Turboengine Blading Member Cantilever Trailing Edge
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Solution Overview
Problem
Turboengine blading members face stress concentrations and reduced fatigue strength due to thermal and mechanical loading, particularly at the transition areas between the airfoil and platform, exacerbated by material and manufacturing differences, leading to potential cracks and reduced structural integrity.
Innovation Solution
A turboengine blading member design where the trailing edge section cantilevers from the profile body without a rigid connection to the platform, allowing for thermal expansion compensation and reduced notch effects, with a recessed indentation on the platform to form a labyrinth seal and facilitate coolant supply, enabling the use of different materials and manufacturing processes for the airfoil and platform.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If the trailing edge section is rigidly connected to the platform, then structural support is improved, but stress concentrations and notch effects increase at the transition area
Solution Approach 1:
The trailing edge section is extracted from the rigid platform connection and allowed to cantilever freely. This removes the stress-inducing rigid constraint while maintaining structural support through the airfoil's own stiffness, eliminating notch effects at the transition area.
Solution Approach 2:
The blading member is segmented into distinct functional zones: the platform, the airfoil profile body, and the cantilevering trailing edge section. This segmentation allows each part to be optimized independently, with the trailing edge free from platform-induced stress concentrations.
2Adaptability or versatility
If the airfoil and platform are manufactured from different materials, then design flexibility and cooling efficiency are improved, but thermal expansion mismatch and stress induction increase
Solution Approach 1:
The blading member is divided into separable airfoil and platform components that can be manufactured from different materials optimized for their specific functions. The airfoil can use materials with high thermal conductivity for cooling, while the platform uses materials optimized for structural support, without inducing thermal stress.
3Productivity
If the trailing edge section is made thin for aerodynamic efficiency, then aerodynamic performance is improved, but mechanical strength and vulnerability to thermal loading increase
Solution Approach 1:
The trailing edge section is extracted from the stress-prone transition area to the platform and allowed to cantilever freely. This removes the mechanical and thermal stress concentrations that would compromise the thin section's strength, while maintaining the thin profile necessary for aerodynamic efficiency.
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 enhances the structural integrity and lifetime of the blading member by reducing stress concentrations, improving fatigue resistance, and allowing for more flexible manufacturing and assembly, while also reducing working fluid ingestion and leakage flow.
Implementation Method 1
allowing for thermal expansion compensation
Implementation Method 2
a recessed indentation on the platform to form a labyrinth seal and facilitate coolant supply, enabling the use of different materials and manufacturing processes for the airfoil and platform
Data Source
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AI summary
A turboengine blading member (1) is disclosed. The blading member comprises at least one airfoil (2) and at least one platform (31) provided at at least one of a base and a tip of the airfoil (2). The airfoil (2) comprising a profile body (23), a leading edge (21) provided at a first side of the profile body (23), and a trailing edge section (24) extending from a second side of the profile body (23) and opposite the leading edge (21). The profile body (23) is connected to the at least one platform (31). The trailing edge section (24) cantilevers from the profile body (23) and is provided without connection to the platform (31).