Multi-Wall Blade Cooling Circuit Segmentation
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Solution Overview
Problem
Conventional gas turbine systems face challenges in effectively cooling turbine blades subjected to high temperature flows, which can lead to component failure and reduced performance.
Innovation Solution
A cooling circuit for a multi-wall blade is introduced, comprising a pressure side cavity, a suction side cavity, a central cavity with no adjacent surfaces, and a leading edge cavity, with impingement openings for efficient fluid coupling and distribution of cooling air, providing convection, impingement, and film cooling.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If conventional internal cooling channels are used in turbine blades, then the blade structure is simple, but the cooling efficiency is insufficient under high temperature flows
Solution Approach 1:
The cooling circuit is divided into multiple independent cavities (pressure side cavity, suction side cavity, central cavity, leading edge cavities) that can be separately designed and optimized. Each cavity serves specific cooling functions for different regions of the blade, allowing complex cooling patterns to be achieved through modular segmentation rather than a single complex channel system.
Solution Approach 2:
Different cavities are designed with different characteristics to meet local cooling requirements. The leading edge cavities have impingement openings for high-intensity cooling at the leading edge, while the pressure and suction side cavities provide film cooling for their respective surfaces. The central cavity collects and redistributes cooling air to lower heat load regions, creating locally optimized cooling zones throughout the blade.
2Reliability
If multiple cavities and impingement openings are added to enhance cooling, then cooling efficiency improves, but manufacturing complexity increases
Solution Approach 1:
Multiple cooling functions (impingement cooling, film cooling, heat sink cooling) are merged into a single integrated cooling circuit system. The cavities are interconnected to form a unified network that distributes cooling air throughout the blade, combining what would otherwise require separate systems into one manufacturable structure.
Solution Approach 2:
The central cavity serves multiple functions: it acts as a heat sink, collects spent cooling flow from the leading edge cavities, and redistributes the collected air to lower heat load regions. This multi-functionality reduces the need for separate dedicated systems for each function, simplifying manufacturing while maintaining comprehensive cooling coverage.
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 cooling circuit enhances the cooling efficiency of turbine blades by effectively distributing cooling air through various channels, reducing temperature and preventing component failure, thereby allowing gas turbine systems to operate at higher temperatures with improved performance.
Implementation Method 1
Cooling air provided by, for example, a compressor of a gas turbine system may be passed through the internal cooling channels to cool the turbine blades
Implementation Method 2
at least one impingement opening for fluidly coupling the first leading edge cavity with a second leading edge cavity
Implementation Method 3
providing convection, impingement, and film cooling
Data Source
AI summary
A cooling circuit according to an embodiment includes: a cooling circuit for a multi-wall blade, the cooling circuit including: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a central cavity disposed between the pressure side and suction side cavities, the central cavity including no surfaces adjacent the pressure and suction sides of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade; and at least one impingement opening for fluidly coupling the first leading edge cavity with a second leading edge cavity.