Accelerator Insert for Gas Turbine Airfoil Cooling
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Solution Overview
Problem
Gas turbine engines face challenges in efficiently cooling high-temperature components like the high pressure turbine, where existing cooling methods may not adequately manage heat transfer due to temperature differences and airflow limitations.
Innovation Solution
The introduction of an accelerator insert within airfoil channels in gas turbine engines, which creates a reduced cross-sectional airflow passage to enhance airflow acceleration and heat transfer, utilizing turbulators for improved cooling while minimizing dust collection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If conventional cooling passages are used in turbine airfoils, then the structure is simple and easy to manufacture, but the heat transfer coefficient is insufficient and cooling efficiency is poor
Solution Approach 1:
The cooling channel is divided into multiple sections by inserting accelerator inserts at different locations along the channel. Each insert creates a localized flow acceleration zone, segmenting the otherwise uniform channel flow into multiple high-velocity regions that enhance heat transfer at critical locations.
Solution Approach 2:
The accelerator inserts modify the flow characteristics locally within the channel rather than changing the entire channel structure. By placing inserts at specific locations where cooling is most needed, the flow velocity and heat transfer coefficient are enhanced locally while maintaining simple channel geometry elsewhere.
2Temperature
If cooling air flow rate is increased to improve cooling efficiency, then heat transfer improves, but pressure balance is disrupted and engine performance deteriorates
Solution Approach 1:
The accelerator inserts change the flow parameters (velocity, pressure distribution) within the cooling channel by creating controlled flow acceleration zones. This allows the same mass flow rate to produce higher heat transfer coefficients due to increased velocity and enhanced turbulence, without requiring additional cooling air that would disrupt engine pressure balance.
3Temperature
If channel cross-sectional area is reduced to accelerate flow, then heat transfer coefficient increases, but flow resistance increases and pressure drop increases
Solution Approach 1:
Instead of reducing the channel cross-sectional area along its entire length, the channel is segmented into zones with and without inserts. The inserts create localized flow acceleration only where needed for heat transfer enhancement, while the rest of the channel maintains its original cross-sectional area, minimizing overall pressure drop.
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 solution effectively increases the heat transfer coefficient, enhancing cooling efficiency and maintaining a proper pressure balance, thereby improving the cooling of high-temperature components in gas turbine engines.
Implementation Method 1
an accelerator insert located within the channel defining an airflow passage. The airflow passage includes a reduced cross-sectional area to accelerate an airflow within the passage
Implementation Method 2
This solution effectively increases the heat transfer coefficient, enhancing cooling efficiency
Data Source
AI summary
An apparatus for a gas turbine engine can include an airfoil having an interior. The interior can be separated into one or more cooling air channels extending in a span-wise direction. An accelerator insert can be placed in one or more cooling air channels to define a reduced cross-sectional area within the cooling air channel to accelerate an airflow passing through the cooling air channel.