Offset Turbine Blade Cooling Turns Reduce Pressure Loss
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Solution Overview
Problem
Conventional gas turbine systems experience increased pressure loss in turbine blade cooling circuits, leading to higher feed pressures and leakages, which can result in inefficiencies and component failure due to high temperature flows.
Innovation Solution
The design incorporates a turbine blade with a central plenum and offset or angled turns in the cooling channels, utilizing a rib to direct gas flows in different directions, reducing impingement and pressure loss by combining flows into a single, combined flow within the central plenum, thereby minimizing pressure loss and leakage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional cooling channels are used in turbine blades, then cooling function is provided, but pressure loss increases leading to higher feed pressure requirements and increased leakages
Solution Approach 1:
The cooling channel is divided into multiple segments including first and second turns with different orientations. Each turn is designed to handle flow from specific directions, segmenting the flow paths to prevent harmful impingement while maintaining effective cooling coverage of the turbine blade.
Solution Approach 2:
The first and second turns are designed with asymmetric orientations - the first turn redirects flow at a first orientation while the second turn redirects flow at a second orientation different from the first. This asymmetric design optimizes flow distribution and prevents impingement in the plenum chamber.
2Reliability
If higher feed pressure is used to maintain gas-path pressure margin, then adequate cooling is achieved, but leakages in secondary flow circuits increase
Solution Approach 1:
The design converts the potential harm of flow impingement into benefit by strategically orienting turns to redirect flows away from each other. This prevents the harmful effect of impingement-induced pressure loss, thereby reducing leakages without requiring higher feed pressure to maintain cooling adequacy.
3Reliability
If cooling channels redirect flows into central plenum, then cooling coverage is improved, but flow impingement occurs causing pressure loss
Solution Approach 1:
Different regions of the cooling channel are designed with different local qualities - the first turn has specific orientation characteristics for handling flow from one direction, while the second turn has different orientation characteristics for flow from another direction. This localized optimization prevents impingement at critical locations while maintaining comprehensive cooling coverage.
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 reduces pressure loss, allowing for lower feed pressures, lower leakages, and improved thermal efficiency by preventing flow impingement, thus maintaining an adequate gas-path pressure margin while reducing component stress from high temperatures.
Implementation Method 1
a first turn for redirecting a first flow of gas flowing through the first channel of the turbine blade into the central plenum of the turbine blade; and a second turn for redirecting a second flow of gas flowing through the second channel of the turbine blade into the central plenum
Implementation Method 2
the rib directs the first flow of gas in a first direction into the central plenum, and wherein the rib directs the second flow of gas in a second, different direction into the central plenum
Data Source
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AI summary
A turbine blade cooling system according to an embodiment includes: a first turn 60, 160 for redirecting a first flow of gas flowing through a first channel 28 of a turbine blade 6 into a central plenum 44 of the turbine blade 6; and a second turn 70, 170 for redirecting a second flow of gas flowing through a second channel 38 of the turbine blade 6 into the central plenum 44; wherein the first turn 60, 160 is offset from the second turn 70, 170 to reduce impingement of the first flow of gas and the second flow of gas in the central plenum 44.