Gas Turbine Combustor Liner Panel With Hemi-Spherical Protuberances
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Solution Overview
Problem
Gas turbine engine combustors face challenges in operating at high compressor exit temperatures, especially at high altitudes where reduced supply pressure results in increased heat loads due to convection and radiation, necessitating enhanced heat transfer capabilities.
Innovation Solution
The combustor liner panel incorporates hemi-spherical protuberances and angled effusion passages to increase surface area and promote turbulence, combined with impingement passages for efficient cooling, enhancing heat transfer and film cooling.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If the combustor operates at high compressor exit temperatures with reduced supply pressure at high altitude, then the heat loads from convection and radiation increase, but the heat transfer capability decreases
Solution Approach 1:
The patent employs hemi-spherical protuberances on the liner panel surface to increase surface area and promote turbulence in the cooling airflow. The curved spherical geometry enhances heat transfer coefficients by creating turbulent flow patterns and increasing the effective heat exchange surface area between the combustion gases and the liner panel
Solution Approach 2:
The patent introduces angled effusion passages that extend through the liner panel at specific angles rather than perpendicular to the surface. This angular configuration adds a dimensional component to the cooling airflow path, allowing coolant to emerge at angles that enhance film cooling effectiveness and increase the path length for heat transfer
2Loss of energy
If heat transfer augmentors are added to increase surface area and promote turbulence, then heat transfer coefficient increases, but device complexity increases
Solution Approach 1:
The patent combines multiple functions into the liner panel structure itself: the liner panel serves as both the thermal barrier and the mounting substrate for heat transfer augmentors. The effusion passages are integrated directly into the liner panel, eliminating the need for separate cooling systems and reducing overall device complexity while maintaining enhanced heat transfer capabilities
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 significantly increases the heat transfer coefficient, improves thermal efficiency, and maintains effective cooling even at reduced supply pressures, ensuring sustainable metal temperatures and efficient engine operation.
Implementation Method 1
The combustor liner panel incorporates hemi-spherical protuberances and angled effusion passages to increase surface area and promote turbulence, enhancing heat transfer
Implementation Method 2
These operational conditions result in relatively convection and radiation high heat loads
Implementation Method 3
A effusion passage is defined through the liner panel
Implementation Method 4
At least one of the multiple of impingement flow passages is directed toward the hemi-spherical protuberance
Implementation Method 5
A liner panel for a combustor of a gas turbine engine... maintains effective cooling even at reduced supply pressures, ensuring sustainable metal temperatures
Data Source
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AI summary
A liner panel for a combustor of a gas turbine engine includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a hemi-spherical protuberance.