Gas Turbine Combustor Tailored Temperature Profile
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Solution Overview
Problem
High fuel-air ratio combustors in gas turbine engines generate non-uniform thermal loads, compromising turbine section durability and thrust generation due to combustor section restrictions.
Innovation Solution
The method involves controlling airflow into a swirler and quench zone to achieve a uniform fuel-air mixture and radial profile, using a liner assembly with quench and trim holes to tailor the combustor flow, thereby reducing the pattern and profile factors to enhance fuel uniformity and reduce thermal stress on turbine components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If high fuel-air ratio is used to increase thrust generation, then productivity is improved, but non-uniform thermal loads are generated that compromise turbine section durability
Solution Approach 1:
The patent applies local quality by introducing a quench zone with specific geometric features (quench holes and trim holes) that create localized cooling effects in the combustor. This localized modification allows the system to maintain high fuel-air ratio for thrust generation while creating specific thermal zones that protect the turbine section from excessive thermal loads, thereby resolving the contradiction between productivity and reliability.
2Reliability
If combustor section restrictions are applied to manage thermal loads, then reliability is improved, but thrust generation is compromised
Solution Approach 1:
The patent employs parameter changes by modifying the flow distribution parameters through the quench zone geometry. By adjusting the number, size, and positioning of quench holes and trim holes, the system optimizes the cooling air distribution to achieve a balanced thermal profile. This allows maintaining high fuel-air ratio for thrust generation while controlling thermal loads to protect the turbine section, thus resolving the contradiction between reliability and productivity.
3Reliability
If cooling air is increased to reduce thermal stress on turbine components, then reliability is improved, but engine efficiency decreases
Solution Approach 1:
The patent applies partial action by providing cooling air through specific quench holes and trim holes only where needed to create the quench zone, rather than uniformly increasing cooling air throughout the combustor. This targeted approach protects the turbine components from excessive thermal stress while minimizing the overall cooling air requirement, thereby maintaining engine efficiency while improving reliability.
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 increases fuel-air ratio for thrust generation while maintaining acceptable combustion gas exit temperature distribution, extending turbine service life and reducing fuel burn, and allows for less cooling air usage, leading to improved engine efficiency and durability.
Implementation Method 1
controlling an airflow into a swirler, and controlling an airflow into a quench zone to provide a desired pattern factor
Implementation Method 2
controlling an airflow into a quench zone to provide a desired pattern factor
Data Source
AI summary
A method of tailoring a combustor flow for a gas turbine engine includes controlling an airflow into a swirler to be generally uniform and controlling an airflow into a quench zone to provide a desired pattern factor.