Gas Turbine Vane Shroud Joint Relief Area Design
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Solution Overview
Problem
In gas turbine engine vane assemblies, existing joint designs between vanes and shrouds face challenges with flowable attachment materials either obstructing airflow or causing damage to vanes due to lug configurations, as enlarged lugs can prevent material from reaching desired areas or allow it to spread beyond intended surfaces.
Innovation Solution
The design incorporates a relief area between the radial wall and slot wall, with a triangular, curved, or rectangular cross-section, allowing the flowable attachment material to be disposed between the lug and slot wall, preventing contact with high-stress areas and minimizing airflow obstruction by providing a space for the material to flow, thus preventing damage and maintaining aerodynamics.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If enlarged lugs are used to prevent flowable attachment material from reaching the airfoil, then the attachment material is contained, but the lugs obstruct the desired air flow cross-sectional area
Solution Approach 1:
The patent introduces a relief area that extends axially (in the longitudinal dimension) between the lug and the airfoil surface. This axial dimension provides a pathway for the attachment material to flow toward the airfoil without requiring the lugs to extend radially outward, thereby containing the material while preserving the air flow cross-sectional area.
2Productivity
If lugs do not extend radially beyond the shroud walls, then air flow is maintained, but the flowable attachment material can move beyond the lug and toward surfaces of the airfoil causing damage
Solution Approach 1:
The relief area acts as an intermediary zone between the lug and the airfoil surface. It provides a designated space where the flowable attachment material can be contained and directed, preventing direct contact with the airfoil surface while maintaining the aerodynamic profile.
Solution Approach 2:
By utilizing the axial dimension to create a relief area, the patent provides a third-dimensional pathway for attachment material containment. This allows the lugs to remain compact (not extending radially beyond shroud walls) while still preventing material from reaching the airfoil through the axial relief space.
3Strength
If flowable attachment material is deposited between lugs and slots, then the vanes are secured to shrouds, but the material may extend to locations on the airfoil or obstruct airflow
Solution Approach 1:
The relief area is specifically positioned and dimensioned to provide localized containment for the attachment material. By creating this dedicated space with appropriate geometry (depth and axial extent), the material is confined to the relief area rather than spreading to obstruct the air flow path or reach the airfoil surface.
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 effectively secures the vane assembly while preventing fatigue and maintaining engine efficiency by ensuring the flowable attachment material does not contact critical stress areas, thereby extending the life of the assembly and optimizing airflow.
Implementation Method 1
A flowable attachment material is disposed in the relief area for engagement of the vane to at least one of the inner and outer shrouds
Data Source
Figure 1
Figure 2~3
Figure 4A~6B
AI summary
A stator joint for a gas turbine engine has a center axis, and a shroud having a radial wall facing substantially radially with respect to the center axis. A slot wall defines in-part a slot in the shroud. A relief wall defines a relief area of the slot. The relief wall extends between the radial wall and the slot wall. A vane has an airfoil and a lug extending into the slot. A flowable attachment material is disposed in the relief area for engagement of the vane to the shroud. A vane assembly and a gas turbine engine are also disclosed.