Segmented Ceramic Matrix Composite Turbine Blade Platforms
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Solution Overview
Problem
The design of ceramic matrix composite blades in gas turbine engines faces challenges in withstanding heat and radial movement of hot gases, as conventional platform geometries can lead to manufacturing complexities and reduced mechanical properties.
Innovation Solution
The use of a turbine wheel design featuring a metallic disk with radially inward slots, ceramic matrix composite blades with integral airfoils, platforms, and retainer shoulders that extend circumferentially to block radial movement of hot gases, and independent platforms that act as dampers to reduce stress and improve manufacturing simplicity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If conventional platform geometry is used with ceramic matrix composite blades, then manufacturing complexity increases, but blade durability and heat resistance are compromised
Solution Approach 1:
The platform is divided into multiple segments that can be independently manufactured and then assembled. Each segment is formed separately using ceramic matrix composite materials and then joined to the blade and to each other, simplifying the manufacturing process while maintaining structural integrity and durability through proper segmentation and assembly procedures
Solution Approach 2:
The platform utilizes ceramic matrix composite materials that combine the advantages of ceramic heat resistance with composite material flexibility and manufacturability. This allows the platform to withstand high temperatures from combustion gases while enabling more straightforward manufacturing processes compared to conventional monolithic geometries
2Object-affected harmful factors
If platforms extend circumferentially in a single direction, then hot gas radial movement is blocked, but blade structural complexity increases
Solution Approach 1:
The platform structure implements local quality by extending circumferentially in only one direction rather than forming a complete circumferential barrier. This localized approach is sufficient to block radial inward movement of hot gases toward the metallic disk while maintaining simpler blade geometry compared to full circumferential platforms
Solution Approach 2:
Instead of having the platform extend in both directions symmetrically from the airfoil, the design extends the platform in only one circumferential direction. This asymmetric configuration achieves the same functional goal of blocking hot gas radial movement while reducing overall structural complexity
Data Source
AI summary
A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. The blades each fit within slots formed in the rotor disk to couple the blades to the rotor disk. Platform segments are arranged about each of the blades.