Gas Turbine Combustor Liner Effusion Cooling
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Solution Overview
Problem
Gas turbine engines face challenges in achieving high-temperature survivability while minimizing cooling air usage, necessitating improved cooling efficiency in combustor liners.
Innovation Solution
The combustor liners incorporate a backside with cooling features such as trip strips, pyramid pin fins, and effusion holes that communicate through the liner, optimizing cooling efficiency by directing cooling air effectively.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If traditional cooling methods are used in combustor liners, then high-temperature survivability is achieved, but cooling air consumption increases
Solution Approach 1:
The patent employs effusion cooling panels with distributed porous structures that allow cooling air to permeate through the liner wall. The porous effusion holes create a distributed cooling effect across the entire liner surface, enabling high-temperature survivability while using less cooling air compared to traditional concentrated cooling methods
Solution Approach 2:
The patent transitions from conventional one-dimensional cooling (internal passages) to two-dimensional effusion cooling through the liner thickness, and further to three-dimensional cooling by adding backside features (protrusions, pins, ribs) that create complex cooling flow patterns in multiple directions, thereby improving cooling efficiency with reduced air consumption
2Temperature
If cooling efficiency is improved through additional cooling air, then temperature control is enhanced, but engine performance deteriorates due to reduced available air for combustion
Solution Approach 1:
The patent optimizes multiple parameters including effusion hole distribution patterns, hole diameter and density, backside feature geometries (pin size, rib height, protrusion shapes), and cooling air pressure ratios. These parameter optimizations enable effective temperature control with minimal cooling air, preserving more air for combustion and maintaining engine performance
Solution Approach 2:
The patent implements location-specific cooling features on the backside of the liner, placing different geometries (pins, ribs, protrusions) in specific high-heat-flux zones. This localized approach concentrates cooling effectiveness where most needed, achieving temperature control with reduced overall cooling air consumption
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 enhances cooling efficiency, allowing the combustor to withstand high temperatures with reduced cooling air consumption, thereby improving the overall performance of gas turbine engines.
Implementation Method 1
effusion cooling and backside features... effusion hole that communicates through the liner
Implementation Method 2
cooling feature projecting from the backside... pyramid pin fin... trip strip
Data Source
AI summary
A liner for a combustor of a turbine engine includes a cooling feature which projects from a backside and one or more effusion holes that communicate(s) through the liner. The effusion hole(s) surround an opening through said liner. The cooling feature may include a trip strip or a pyramid pin fin (e.g., a three-side pyramid pin fin, a conical pyramid pin fin). The effusion hole(s) may penetrate said cooling feature. The effusion hole(s) may define an angle less than or equal to ninety (90) degrees with respect to a face of said liner. The effusion hole(s) may be proximate an opening through said liner.