Multi-Wall Blade Cooling Circuit Design
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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 existing multi-wall blade cooling systems may not adequately distribute cooling air to maintain efficiency and performance at increased temperatures.
Innovation Solution
A cooling circuit for a multi-wall blade is introduced, comprising pressure side and suction side cavities, along with first and second leading edge cavities, that directs cooling air flow radially through these cavities to provide convection cooling and tip film cooling, enhancing heat management and air distribution.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional cooling systems are used in turbine blades, then the blade structure is simpler, but the blade cannot effectively withstand high temperature flows and may fail
Solution Approach 1:
The blade is divided into multiple walls with separate internal cooling channels for different functions. The multi-wall structure allows independent cooling circuits for near-wall cooling and central channel cooling, enabling targeted temperature control in different blade regions while maintaining overall structural integrity
Solution Approach 2:
Different cooling strategies are applied to different locations within the blade. Near-wall channels provide intensive cooling where heat flux is highest, while central channels provide broader cooling coverage. This localized approach optimizes cooling effectiveness without requiring complex systems throughout the entire blade structure
2Productivity
If higher temperature flows are used to increase performance and power output, then gas turbine efficiency improves, but the risk of component failure increases
Solution Approach 1:
Cooling air is introduced into the blade structure before it encounters the high-temperature gas flow. The internal cooling channels pre-cool the blade walls and surfaces, creating a thermal barrier that protects the blade material from the extreme temperatures of the combustion gases, thereby enabling the turbine to operate at higher temperatures without compromising reliability
3Quantity of substance
If near wall cooling channels are made small to reduce cooling flow requirements, then cooling air consumption decreases, but maintaining sufficient cooling velocity becomes challenging
Solution Approach 1:
The cross-sectional area and geometry of the near-wall cooling channels are optimized to maintain adequate flow velocity with reduced cooling air quantity. By carefully controlling channel dimensions and length, the system achieves effective convective cooling with lower mass flow rates, improving overall cooling efficiency
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 effectively manages heat dissipation across the multi-wall blade, maintaining performance and efficiency by ensuring adequate cooling air distribution and reuse, thereby extending the operational temperature range of the gas turbine system.
Implementation Method 1
directs cooling air flow radially through these cavities to provide convection cooling
Implementation Method 2
provide convection cooling and tip film cooling
Data Source
AI summary
A cooling circuit for a multi-wall blade according to an embodiment includes: 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 first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade, the first leading edge cavity located forward of the pressure and suction side cavities; and a second leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade, the second leading edge cavity located forward of the first leading edge cavity.