Gas Turbine Blade Graded Material Cooling
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Solution Overview
Problem
Current additive manufacturing techniques cannot create single crystal materials, and traditional casting methods are costly and inefficient for producing gas turbine engine blades with intricate cooling configurations.
Innovation Solution
The use of functionally graded materials, such as nickel alloy and ceramic, with progressively more ceramic towards the tip and more metallic alloy towards the root, combined with additive manufacturing to create complex cooling passages and structures within the airfoil, allowing for efficient cooling and reduced material costs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If traditional investment casting processes are used to manufacture turbine blades, then single crystal nickel alloys can be produced with superior high-temperature strength, but manufacturing costs are extremely high and manufacturing complexity is high due to intricate cooling configurations
Solution Approach 1:
The patent changes the manufacturing process parameters from traditional investment casting to additive manufacturing, enabling the production of turbine blades with functionally graded materials. This parameter change allows for reduced manufacturing costs and simplified production while maintaining the ability to create complex cooling configurations through digital modeling and direct fabrication
Solution Approach 2:
The patent employs functionally graded composite materials that transition from single crystal nickel alloy at the root to ceramic at the tip. This composite approach allows different material properties to be optimized for different regions: the metallic alloy provides high-temperature strength and ductility at the root, while the ceramic provides superior heat resistance at the tip, reducing the need for complex cooling systems
2Ease of manufacture
If additive manufacturing is used to create turbine blades, then manufacturing cost is reduced and design flexibility is increased, but single crystal materials cannot be produced
Solution Approach 1:
The patent applies local quality by creating a functionally graded structure where the material composition varies spatially from root to tip. The single crystal nickel alloy is localized to the root region where high-temperature strength and ductility are critical, while ceramic material is localized to the tip region where heat resistance is paramount. This local differentiation allows additive manufacturing to produce the blade without requiring single crystal formation throughout the entire structure
Solution Approach 2:
The patent segments the blade into distinct material zones: a metallic alloy region at the root, a transition zone with functionally graded composition in the middle, and a ceramic region at the tip. This segmentation allows each region to be optimized for its specific functional requirements while being manufactured as an integrated component through additive manufacturing processes
3Temperature
If ceramic material is used at the blade tip, then heat resistance is improved, but thermal shock resistance may be reduced without proper transition structure
Solution Approach 1:
The patent changes the material composition parameter gradually from the root to the tip through a functionally graded structure. This gradual parameter change creates a smooth transition in thermal and mechanical properties, preventing sudden property changes that would cause thermal stress concentrations and improve thermal shock resistance
Solution Approach 2:
The patent uses a composite structure with functionally graded materials that combine metallic alloy and ceramic phases. The intermediate transition zone contains a mixture of both materials, creating a gradient that bridges the thermal and mechanical property differences between the metallic root and ceramic tip, thereby preventing thermal shock failures
4Temperature
If intricate interior cooling configurations are added to turbine blades, then high-temperature operation capability is improved, but manufacturing complexity and cost increase
Solution Approach 1:
The patent extracts the cooling function from complex internal configurations and replaces it with a passive thermal barrier approach using ceramic material at the tip. The ceramic layer itself acts as a thermal insulator, reducing the heat flux into the blade interior and eliminating or simplifying the need for intricate internal cooling channels and fluid distribution systems
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 enables the production of gas turbine engine blades with advanced cooling configurations that improve thermal management and reduce material costs, leveraging additive manufacturing to create complex geometries that traditional methods cannot form.
Implementation Method 1
functionally graded materials, such as nickel alloy and ceramic, with progressively more ceramic towards the tip and more metallic alloy towards the root
Implementation Method 2
an exterior wall provides an interior cavity that is configured to supply a cooling fluid to the airfoil. Radially extending cooling passageways are provided within the exterior wall and are in fluid communication with the interior cavity
Data Source
Figure 1~2B
Figure 3~5
AI summary
A blade for a gas turbine engine includes an airfoil that extends a span from a root to a tip. The airfoil is provided by a first portion near the root and has a metallic alloy. A third portion near the tip has a refractory material. A second portion joins the first and third portions and has a functional graded material.