Single Crystal Superalloy Blade Tip Cladding
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Solution Overview
Problem
Current turbine blade designs face challenges in maintaining structural integrity at operating temperatures exceeding 1150°C, particularly at the tips or parapets which lack active cooling and are prone to high heat and stress, leading to potential deformation and reduced service life.
Innovation Solution
The implementation of a turbine blade with a single crystal superalloy material and a cladding layer composed of zirconia grain stabilized platinum alloy on the tip, providing creep resistance and thermal protection, along with an internal cooling circuit and specific coatings for oxidation resistance and thermal conductivity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If operating temperatures are increased to improve engine efficiency, then engine efficiency is improved, but blade structural integrity deteriorates due to excessive heat and stress
Solution Approach 1:
The blade incorporates different material properties in different regions: the tip region uses a platinum-based cladding layer with specific creep resistance properties, while the main blade body uses a nickel-based superalloy. This local differentiation allows the blade to withstand higher operating temperatures while maintaining structural integrity at the most vulnerable region.
Solution Approach 2:
The blade employs a composite structure combining a nickel-based superalloy substrate with a platinum-based cladding layer. This composite material system provides both the high-temperature strength of the superalloy and the creep resistance of the platinum-containing cladding, enabling operation at temperatures exceeding 1150°C without compromising structural integrity.
2Use of energy by moving object
If tip temperature exceeds 1150°C to improve efficiency, then engine efficiency is improved, but tip structural integrity deteriorates due to creep and deformation
Solution Approach 1:
The blade incorporates different material properties in different regions: the tip region uses a platinum-based cladding layer with specific creep resistance properties, while the main blade body uses a nickel-based superalloy. This local differentiation allows the blade to withstand higher operating temperatures while maintaining structural integrity at the most vulnerable region.
Solution Approach 2:
The cladding layer composition is specifically designed with platinum and zirconia to alter the material parameters at the tip region, providing enhanced creep resistance and structural stability at temperatures exceeding 1150°C, where the nickel-based superalloy alone would be insufficient.
3Temperature
If active cooling is added to the tip to reduce temperature, then thermal protection is improved, but device complexity increases
Solution Approach 1:
The blade tip material itself provides thermal protection through its inherent properties. The platinum-based cladding layer with zirconia stabilization offers high-temperature stability and creep resistance without requiring active cooling mechanisms, allowing the structure to 'self-protect' against thermal degradation.
Solution Approach 2:
The blade employs a composite structure combining a nickel-based superalloy substrate with a platinum-based cladding layer. This composite material system provides both the high-temperature strength of the superalloy and the creep resistance of the platinum-containing cladding, enabling operation at temperatures exceeding 1150°C without compromising structural integrity.
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 solution enhances the blade's ability to withstand extreme temperatures, reduces thermal mechanical fatigue, and improves service life by maintaining structural integrity and preventing unwanted deformation, while being relatively simple and cost-effective to manufacture.
Implementation Method 1
a cladding layer disposed over the tip, the cladding layer comprising a zirconia grain stabilized platinum alloy
Implementation Method 2
providing creep resistance and thermal protection
Implementation Method 3
the blade cooling scheme directs cooling air through an internal cooling circuit formed in the blade
Implementation Method 4
specific coatings for oxidation resistance and thermal conductivity
Data Source
Figure 1
Figure 2
Figure 3~5
AI summary
The blade (200) includes an airfoil (204) including a convex suction side wall (212), a concave pressure side wall (210), a leading edge (214), a trailing edge (216), a root (208), and a tip (222), the convex suction side wall (212), the concave pressure side wall (210), and the tip (222) each including interior surfaces that together define an internal cooling circuit, the airfoil (204) including a single crystal superalloy, and a cladding layer (250) disposed over the tip (222), the cladding layer (250) including a zirconia grain stabilized platinum alloy.