Transversely Angled Impingement Ribs for Gas Turbine Cooling
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Solution Overview
Problem
Certain components in gas turbine engines face challenges in cooling due to exposure to hot combustion gases, particularly in areas that are difficult to reach with internal cooling circuits.
Innovation Solution
The implementation of transversely angled impingement ribs and corresponding casting systems that include transversely angled openings to form these ribs, allowing for targeted cooling airflow to impinge on specific surfaces, enhancing heat transfer and cooling efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If internal cooling circuits are used to cool gas turbine engine components, then cooling coverage is provided, but certain portions of the components remain difficult to cool due to inaccessibility
Solution Approach 1:
The patent introduces transverse cooling ribs that extend perpendicular to the axial direction of the component, creating a three-dimensional cooling network. These ribs project cooling airflow from the internal cooling circuits to previously inaccessible external surfaces, effectively adding a transverse dimension to the cooling coverage and enabling heat removal from areas that were previously difficult to reach with conventional axial cooling circuits.
2Temperature
If cooling airflow is directed through internal cooling circuits, then heat transfer occurs, but targeted cooling of specific surfaces is insufficient
Solution Approach 1:
The transverse cooling ribs are strategically positioned and oriented to direct cooling airflow to specific high-heat-flux areas of the component. Each rib can be independently configured to target particular surfaces or regions that require enhanced cooling, allowing localized optimization of heat transfer efficiency rather than uniform cooling across the entire component.
Solution Approach 2:
By extending cooling ribs in the transverse direction perpendicular to the axial flow, the system creates multiple cooling zones that can be independently controlled. This dimensional expansion enables selective targeting of different component surfaces, providing versatility in adapting the cooling pattern to match the thermal requirements of specific areas.
3Temperature
If conventional cooling circuits are implemented, then cooling is provided, but cooling coverage to difficult-to-reach portions is insufficient
Solution Approach 1:
The transverse cooling ribs extend perpendicular to the axial direction of the component, creating a three-dimensional cooling network that reaches into previously inaccessible regions. This dimensional expansion significantly increases the total cooled surface area by bringing cooling airflow to external surfaces and hard-to-reach portions that conventional axial cooling circuits cannot effectively access.
Solution Approach 2:
The cooling system is divided into multiple discrete transverse ribs that can be independently configured and positioned. Each rib segment can be optimized to cool specific portions of the component, and the segmented structure allows better penetration into complex geometries, thereby increasing overall cooling coverage throughout the component volume.
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 cools critical components by directing cooling airflow through impingement holes in angled ribs, improving thermal management and extending the lifespan of engine parts under extreme conditions.
Implementation Method 1
cooling airflow that is communicated through a cooling circuit of the component. The plurality of transversely angled impingement ribs include at least one impingement hole that extends through the at least one impingement rib such that the cooling airflow can impinge on an interior surface of the component
Implementation Method 2
directing cooling airflow through impingement holes in angled ribs, improving thermal management and extending the lifespan of engine parts under extreme conditions
Data Source
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AI summary
A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a body portion that includes a first wall spaced apart from a second wall and disposed about a centerline axis. At least one rib extends between the first wall and the second wall. The at least one rib extends along a rib axis that is transversely angled relative to the centerline axis. At least one impingement hole extends through the at least one rib.