Baffle Insert for Gas Turbine Airfoil Cooling
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Solution Overview
Problem
Gas turbine engine airfoil sections face high thermal and mechanical loads due to high combustion temperatures, leading to reduced service life and increased maintenance costs, necessitating effective cooling techniques.
Innovation Solution
A baffle insert is used within the airfoil's cooling passages to create smaller air passages, increasing Mach numbers and heat transfer through turbulence, enhancing convective cooling by directing cooling fluid flows through multiple conduits with a sealing member that isolates and alternates fluid paths, thereby improving heat transfer efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling passages are provided in airfoil sections, then thermal loads on turbine airfoils are reduced, but the complexity of the component increases due to the need for internal cooling structures
Solution Approach 1:
The cooling passage is divided into multiple segments or zones along the flow direction. Baffle inserts are placed at specific locations to segment the flow path, creating distinct cooling regions that can be independently optimized. This segmentation allows complex cooling requirements to be met through modular construction rather than a single complex passage.
Solution Approach 2:
Baffle inserts serve as intermediary elements within the cooling passage. These baffles mediate the interaction between the cooling fluid and the airfoil structure by directing flow patterns, creating turbulence, and enhancing heat transfer without requiring the entire passage structure to be complex. The baffles are removable and replaceable, adding flexibility to the system.
2Power
If high combustion temperatures are used, then power output is increased, but thermal and mechanical loads on turbine airfoils increase, reducing service life
Solution Approach 1:
The cooling system utilizes periodic or alternating flow patterns created by the baffle inserts. The baffles induce flow separation and reattachment, creating periodic turbulence that enhances convective heat transfer. This periodic action allows more efficient heat removal at higher combustion temperatures, enabling increased power output while maintaining airfoil reliability.
Solution Approach 2:
The baffle inserts change the flow parameters within the cooling passage by increasing turbulence intensity, modifying velocity profiles, and creating recirculation zones. These parameter changes enhance the heat transfer coefficient, allowing the airfoil to withstand higher combustion temperatures without compromising service life.
3Temperature
If cooling efficiency is increased through turbulence, then heat transfer is improved, but pressure loss in the cooling passages increases
Solution Approach 1:
Baffle inserts are strategically positioned at specific locations within the cooling passage where turbulence is most beneficial for heat transfer. Rather than creating turbulence throughout the entire passage, the baffles generate localized turbulent regions near the airfoil surface where heat transfer coefficients are lowest. This local quality approach improves heat transfer efficiency while minimizing overall pressure loss.
Solution Approach 2:
The baffle inserts create more turbulence than strictly necessary for basic cooling, but this excessive action is concentrated in specific regions where it provides maximum heat transfer benefit. The partial application of turbulence-generating elements allows the system to achieve superior heat transfer in critical areas without incurring excessive pressure loss across the entire cooling passage.
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 baffle insert enhances convective cooling, reduces operating temperatures, extends airfoil service life, and optimizes cooling flow efficiency, addressing the thermal challenges faced by gas turbine engines.
Implementation Method 1
The baffle insert having: a first fluid conduit having a first interior cavity extending therethrough; a second fluid conduit having a second interior cavity extending therethrough; and a member located between the first fluid conduit and the second fluid conduit, wherein the member fluidly couples the first interior cavity to an exterior of the second fluid conduit, and wherein the member fluidly couples the second interior cavity to an exterior of the first fluid conduit
Implementation Method 2
an insert for use in convective cooling of the airfoils of the gas turbine engine which are exposed to high-temperature working fluid flow
Data Source
AI summary
A baffle insert for a component of a gas turbine engine is provided. The baffle insert having: a first fluid conduit having a first interior cavity extending therethrough; a second fluid conduit having a second interior cavity extending therethrough; and a member located between the first fluid conduit and the second fluid conduit, wherein the member fluidly couples the first interior cavity to an exterior of the second fluid conduit, and wherein the member fluidly couples the second interior cavity to an exterior of the first fluid conduit and wherein the first interior cavity is isolated from the second interior cavity.