Double Shelf Squealer Tip Impingement Cooling Turbine Blade
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Solution Overview
Problem
Turbine blades in high-temperature environments face premature coating failure and substrate oxidation due to high heat loads at the trailing edge tip region, where conventional cooling methods like serpentine cooling and film holes are ineffective in managing gas path migration effects.
Innovation Solution
A double shelf squealer tip design with impingement cooling, featuring a serpentine cooling circuit and impingement holes that force coolant to exit through specific holes onto the squealer tip floor, enhancing heat transfer and local convection for improved cooling.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If serpentine cooling passages are used to cool turbine blades, then cooling coverage is improved, but cooling effectiveness at the trailing edge tip region deteriorates due to gas path migration effects
Solution Approach 1:
The cooling system is segmented into two distinct components: serpentine cooling passages for general blade cooling and impingement cooling holes specifically targeted at the trailing edge tip region. This segmentation allows each cooling method to address specific thermal challenges in different blade regions, with impingement cooling providing concentrated cooling where gas path migration creates highest thermal loads.
Solution Approach 2:
The patent applies local quality by providing enhanced cooling specifically at the trailing edge tip region through impingement cooling holes, rather than uniform cooling throughout the blade. The impingement holes are strategically positioned to target the squealer tip floor and trailing edge region, delivering concentrated coolant flow precisely where gas path migration effects create highest temperatures and greatest cooling demand.
2Temperature
If film holes are added to the trailing edge tip region, then cooling benefit is attempted, but configuration difficulty increases due to penetration requirements into cooling cavities
Solution Approach 1:
The patent employs pneumatic principles by using impingement cooling holes that utilize pressurized coolant flow dynamics to achieve effective cooling. The impingement holes are designed to project coolant jets onto the squealer tip floor and trailing edge region, leveraging fluid dynamics and pressure-driven flow to deliver concentrated cooling without requiring complex geometric configurations or penetration into cooling cavities.
3Ease of manufacture
If conventional squealer tip design is used, then manufacturing is simplified, but heat load management at the trailing edge tip deteriorates
Solution Approach 1:
The patent applies preliminary action by providing cooling to the trailing edge tip region before the highest thermal loads occur during operation. The impingement cooling holes are positioned to deliver coolant flow in advance to the squealer tip floor and trailing edge region, preventing temperature buildup and thermal damage before they can occur during high-stress operational conditions.
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 design extends the life and reliability of turbine blades by preventing premature coating failure and substrate oxidation, reducing maintenance and operational costs through enhanced cooling efficiency.
Implementation Method 1
The cooling circuit extends inside the airfoil between the pressure and suction sides and is bounded at its top by the blade tip section. As coolant flows through the cooling passages, heat is extracted from the blade, thereby cooling the part.
Implementation Method 2
one or more impingement holes through which coolant is expelled to cool the turbine blade
Implementation Method 3
one or more impingement holes through which coolant is expelled to cool the turbine blade
Data Source
AI summary
A turbine blade comprises a leading edge, a trailing edge, a squealer tip floor, and one or more walls arranged to form a cooling circuit within the turbine blade, the one or more walls forming an impingement shelf having one or more impingement holes through which coolant is expelled to cool the turbine blade.