Gas Turbine Shroud Cooling via Segmented Impingement Plates
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Solution Overview
Problem
Gas turbine engines face efficiency decreases due to increased temperatures causing shroud expansion and tip clearance issues, requiring localized cooling that varies by region, but existing methods often decrease engine efficiency when applying additional cooling fluid to the entire shroud.
Innovation Solution
A cooling system with first and second impingement plates positioned over target surfaces with different thicknesses, channeling a single flow of cooling fluid to absorb heat from both surfaces, optimizing heat transfer and reducing the need for additional cooling streams.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If additional cooling fluid is supplied to the entire shroud, then the shroud temperature is reduced and tip clearance is maintained, but the operating efficiency of the gas turbine engine decreases
Solution Approach 1:
The patent applies local quality by providing cooling only to specific high-temperature regions of the shroud (such as regions adjacent to turbine blades) rather than uniformly cooling the entire shroud. This is achieved through localized cooling holes and cooling passages positioned at thermally critical locations, allowing temperature control where needed while preserving engine efficiency by minimizing overall cooling fluid consumption.
2Stability of the object's composition
If the shroud is cooled uniformly, then temperature distribution is improved, but the complexity of the cooling system increases
Solution Approach 1:
The cooling system is segmented into multiple localized cooling zones with independent cooling passages and holes positioned at specific thermal hot spots. This segmentation allows each region to be cooled according to its specific thermal requirements, achieving stable temperature distribution without requiring a complex uniform cooling system across the entire shroud.
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 approach enhances the efficiency of the gas turbine engine by effectively cooling critical regions while minimizing weight and mechanical stress, maintaining engine performance without the efficiency losses associated with uniform cooling.
Implementation Method 1
channeling a first flow of cooling fluid towards the first target impingement surface... channeling a second flow of cooling fluid toward the second target impingement surface
Data Source
AI summary
A rotary machine includes a rotatable member and a casing extending circumferentially over the rotatable member. The casing includes first and second target impingement surfaces. The cooling system includes first and second impingement plates. The first impingement plate is positioned over the first target impingement surface and at least a portion of the second target impingement surface. The first impingement plate defines a plurality of first impingement holes configured to channel a first flow of cooling fluid toward the first target impingement surface. The second impingement plate is positioned over the second target impingement surface. The second impingement plate defines a plurality of second impingement holes configured to channel a second flow of cooling fluid toward the second target impingement surface. A thickness of the casing in the first target impingement surface is different than a thickness of the casing in the second target impingement surface.