Gas Turbine Vane Thermal Barrier Coating Strategy
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Solution Overview
Problem
Gas turbine vanes and blades experience significant oxidation due to high temperatures, leading to premature degradation and reduced lifespan, with existing thermal barrier coatings either costly or weight-intensive.
Innovation Solution
A vane segment for gas turbines featuring a MCrAlY coating combined with locally applied thermal barrier coating (TBC) patches on the suction side of airfoils and inner platforms, optimized for specific high-temperature regions to enhance heat resistance while minimizing material usage and weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If a thermal barrier coating is applied to the entire surface of the vane segment, then heat resistance is improved, but weight and manufacturing cost increase
Solution Approach 1:
The patent applies thermal barrier coating only to specific high-temperature zones (suction side of airfoils and inner platforms) rather than the entire surface. This localized approach provides heat protection where most needed while minimizing unnecessary coating material, thus reducing weight while maintaining heat resistance in critical areas.
Solution Approach 2:
The vane segment surface is divided into distinct coating zones: TBC patches on suction sides and separate TBC patches on inner platforms. This segmentation allows selective application of thermal protection only where required, avoiding full-surface coating and thereby reducing overall weight and material cost.
2Temperature
If a thermal barrier coating is applied to the entire surface of the vane segment, then heat resistance is improved, but manufacturing cost increases
Solution Approach 1:
By applying TBC only to high-temperature zones (suction sides and inner platforms) rather than the entire surface, the patent reduces the quantity of expensive ceramic coating material required, thereby lowering manufacturing cost while maintaining adequate heat resistance in critical areas.
Solution Approach 2:
The coating application is segmented into discrete patches on specific surfaces, reducing total coating area and material consumption. This segmented approach lowers manufacturing cost compared to full-surface coating while providing targeted thermal protection.
3Duration of action of stationary object
If the vane segment is designed with full thermal barrier coating, then lifespan is improved, but weight increases
Solution Approach 1:
The patent extends lifespan by applying TBC to critical high-temperature zones (suction sides and inner platforms) that are most susceptible to oxidation and thermal degradation. This localized protection prevents premature failure in key areas without the weight penalty of full-surface coating.
Solution Approach 2:
By segmenting the coating application to specific high-risk zones, the patent provides sufficient thermal protection to extend component lifespan while minimizing the total weight added by the coating system.
4Reliability
If MCrAlY coating is applied to protect against oxidation, then reliability is improved, but manufacturing complexity increases
Solution Approach 1:
The patent uses a composite coating system combining MCrAlY (metallic bond coat providing oxidation resistance) with TBC (ceramic top coat providing thermal insulation). This composite approach enhances reliability by addressing both oxidation and thermal degradation through complementary materials with synergistic properties.
Solution Approach 2:
The dual-coating system is applied locally to high-temperature zones where oxidation resistance is most critical, providing reliable protection where needed without unnecessarily complicating the manufacturing of the entire component.
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 effectively increases the lifespan of gas turbine components by providing targeted heat protection without increasing weight or manufacturing costs, while maintaining aerodynamic performance and avoiding premature oxidation.
Implementation Method 1
a MCrAlY coating, wherein at least a section of the vane segment is coated with a thermal barrier coating (TBC)
Implementation Method 2
Due to the high temperature a significant oxidation of the base alloy can occur at the leading edge of an airfoil of the stator vane or, the rotor blade
Data Source
Figure 1~2
Figure 3~4
Figure 5
AI summary
The present invention relates to a vane device (100) for a gas turbine. The vane device (100) comprises a first airfoil (101) comprising a first suction side (107) and a first pressure side (108), a second airfoil (115) comprising a second suction side (118) and a second pressure side (119), an inner shroud (110) and an outer shroud (120). The first airfoil (101) and the second airfoil (115) are arranged between the inner shroud (110) and the outer shroud (120), wherein the first airfoil (101) and the second airfoil (115) are at least partially coated with a MCrAIY coating. At least the first suction side (107) comprises a first coated surface section (104) which is coated with a thermal barrier coating and which represents at least a part of the total surface of the first suction side (107). At least the inner shroud (110) or the outer shroud (120) comprises a further coated surface section (106) which is coated with a further thermal barrier coating. A corrsponding method of manufacturing is also provided.