Modular Guide Vane Assembly with Shrink-Fit Liner
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Solution Overview
Problem
Existing guide vane assemblies in turbomachines lack modular designs that allow for efficient interchangeability and repair of damaged components, leading to increased maintenance costs and reduced component life due to the use of integral, non-replaceable structures.
Innovation Solution
A modular guide vane assembly comprising separate airfoil and platform components with interchangeable connections, utilizing force-fit, friction-locked, or metallic/ceramic bonding, and incorporating removable inserts and shells to resist thermal and physical stresses, allowing for selective material use and easy replacement of damaged parts.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of stationary object
If an integral, non-replaceable guide vane structure is used, then manufacturing simplicity is maintained, but component life is reduced and maintenance costs increase due to inability to replace damaged parts selectively
Solution Approach 1:
The guide vane assembly is divided into multiple replaceable elements including the airfoil, inner platform, outer platform, and flow-applied liner, allowing selective replacement of damaged components rather than replacing the entire assembly. This segmentation enables extended component life through modular repair strategies.
Solution Approach 2:
The modular design allows damaged elements such as the airfoil or liner to be discarded and replaced while recovering and reusing undamaged components like the platforms, reducing overall maintenance costs and extending the operational life of the guide vane assembly.
2Ease of repair
If separate modular elements are used, then ease of repair is improved, but connection complexity increases due to multiple joining methods required
Solution Approach 1:
The guide vane is segmented into airfoil, platforms, and liner elements that can be independently removed and replaced, significantly improving ease of repair while the standardized connection interfaces minimize the added complexity.
Solution Approach 2:
Connection elements serve as intermediaries between the airfoil and platforms, providing standardized interfaces that simplify the joining process. These intermediaries enable easy assembly and disassembly while maintaining structural integrity, balancing repairability with connection complexity.
3Manufacturing precision
If various materials are used in modular components, then aerodynamic performance is optimized, but manufacturing complexity increases due to multiple material processing requirements
Solution Approach 1:
Different materials are applied to specific components based on their functional requirements: ceramic matrix composites for the liner to resist thermal stress, metallic alloys for the airfoil and platforms for structural strength, and sealing materials at interfaces. This local quality optimization achieves superior aerodynamic performance while managing manufacturing complexity through specialized component fabrication.
4Stability of the object's composition
If force-fit and permanent connections are used, then structural stability is improved, but ease of operation deteriorates due to difficulty in disassembly for maintenance
Solution Approach 1:
The connection system incorporates both permanent bonds (brazing, welding) for structural stability and detachable elements (mechanical fasteners, interlocking features) that allow controlled disassembly. This dynamic connection approach maintains structural integrity during operation while enabling maintenance access when needed.
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
The modular design enhances component life, reduces maintenance costs, and optimizes aerodynamic performance by enabling the use of various materials and flexible cooling configurations, while minimizing hot gas infiltration and thermal deformations.
Implementation Method 1
the flow-charged outer hot gas path liner is connected to the guide vane airfoil by using a shrinkage joint
Implementation Method 2
the assembling of the airfoil with respect to at least the platform is based on a force-fit and/or a form-fit connection
Implementation Method 3
The detachable or permanent connection comprises force closure means which have bolt or rivet finish, or a HT brazing step
Data Source
Figure 1~2
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AI summary
The invention relates to a guide vane assembly of a turbomachine on the basis of a modular structure, wherein the guide vane elements comprise at least an airfoil, an inner platform, an outer platform, wherein the guide vane airfoil and/or platforms have at its one ending provisions for the purpose of a connection of the guide vane elements among each other. The connections of the guide vane elements among each other are configured as a detachable, permanent or semi-permanent fixation with respect to the radial or quasi-radial extension of the airfoil compared to the rotor axis of the turbomachine. The assembling of the airfoil with respect to at least one platform is based on a force-fit and/or a form-fit connection, or the assembling of the airfoil with respect to at least one platform is based on the use of a metallic and/or ceramic fitting surface, or the assembling of the airfoil with respect to at least one platform is based on force closure means with a detachable, permanent or semi-permanent fixation. At least the guide vane airfoil or an alternative base structure of the airfoil comprises at least one flow-charged outer hot gas path liner, which encases at least one part of the guide vane airfoil. The flow-charged outer hot gas path liner is connected with respect to the guide vane airfoil or alternative base structure of the airfoil by using a shrinking joint.