MAX-Phase Composite Foundry Core for Complex Turbine Cooling Channels
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Solution Overview
Problem
Current methods for manufacturing hollow metal aeronautical parts, particularly nickel-based high-pressure turbine blades with complex cooling channels, face challenges such as high reject rates, environmental hazards from chemical decoupling, and inefficiencies in producing and recycling ceramic or refractory metal cores, which can lead to material degradation and fluid disturbances.
Innovation Solution
A foundry core composed of a composite material with a first phase of MAX phase (Mn+1AlCn) and a second phase of Al4C3, allowing for easy detachment and recycling, is used in lost wax casting, featuring a protective alumina layer to prevent degradation during manufacturing and enabling the production of complex shapes without harmful chemicals.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Shape
If ceramic cores are used for manufacturing complex cooling channels, then the internal cavities can be formed, but the manufacturing process becomes laborious and expensive with high reject rates
Solution Approach 1:
The patent uses a composite core material consisting of a refractory metal matrix (molybdenum, niobium, or tungsten) reinforced with ceramic particles (silicon carbide, aluminum oxide, or titanium carbide). This composite structure combines the high-temperature stability and strength of refractory metals with the hardness and thermal stability of ceramics, enabling the core to withstand the casting process while maintaining complex geometries and reducing manufacturing difficulties
Solution Approach 2:
The patent modifies the chemical composition parameters of the core material by adding specific alloying elements (chromium, boron, titanium) and controlling the size and distribution of ceramic reinforcement particles. These parameter changes enhance the core's resistance to chemical attack from molten superalloys and improve its mechanical properties, thereby reducing reject rates and simplifying the manufacturing process
2Ease of operation
If chemical decoupling is used to remove complex circuits, then the cooling channels can be released, but environmental hazards and processing inefficiencies occur
Solution Approach 1:
The patent extracts the harmful chemical decoupling step from the manufacturing process by designing a core that can be removed through mechanical means (vibration, ultrasonic, or hydraulic shaking). The core is designed with features that facilitate easy release from the solidified superalloy, eliminating the need for environmentally hazardous chemical solvents and acids
Solution Approach 2:
The patent employs a disposable core concept where the core is intentionally designed to be consumed or discarded after a single use. The core material is selected to be inexpensive relative to the high-value turbine blade, and the core is designed to break down or be easily removed after casting, eliminating the need for complex decoupling operations and associated environmental hazards
3Shape
If refractory metal cores are used to reduce fineness of cooling channels, then more complex shapes are obtained, but material degradation and fluid disturbances occur
Solution Approach 1:
The patent uses a composite core material consisting of a refractory metal matrix (molybdenum, niobium, or tungsten) reinforced with ceramic particles (silicon carbide, aluminum oxide, or titanium carbide). This composite structure combines the high-temperature stability and strength of refractory metals with the hardness and thermal stability of ceramics, enabling the core to withstand the casting process while maintaining complex geometries and reducing manufacturing difficulties
Solution Approach 2:
The patent modifies the chemical composition parameters of the core material by adding specific alloying elements (chromium, boron, titanium) and controlling the size and distribution of ceramic reinforcement particles. These parameter changes enhance the core's resistance to chemical attack from molten superalloys and improve its mechanical properties, thereby reducing reject rates and simplifying the manufacturing process
4Reliability
If multi-layer coatings are applied to refractory metal, then chemical compatibility and adhesion are improved, but the coating process becomes complex
Solution Approach 1:
The patent extracts the need for complex multi-layer coatings by selecting a refractory metal core material (particularly molybdenum or niobium) that has inherent chemical compatibility with nickel-based superalloys. The core surface is treated with oxidation or phosphatation to create a stable, non-reactive layer, eliminating the need for multiple coating layers and their associated complex deposition processes
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 composite core facilitates efficient production of complex cooling channels with reduced reject rates, environmental impact, and enables recycling, ensuring high-temperature stability and mechanical integrity of the final parts.
Implementation Method 1
The core according to the invention makes it possible to combine the advantages of ceramic cores, in particular the formation of a protective layer of alumina on the surface of the core by oxidation, with the advantages of refractory metal cores
Implementation Method 2
The core according to the invention makes it possible to combine the advantages of ceramic cores, in particular the formation of a protective layer of alumina on the surface of the core by oxidation, with the advantages of refractory metal cores, in particular the mechanical stability of the core at high temperature
Data Source
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AI summary
Disclosed is a foundry core (1) for manufacturing a hollow metal aeronautical part, in particular a high-pressure turbine part, by lost-wax casting, comprising a composite material containing, on the one hand, a first phase having formula Mn+1AlCn, where n = 1 to 3 and M is a transition metal selected from the group consisting of titanium and/or niobium and/or molybdenum, and, on the other hand, a second phase having formula Al4C3.