Turbine Cooling Hole with Asymmetrical Diffusing Section
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Solution Overview
Problem
Turbine engine components face efficiency losses due to cooling requirements, as bleeding air from the compressor reduces engine efficiency and necessitates cooling of hot gas path components, which can be inefficient.
Innovation Solution
The design incorporates cooling holes with a diffusing section having an asymmetrical cross-sectional shape, increasing in area towards the heated surface, to enhance cooling fluid distribution and effectiveness, forming a wider and slower cooling film on heated surfaces.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If cooling air is bled from the compressor to cool hot gas path components, then component durability is improved, but engine efficiency deteriorates
Solution Approach 1:
The cooling hole geometry is optimized with a diffusing section that has an asymmetrical cross-sectional shape, creating localized high-velocity jet flow at the outlet to enhance cooling effectiveness only where needed on the heated surface, rather than using uniform cooling throughout
Solution Approach 2:
The cooling hole outlet geometry parameters are specifically designed with a diffusing section that increases in cross-sectional area toward the heated surface, changing the flow parameters to create a wider, slower cooling film that improves heat transfer efficiency
2Reliability
If conventional cooling holes are used, then manufacturing is simple, but cooling effectiveness is insufficient
Solution Approach 1:
The diffusing section is designed with an asymmetrical cross-sectional shape where the side walls are spaced differently relative to the centerline, creating an asymmetrical flow pattern that optimizes cooling film distribution on the heated surface
Solution Approach 2:
The cooling hole geometry transitions from a simple cylindrical shape to a three-dimensional diffusing section with varying cross-sectional area, adding geometric complexity to achieve superior cooling performance
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 configuration improves cooling effectiveness, increases durability of hot gas path components, reduces maintenance and manufacturing costs, and enhances specific fuel consumption by optimizing film cooling and fluid dynamics.
Implementation Method 1
at least one cooling hole comprising a connecting passage extending between an inlet at the cooled surface and an outlet defining a diffusing section and located at the heated surface having an increasing cross-sectional area in a direction toward the heated surface
Implementation Method 2
provides a cooling fluid flow... a cooled surface facing the cooling fluid flow
Data Source
AI summary
An apparatus and method relating to a cooling hole of a component of a turbine engine. The cooling hole can extend from an inlet to an outlet to define a connecting passage. The cooling hole can contain a diffusing section. The diffusing section can be defined by an interior surface having variable geometries.