrations
Solution Approach 1:
The socket is designed with an porous structure that allows the fastening material to penetrate and anchor into the blade end, creating a mechanically interlocked connection. The porous walls provide increased surface area and mechanical engagement, preventing loss of cohesion under vibrational loads while maintaining strong fastening between the shroud and blades
Solution Approach 2:
The fastening system uses a composite approach combining the porous socket structure (likely ceramic or metal matrix) with a specialized fastening material that has both adhesive and mechanical interlocking properties. This composite system provides superior connection strength compared to simple material application between reinforcements and blades
2Reliability
If retention plates are bonded through openings in blade ends, then the shroud can be anchored, but complex manipulations are required to place each plate
Solution Approach 1:
The socket integrates multiple functions into a single component: it provides the anchoring structure, contains the fastening material reservoir, and creates the mechanical interlock all in one element. This eliminates the need for separate retention plates and their complex placement procedures, while maintaining reliable anchoring of the shroud to the blade ends
Solution Approach 2:
The porous socket acts as an intermediary structure between the shroud and blade ends, providing a built-in mechanism for material penetration and mechanical engagement. This intermediary design simplifies the fastening process by eliminating the need for complex plate placement manipulations while ensuring reliable anchoring
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 solution increases the anchoring strength between the blade and socket, provides progressive failure in case of breakage, and simplifies the replacement process by using a removable thermoplastic layer, reducing physical and chemical operations.
Implementation Method 1
a cementation layer at the interface between the airfoil and the socket so as to fasten the airfoil to the wall by bonding
Implementation Method 2
the interface comprises asperities in contact with the fastening layer so as to ensure anchoring by engagement of material
Data Source
AI summary
The present application is concerned with a blading structure of a compressor of an axial turbomachine for an aircraft. The blading structure includes a wall, such as a composite internal shroud with an organic matrix, which is intended to radially delimit a primary annular flow of the turbomachine and which comprises a fastening socket. The structure additionally has a blade fastened in the fastening socket and extending radially with respect to the wall, and a fastening layer at the interface between the blade and the socket. The interface includes asperities hugging the fastening layer, so as to ensure anchoring by engagement of material in order to fasten the blade in the socket by bonding. The present application also proposes a low-pressure compressor with an internal shroud with sockets bonded to blades.