Selective Thermal Barrier Coating for Gas Turbine Stator Vanes
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Gas turbine components, particularly turbine stator vanes, are susceptible to deformation and fracture due to high-temperature operating cycles, and existing thermal barrier coatings can alter the geometry, reducing efficiency and increasing the risk of vibratory stimulus-induced failure.
Innovation Solution
A selective thermal barrier coating is applied to specific surfaces of gas turbine stator vanes, focusing on areas prone to stress concentration at higher temperatures, while maintaining the geometry and mass flow characteristics of the components by leaving certain areas uncoated, such as the pressure sides at trailing edges and suction sides.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of stationary object
If a thermal barrier coating is applied to gas turbine components, then the component can withstand higher temperatures and its useful life is improved, but the geometry of the component is altered which adversely affects operating efficiency
Solution Approach 1:
The patent applies thermal barrier coating selectively to specific surfaces of the stator vane (suction side and pressure side) while leaving the trailing edge uncoated. This local differentiation allows the coated areas to withstand high temperatures while the uncoated trailing edge maintains the original geometry for efficient gas flow, thus resolving the contradiction between extending component life and preserving operating efficiency
2Temperature
If a thermal barrier coating is applied to gas turbine components, then the component can withstand higher temperatures, but the mass flow characteristics are altered which reduces operating efficiency
Solution Approach 1:
By coating only specific surfaces (suction side and pressure side) and leaving the trailing edge uncoated, the patent ensures that the mass flow path remains unobstructed. The uncoated trailing edge maintains the original flow characteristics while the coated surfaces provide temperature protection, thus resolving the contradiction between temperature resistance and mass flow preservation
3Duration of action of stationary object
If a thermal barrier coating is applied to gas turbine components, then the useful life is extended, but the risk of vibratory stimulus-induced failure increases due to geometry alteration
Solution Approach 1:
The selective coating approach preserves the original geometry at the trailing edge where gas flow occurs, preventing the creation of new flow patterns that could induce vibratory stimuli. Meanwhile, the coated surfaces provide thermal protection to extend component life, thus resolving the contradiction between extended useful life and reduced risk of vibratory failure
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 allows gas turbine components to withstand higher temperatures without compromising the mass flow and efficiency, reducing the likelihood of vibratory stimulus-induced failure and extending the components' useful life.
Implementation Method 1
apply a thermal barrier coating to at least some known gas turbine components, thereby improving the useful life of the components
Data Source
Figure 1
Figure 2
Figure 3
AI summary
A gas turbine component is provided. The gas turbine component includes an airfoil having a leading edge 222,230, a trailing edge 224,232, a suction side 226,234 extending from the leading edge to the trailing edge, and a pressure side 228,236 extending from the leading edge to the trailing edge opposite the suction side. The gas turbine component also includes a thermal barrier coating 240 applied to the airfoil pressure side such that an uncoated margin 278 is defined on the pressure side at the trailing edge.