Turbine Blade Tip Protrusion Blocks Hot Gas
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Solution Overview
Problem
Contemporary turbine blade cooling methods fail to effectively prevent hot combustion gas from invading the internal cooling passages, leading to reduced durability and maintenance challenges.
Innovation Solution
A turbine blade design featuring a protrusion at the blade tip with exit holes that communicate with the cooling passage, minimizing the intrusion of hot combustion gas and enhancing cooling efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If a turbine blade cooling passage is provided inside the airfoil, then the turbine blade can be cooled by cooling fluid flowing through the passage, but hot combustion gas invades the cooling passage reducing cooling effectiveness
Solution Approach 1:
The blade tip is segmented into multiple sections with individual protrusions, each creating a separate barrier against hot gas invasion. The cooling passage is also segmented with multiple exit holes distributed along the blade tip, allowing localized cooling while maintaining overall protection.
Solution Approach 2:
Protrusions are formed at the blade tip before the hot combustion gas can invade the cooling passage. These protrusions create a preliminary barrier that prevents hot gas from entering the cooling passage in the first place, rather than attempting to mitigate the effects after invasion occurs.
2Reliability
If the blade tip is formed with a protrusion, then hot combustion gas invasion is prevented, but the blade tip structure becomes more complex
Solution Approach 1:
The protrusions are merged with the blade tip structure as an integrated design rather than separate components. The protrusions are formed directly on the pressure and suction surfaces of the blade tip, combining the protective function with the existing aerodynamic surfaces.
Solution Approach 2:
The protrusions serve multiple functions: they act as barriers against hot gas invasion, maintain the aerodynamic shape of the blade tip, and work in conjunction with the exit holes to distribute cooling fluid effectively. This multi-functionality reduces the need for additional separate components.
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 design effectively prevents combustion gas from entering the cooling passage, extending the service life of the turbine blade and increasing maintenance cycles by maintaining the cooling fluid's effectiveness.
Implementation Method 1
a blade cooling passage that is formed inside the airfoil and communicates with an exit hole formed in the blade tip, the blade cooling passage configured to pass cooling fluid through the airfoil such that the cooling fluid exits the airfoil through the exit hole
Data Source
AI summary
A turbine blade includes a root to be mounted to a rotor; a platform having an inner side and an outer side, the inner side being coupled to the root; an airfoil extending from the outer side of the platform in a radial direction of the rotor and including an outer end on which a blade tip is formed; a protrusion formed in the blade tip; and a blade cooling passage that is formed inside the airfoil and communicates with an exit hole formed in the blade tip, the blade cooling passage to pass cooling fluid through the airfoil such that the cooling fluid exits the airfoil through the exit hole. The protrusion includes an outer side surface that is flush with an outer end surface of the airfoil and protrudes in a direction perpendicular to the radial direction to prevent hot combustion gas from invading the blade cooling passage.