Ceramic Matrix Composite Turbine Blade with Independent Platform
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Solution Overview
Problem
The manufacture of turbine blades using ceramic matrix composite materials poses challenges due to material properties and manufacturing methods, particularly in creating detailed features that require complex integrated composite material processes.
Innovation Solution
A turbine blade assembly is configured with a primary member made from ceramic matrix composite materials and an independent platform, which is coupled using retainer blocks, clips, or a braze layer to block motion and secure the platform in place, allowing for separate fabrication and assembly of the airfoil and platform components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If turbine blades are manufactured using ceramic matrix composite materials with integrated detailed features, then high-temperature resistance and structural integrity are improved, but manufacturing complexity and difficulty increase significantly
Solution Approach 1:
The turbine blade is divided into separate components: a primary member made from ceramic matrix composite materials and an independent platform. This segmentation allows each component to be manufactured separately using appropriate processes, avoiding the complexity of creating integrated detailed features in a single monolithic composite structure while maintaining the high-temperature resistance and structural integrity of the CMC primary member.
Solution Approach 2:
A retaining structure consisting of retainer blocks and clips is introduced as an intermediary mechanism to connect the primary member and the independent platform. This retaining structure simplifies the manufacturing process by enabling separate fabrication of components that are subsequently assembled, rather than requiring complex integrated manufacturing of the entire blade assembly as a single composite piece.
2Manufacturing precision
If complex integrated composite material processes are used to create detailed features, then manufacturing precision and feature integration are improved, but production time and complexity increase
Solution Approach 1:
By segmenting the turbine blade into a primary member and an independent platform that can be manufactured separately and then assembled using the retaining structure, the invention avoids the time-consuming integrated composite material processes while achieving the necessary feature integration through mechanical assembly of pre-fabricated components.
Solution Approach 2:
The primary member and platform are prepared in advance as separate components before final assembly. This preliminary preparation allows each component to be optimized and manufactured independently using the most efficient processes for each, rather than requiring a single lengthy integrated manufacturing process, thereby improving overall production speed.
3Ease of manufacture
If separate components are used for primary member and platform, then manufacturing complexity is reduced and production is simplified, but assembly requirements and connection reliability challenges increase
Solution Approach 1:
The retaining structure with retainer blocks and clips serves as a reliable intermediary connection mechanism between the primary member and platform. This mechanical retention system provides robust connectivity that ensures the assembled components function as a unified structure, addressing connection reliability challenges while maintaining the manufacturing simplicity benefits of separate components.
Solution Approach 2:
The retainer blocks are coupled to both the primary member and the platform, merging these separate components into a functionally integrated assembly. This combining approach ensures reliable connection while allowing the components to be manufactured separately, thus resolving the contradiction between manufacturing simplicity and connection reliability.
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 approach simplifies the manufacturing process by enabling the use of separate components, potentially speeding up production and facilitating the creation of complex shapes, such as tip shrouds, while maintaining high-temperature resistance and efficiency.
Implementation Method 1
The independent platform may be formed to include an aperture that receives the attachment post and engages a substantially radially-inwardly facing surface of the airfoil to block radially-outward motion of the independent platform relative to the primary member
Implementation Method 2
a braze layer configured to resist radially-inward motion of the independent platform relative to the primary member
Implementation Method 3
Ceramic matrix composite materials are able to withstand very high temperatures, often without active cooling
Data Source
AI summary
A turbine blade assembly adapted for use in a gas turbine engine is disclosed in this paper. A primary member of the turbine blade assembly shaped to form an airfoil and comprises ceramic matrix composite materials. A independent platform of the turbine blade assembly is coupled to the primary member of the turbine blade assembly such that the primary member need not be shaped to provide the platform.