Variable Porosity Combustor Liner for Gas Turbine Cooling

Solution Overview

Problem

Existing gas turbine engine combustor liners face challenges in efficiently managing cooling flows due to uniform porosity, which can lead to inadequate cooling in high-temperature regions and excessive cooling in low-temperature regions, resulting in inefficiencies and potential damage.

Innovation Solution

A variable porosity combustor liner is designed with different cooling flow amounts in various regions by strategically arranging cooling flow holes and passages in the walls, allowing for tailored cooling based on specific zones' requirements, achieved through a laminated alloy configuration with inner and outer sheets having distinct hole configurations and pedestals.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of manufacture

If uniform porosity is used in the combustor liner, then the structure is simple and easy to manufacture, but cooling is inadequate in high-temperature regions and excessive in low-temperature regions

Engineering Contradiction:

Improvemanufacturing simplicityVSAvoidcooling effectiveness

Core Design Contradiction:

Ease of manufactureVSReliability

Solution Approach 1:

The combustor liner incorporates variable porosity regions with different cooling flow amounts tailored to specific zones. High-temperature regions have higher porosity for increased cooling, while low-temperature regions have lower porosity to reduce excessive cooling. This local differentiation optimizes cooling effectiveness across different areas of the combustor liner.

Inventive Principle:

Principle #3Local quality

Solution Approach 2:

The combustor liner is divided into multiple discrete porosity regions, each with independently controlled cooling flow characteristics. The liner includes a first porosity region with a first cooling flow amount and a second porosity region with a second cooling flow amount, allowing segmented control of cooling distribution to match thermal requirements of different zones.

Inventive Principle:

Principle #1Segmentation

2Reliability

If variable porosity regions are implemented, then cooling effectiveness is improved, but the structure becomes more complex

Engineering Contradiction:

Improvecooling effectivenessVSAvoidstructural complexity

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The combustor liner incorporates variable porosity regions with different cooling flow amounts tailored to specific zones. High-temperature regions have higher porosity for increased cooling, while low-temperature regions have lower porosity to reduce excessive cooling. This local differentiation optimizes cooling effectiveness across different areas of the combustor liner.

Inventive Principle:

Principle #3Local quality

Solution Approach 2:

The combustor liner is divided into multiple discrete porosity regions, each with independently controlled cooling flow characteristics. The liner includes a first porosity region with a first cooling flow amount and a second porosity region with a second cooling flow amount, allowing segmented control of cooling distribution to match thermal requirements of different zones.

Inventive Principle:

Principle #1Segmentation

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 enables targeted cooling, preventing overheating in critical areas while minimizing unnecessary cooling, thus enhancing the durability and efficiency of the combustor liner by optimizing cooling flow distribution.

Implementation Method 1

porous zones having respective different cooling flow amounts are formed in the combustor liner structure based on an arrangement of the cooling flow holes and cooling flow passages in the walls of the combustor liner

Methodology Applied

Scientific EffectConvection: Convection

Data Source

PatentUS10203115B2Gas turbine engine variable porosity combustor liner

Publication Date: 2019.02.12 ROLLS ROYCE CORP

AI summary

A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated alloy structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages.