Combustion Liner Dilution Passage Geometry
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Solution Overview
Problem
Current combustion liners in gas turbine engines face inefficiencies in cooling and mixing of dilution air with primary combustion products, leading to high temperature pockets and increased NOx emissions due to either low turbulence from discrete dilution holes or high exit temperatures from annular dilution passages.
Innovation Solution
A combustor liner with a dilution passage featuring a concatenated geometry that integrates discrete dilution holes and annular slots, combining first and second dilution air flows to enhance jet penetration and mixing, reducing temperature and NOx emissions through a balanced air split ratio and hydraulic support/shielding.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If discrete dilution holes are used in the combustion liner, then the structure is simple and easy to manufacture, but the turbulence is low leading to poor mixing of dilution air with primary combustion products
Solution Approach 1:
The patent combines discrete dilution holes with annular dilution passages to create a hybrid dilution system. The discrete holes provide simple manufacturing and structural integrity, while the annular passages enhance turbulence and mixing efficiency. This merging of two different dilution approaches resolves the contradiction between ease of manufacture and mixing efficiency.
2Productivity
If annular dilution passages are used in the combustion liner, then the mixing and turbulence are improved, but the exit temperature becomes too high
Solution Approach 1:
The patent applies different dilution characteristics to different regions of the combustion liner. Discrete dilution holes are positioned in specific areas to provide localized cooling and temperature control, while annular passages are positioned in other areas to provide turbulence and mixing. This spatial differentiation of dilution quality allows the system to achieve good mixing without excessive exit temperatures.
3Ease of manufacture
If only discrete dilution holes are used, then the manufacturing is simple, but temperature pockets form due to insufficient mixing
Solution Approach 1:
The hybrid dilution system merges discrete holes and annular passages to eliminate temperature pockets. The annular passages create turbulence that promotes uniform mixing of dilution air with combustion products, preventing localized hot spots, while the discrete holes maintain manufacturing simplicity.
4Productivity
If a hybrid dilution system with concatenated geometry is implemented, then mixing and temperature control are improved, but the device complexity increases
Solution Approach 1:
The hybrid dilution system is segmented into distinct functional zones within the combustion liner. Discrete dilution holes and annular passages are positioned at different locations and orientations to perform specific functions. This segmentation allows each component to be optimized independently while working together to achieve improved combustion efficiency without excessive overall complexity.
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 integrated dilution air flow achieves rapid quenching and uniform temperature distribution within the core primary combustion zone, reducing NOx emissions and maintaining a combustor exit temperature profile within acceptable limits, thus improving combustion efficiency and extending turbine component life.
Implementation Method 1
enhance jet penetration and mixing, reducing temperature and NOx emissions through a balanced air split ratio and hydraulic support/shielding
Implementation Method 2
The integrated dilution air flow achieves rapid quenching and uniform temperature distribution within the core primary combustion zone
Implementation Method 3
hydraulic support/shielding
Data Source
AI summary
A liner for a combustor in a gas turbine engine and a related method. The liner includes a liner body having a cold side and a hot side. The liner includes a dilution passage having a concatenated geometry extending through the liner body. The concatenated geometry has a plurality of discrete dilution holes, an annular slot, and a plurality of dilution inserts. The dilution passage is configured (i) to integrate a first dilution air flow flowing through the dilution passage from the cold side to the hot side and a second dilution air flow flowing through the dilution passage from the cold side to the hot side into an integrated dilution air flow, and (ii) to inject the integrated dilution air flow into a core primary combustion zone of the combustor to attain a predetermined combustion state of the combustor.