Gas Turbine Stator Vane Cooling Aperture Layout
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing air-cooled stator assemblies in gas turbine engines face inefficiencies due to the difficulty in effectively cooling blades with a limited amount of air, often resulting in air stagnation zones and inadequate cooling, especially where high-temperature combustion gases are present, and previous solutions like flow-rate control plates increase structural complexity and cost.
Innovation Solution
A stator assembly with a cooling passage and an adjustment member featuring two apertures spaced along the camber line of the stator vane, ensuring even airflow distribution and preventing stagnation zones, allowing for efficient cooling with a minimal amount of air by positioning apertures strategically to direct airflow evenly across the blade.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a single aperture is used to introduce cooling air into the cooling passage, then the structure is simple, but the cooling air flows only through the central portion and causes air stagnation zones, resulting in inadequate cooling
Solution Approach 1:
The single aperture is divided into multiple apertures (first aperture and second aperture) positioned at different locations along the camber line. This segmentation allows cooling air to be introduced at multiple points, distributing the flow more evenly throughout the cooling passage and eliminating stagnation zones while maintaining structural simplicity.
Solution Approach 2:
Different apertures are positioned at specific locations along the camber line to target different regions of the cooling passage. The first aperture is positioned to introduce air toward the front wall, while the second aperture is positioned to introduce air toward the rear wall, ensuring each region receives adequate cooling air distribution.
2Reliability
If a flow-rate control plate with multiple small apertures is used, then the cooling effectiveness is improved, but the structural complexity and cost increase
Solution Approach 1:
The multiple apertures are integrated directly into the adjustment member as a unified structure rather than using separate small apertures in a control plate. This merging approach achieves the same cooling effectiveness as multiple small apertures while simplifying the overall structure and reducing manufacturing complexity.
Solution Approach 2:
The adjustment member serves multiple functions: it covers the inlet to control air flow, distributes cooling air through multiple apertures, and eliminates the need for separate flow-rate control plates. This multi-functionality reduces structural complexity while maintaining cooling effectiveness.
3Reliability
If the amount of cooling air is increased, then the cooling effectiveness is improved, but the efficiency of the gas turbine engine decreases
Solution Approach 1:
Instead of using a single large aperture that would require excessive air flow, the solution uses multiple smaller apertures that collectively provide the necessary cooling air distribution. This partial action approach achieves effective cooling with a minimized total amount of air, preventing excessive energy loss.
Solution Approach 2:
The positions and sizes of the apertures are optimized to change the flow distribution parameters. By positioning apertures at specific distances along the camber line and adjusting their dimensions, the system achieves optimal cooling air distribution that maximizes cooling effectiveness while minimizing air consumption and energy loss.
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 ensures effective cooling of the stator assembly, particularly the front wall, where high-temperature gases are most impactful, by dispersing cooling air evenly, thereby enhancing the operational efficiency of the gas turbine engine while minimizing air consumption.
Implementation Method 1
a cooling air passage defined within the blade into which a compressed air from the compressor is introduced for the cooling of the blade
Implementation Method 2
the cooling air flows evenly in the cooling passage... the turbine stator assembly, in particular the upstream end thereof is effectively cooled
Data Source
AI summary
A gas turbine engine and a turbine stator assembly which is capable of being cooled effectively with a small amount of air. The stator assembly comprises a stator vane disposed to be exposed to a combustion gas passage. The stator vane comprises a cooling passage defined therein. The cooling passage is disposed on an upstream of the gas turbine engine and extending in a radial direction with respect to a central axis of the gas turbine engine. The stator vane also has an inlet communicated to a radially outward end of the cooling passage. The stator vane further has an adjustment member secured to the stator vane so that it covers the inlet. The adjustment member has two apertures for guiding a cooling air radially inwardly through the inlet into the cooling passage. The two apertures are spaced away from each other along a camber line of the stator vane.