Variable Vane Segment Cooling via Segmented Impingement
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Solution Overview
Problem
Gas turbine engines face challenges in cooling rotating vanes due to high pressure cooling air requirements, leading to uneven cooling air distribution and potential thermal deflections that can damage components, especially in low-pressure implementations where thinner airfoils necessitate larger cooling air supplies.
Innovation Solution
A variable vane pack design featuring an inner and outer platform with a pressure distribution plate and impingement plate, including a radially inward impingement plate and a radially outward pressure distribution plate, with slots and impingement openings for even airflow distribution, ensuring uniform cooling across the vane segment.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If high pressure cooling air supply is used to cool thinner airfoils in low-pressure rotating vane implementations, then cooling effectiveness is improved, but flow losses in the gas-path increase and device complexity increases
Solution Approach 1:
The cooling air supply system is segmented into multiple zones using radially inward and radially outward plates that create distinct cooling regions. This allows different pressure zones to be established, enabling effective cooling of thinner airfoils while controlling flow losses by directing cooling air through specific pathways that minimize disruption to the main gas path flow.
Solution Approach 2:
The cooling system implements local quality by creating high-pressure cooling zones specifically where needed on the airfoil surfaces through the plate structure. The radially inward and radially outward plates establish localized high-pressure regions that deliver cooling air precisely to thinner airfoil sections requiring enhanced cooling, rather than applying uniform high pressure throughout the entire system.
2Temperature
If high pressure cooling air supply is used to cool thinner airfoils in low-pressure rotating vane implementations, then cooling effectiveness is improved, but device complexity increases
Solution Approach 1:
The cooling air supply system is segmented into multiple zones using radially inward and radially outward plates that create distinct cooling regions. This allows different pressure zones to be established, enabling effective cooling of thinner airfoils while controlling flow losses by directing cooling air through specific pathways that minimize disruption to the main gas path flow.
Solution Approach 2:
The cooling system employs a nested structure where radially inward plates and radially outward plates are positioned concentrically around the airfoil, creating nested cooling zones. This nested arrangement allows multiple cooling functions to be integrated within a compact structure, reducing overall device complexity while maintaining effective cooling of thinner airfoils.
3Temperature
If cooling air is extracted from the compressor to cool turbine components, then component cooling is improved, but engine efficiency decreases
Solution Approach 1:
The cooling system implements local quality by creating high-pressure cooling zones specifically where needed on the airfoil surfaces through the plate structure. The radially inward and radially outward plates establish localized high-pressure regions that deliver cooling air precisely to thinner airfoil sections requiring enhanced cooling, rather than applying uniform high pressure throughout the entire system.
Solution Approach 2:
The system converts the potentially harmful effect of cooling air extraction into a benefit by using the extracted cooling air to create controlled high-pressure zones through the plate structure. This converts the loss of efficiency from air extraction into a useful function of localized pressure control that enhances cooling effectiveness where needed most.
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 solution provides a uniform cooling airflow pressure gradient across the vane pack, reducing thermal deflections and maintaining component integrity by effectively distributing cooling air, thus enhancing the operational reliability of gas turbine engines.
Implementation Method 1
passing the cooling air through a pressure distribution plate into an impingement plenum, thereby providing an even distribution of air pressure to the impingement plenum
Implementation Method 2
feeding the cooling air through impingement openings in an impingement plate, thereby impinging cooling air on a radially outward platform of the engine component and cooling the radially outward platform
Data Source
AI summary
A variable vane pack includes an inner platform, an outer platform, radially outward of the inner platform, a plurality of vanes connecting the inner platform to the outer platform, wherein the outer platform comprises a platform body and an impingement plate, the impingement plate having a radially inward impingement plate, a radially outward pressure distribution plate, and an impingement plenum defined between the radially inward impingement plate and the radially outward pressure distribution plate.