CMC Turbine Blade Thermal Gradient Design
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Solution Overview
Problem
The high temperature and non-uniform inflow conditions in modern aero-engines pose significant challenges for ceramic matrix composite (CMC) turbine blades, as they exceed the heat resistance limits of metal blades and induce thermal stress due to differing thermal expansion coefficients.
Innovation Solution
A collaborative design system and method that utilizes a simulation analysis platform to generate temperature field parameters and extract convective heat transfer coefficients, followed by partitioning the CMC turbine blade and importing fluid-solid heat transfer boundary conditions into an optimization platform for multi-objective optimization of thermophysical property gradients. This process involves generating C nanotube contents for different regions based on material thermal conductivities to optimize the braided structure of the CMC.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If CMC turbine blades are used to withstand high temperatures exceeding metal heat resistance limits, then temperature resistance is improved, but thermal stress increases due to differing thermal expansion coefficients
Solution Approach 1:
The patent implements spatially varying thermal conductivity properties within the CMC turbine blade structure. Different regions of the blade have different thermal conductivity values, creating a gradient distribution that allows heat to be conducted more effectively in high-temperature zones while reducing thermal stress in other areas. This local variation in thermal properties resolves the contradiction between temperature resistance and thermal stress by optimizing heat flow paths throughout the blade structure.
2Ease of manufacture
If uniform material composition is used for simplicity, then manufacturing ease is improved, but thermal performance under non-uniform inflow conditions deteriorates
Solution Approach 1:
The patent changes the thermal conductivity parameter spatially throughout the CMC turbine blade structure. By varying the thermal conductivity parameter in different regions according to the thermal stress and heat flow requirements, the blade achieves optimized thermal performance under non-uniform inflow conditions. This parameter variation is implemented through controlled changes in the braided structure composition, allowing the material to adapt to local thermal conditions while maintaining manufacturability.
3Temperature
If detailed multi-objective optimization is performed on thermophysical property gradients, then thermal performance is improved, but computational complexity and design time increase
Solution Approach 1:
The patent divides the CMC turbine blade into multiple discrete regions, each with optimized thermal conductivity properties tailored to local thermal conditions. This regional decomposition approach allows multi-objective optimization to be performed on manageable subsets of the overall structure rather than the entire blade at once. Each region can be optimized independently for its specific thermal performance requirements, reducing computational complexity while achieving overall thermal optimization.
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 approach effectively reduces the maximum temperature and temperature gradient of CMC turbine blades under non-uniform inflow conditions, enhancing their thermal performance and durability.
Implementation Method 1
generating C nanotube contents of different regions of the CMC turbine blade based on a correspondence function and values of material thermal conductivities of the different regions
Data Source
AI summary
Disclosed is a collaborative design system and method for a thermophysical property gradient distribution and a braided structure of a CMC and a storage medium. The system comprises at least one storage medium and at least one processor. The at least one processor is configured to: generate a temperature field parameter of a surface of a CMC turbine blade under a non-uniform inflow condition based on a simulation analysis platform, and extract a convective heat transfer coefficient; partition the CMC turbine blade and import an extracted fluid-solid heat transfer boundary condition into an optimization platform; perform multi-objective optimization on the thermophysical property gradient distribution of the CMC turbine blade under the non-uniform inflow condition based on an optimization simulation tool; and generate C nanotube contents of different regions of the CMC turbine blade based on a correspondence function and values of material thermal conductivities of the different regions of the CMC turbine blade to realize the collaborative design of the thermophysical property gradient distribution and the braided structure of the CMC.