Turboengine Blading Member Retainer Bonding
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Solution Overview
Problem
Existing methods for assembling turboengine blading members, such as those involving in situ primary forming of retainer members through liquid casting, are expensive and time-consuming due to the need for preheating and complex process know-how, and often face challenges with high-temperature materials that exhibit poor welding properties.
Innovation Solution
A turboengine blading member assembly method that avoids in situ primary forming of retainer members by using pre-inserted retainer members within flutes on the connector post and receiver opening, which are then bonded to form a common retainer member, allowing for interlocking of the airfoil and platform members without the need for extensive heat treatment, and utilizing bonding methods like electron beam welding within a controlled gas atmosphere to reduce heat intake and enhance the assembly process.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If in situ primary forming of retainer members through liquid casting is used, then reliable joining of airfoil and platform members is achieved, but the assembly process becomes expensive and time-consuming due to preheating requirements
Solution Approach 1:
The retainer members are pre-formed separately from the airfoil and platform members, then inserted into position before final assembly. This eliminates the need for in situ casting and preheating during assembly, significantly reducing assembly time while maintaining reliable joining through controlled manufacturing of the retainer members beforehand
2Reliability
If in situ primary forming of retainer members through liquid casting is used, then reliable joining of airfoil and platform members is achieved, but the process complexity and cost increase due to extensive process know-how requirements
Solution Approach 1:
The retainer members are segmented as separate components that can be manufactured independently using standard processes, then assembled into the final structure. This segmentation eliminates the need for complex in situ casting processes while ensuring reliable joining through controlled manufacturing and assembly of pre-formed retainer members
3Strength
If welding of airfoil member to platform member is performed, then permanent joining is achieved, but the poor welding properties of high temperature materials make this challenging
Solution Approach 1:
The retainer members serve as intermediary components that mechanically connect the airfoil and platform members without requiring direct welding between these high-temperature materials. The retainer members can be manufactured from materials with favorable machining and assembly properties, eliminating the welding challenges associated with the airfoil and platform materials
4Strength
If airfoils and platforms are joined permanently, then structural integrity is maintained, but replacement of worn airfoils becomes difficult without damaging the platform
Solution Approach 1:
The retainer members are designed as separate, removable components that secure the airfoil to the platform. This segmentation allows the airfoil to be detached and replaced by simply removing the retainer members, while the platform and retainer members can be reused, maintaining structural integrity during operation but enabling easy maintenance
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 method reduces the complexity and cost of assembly by minimizing heat intake and eliminating the need for extensive process know-how, while providing a reliable and easily disassemblable joint that can withstand high-temperature conditions, facilitating the replacement of airfoil members without damaging the platform.
Implementation Method 1
The first and second retainer members are bonded to each other to provide a common retainer member
Implementation Method 2
utilizing bonding methods like electron beam welding within a controlled gas atmosphere to reduce heat intake
Data Source
Figure 1~2
Figure 3~4
Figure 5~6
AI summary
Disclosed is a turboengine blading member (1), comprising at least one platform member (2) and at least one airfoil member (3). A receiver through opening (21) extends through the platform member. The connector post is received within the receiver through opening. Each of the connector post and the receiver through opening comprise a retainer flute (25, 35) provided on the circumferential wall and extending along at least a part of the circumferential extent. The retainer flutes are arranged juxtaposed each other with the open sides facing each other such as to jointly form a joint retainer cavity. A first retainer member (41) is provided in one of the corresponding retainer flutes, a second retainer member (42) is provided in the other one of the corresponding retainer flutes, and the first and second retainer members are bonded to each other to provide a common retainer member (40) extending into both corresponding retainer flutes (25, 35), thereby retaining the connector post within the receiver through opening and interlocking the airfoil member and the platform member.