Turbine Airfoil Flow Enhancer for Cooling Efficiency
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Solution Overview
Problem
Turbine engine components, such as airfoils, face challenges in effectively cooling high-temperature areas due to inadequate cooling flow and heat transfer efficiency, particularly in regions like the leading edge, trailing edge, and tip, where traditional cooling methods fall short in managing temperature distribution and heat pickup.
Innovation Solution
The design incorporates at least two ribs within the airfoil to define a cooling passage and a flow enhancer extending between these ribs, spaced from the pressure and suction sides, which increases the speed of cooling fluid flow and enhances heat transfer by creating turbulent conditions, thereby improving cooling efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If traditional cooling circuits are used to route cooling air through the airfoil, then cooling is provided to turbine components, but the cooling flow is inadequate and heat transfer efficiency is insufficient in high-temperature regions
Solution Approach 1:
The airfoil interior is divided into multiple cooling circuits (first cooling circuit, second cooling circuit, third cooling circuit) with dedicated flow enhancers in each. This segmentation allows independent optimization of cooling flow in different regions, enabling adequate cooling flow distribution to high-temperature areas without requiring a single large cooling flow that would be inefficient
Solution Approach 2:
Flow enhancers (such as turbulators or vortex generators) are introduced as intermediary elements within the cooling passages. These flow enhancers act as mediators that actively manipulate the cooling air flow, creating turbulence and enhancing heat transfer coefficients, thereby improving cooling efficiency without increasing the total cooling flow quantity
2Temperature
If cooling air is ducted from compressors to turbine components, then cooling is achieved, but heat transfer efficiency remains insufficient in leading edge, trailing edge, and tip regions
Solution Approach 1:
Different cooling circuits are dedicated to different regions of the airfoil (leading edge cooling circuit, trailing edge cooling circuit, tip cooling circuit). Each circuit is tailored to the specific thermal requirements of its region, with flow enhancers positioned to optimize local heat transfer. This local quality approach improves heat transfer efficiency in critical regions without requiring a single complex unified system
Solution Approach 2:
The cooling system is segmented into multiple independent cooling circuits, each serving specific high-temperature regions. This segmentation allows for targeted heat transfer enhancement in leading edges, trailing edges, and tips without unnecessarily complicating the entire cooling system, as each circuit can be independently optimized
3Temperature
If cooling passages are defined by ribs extending between pressure and suction sides, then cooling air can be routed through the airfoil, but flow speed and heat transfer coefficients are insufficient
Solution Approach 1:
Flow enhancers are introduced as intermediary elements within the cooling passages defined by ribs. These flow enhancers actively interact with the cooling air flow, generating turbulence and increasing flow velocity through pressure differentials and flow redirection. This mediation increases cooling air flow speed and heat transfer coefficients without requiring a complete redesign of the rib-based cooling passage structure
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 configuration increases the speed of cooling air within the passages, enhances heat transfer coefficients, and optimizes temperature distribution across the airfoil, ensuring more effective cooling of turbine engine components by managing airflow and heat transfer.
Implementation Method 1
a flow enhancer extending between these ribs, spaced from the pressure and suction sides, which increases the speed of cooling fluid flow and enhances heat transfer by creating turbulent conditions
Implementation Method 2
cooling is accomplished by ducting cooler air from the high and/or low-pressure compressors to the engine components that require cooling
Data Source
AI summary
An apparatus and method relating to an airfoil for a turbine engine and cooling channels within the airfoil. The airfoil includes an outer wall defining an interior bound by a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction. Further, the airfoil includes ribs located within the interior and a flow enhancer extending between the ribs.