Gas Turbine Combustor Liner Panel Interface Curvature
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Solution Overview
Problem
The combustor section of gas turbine engines faces durability and aerodynamics challenges due to steps between panels, dead regions, and cooling issues at interfaces where forward and aft panels merge, leading to adverse local aerodynamics and cooling inefficiencies.
Innovation Solution
Incorporating a furrowed surface on the combustor liner support shell that receives perimeter rails from both forward and aft liner panels, with angled and curved surfaces that include cooling impingement passages to enhance panel mounting and cooling efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If liner panels are merged at interfaces to form a continuous combustor lining, then the combustor structure is simplified, but steps between panels and dead regions are created causing adverse local aerodynamics and cooling inefficiencies
Solution Approach 1:
The patent applies curvature by replacing the conventional flat panel interface with a curved surface. The forward panel's downstream edge and the aft panel's upstream edge are both curved, allowing them to meet and form a smooth transition without steps or dead regions. This curved interface eliminates the aerodynamic adverse effects and cooling inefficiencies associated with flat panel joints while maintaining structural simplicity.
2Duration of action of stationary object
If cooling airflow is provided to meet service life requirements in high temperature combustor section, then durability is improved, but cooling inefficiencies occur at panel interfaces
Solution Approach 1:
The curved panel interfaces eliminate dead regions where hot gases could stagnate and reduce cooling effectiveness. The smooth curved transition allows cooling airflow to flow continuously without disruption, maintaining efficient heat removal from the panel surfaces and improving overall cooling efficiency while extending service life.
3Strength
If perimeter rails contact the inner surface of combustor liner support shells, then liner panels are mounted securely, but leakage occurs at panel interfaces
Solution Approach 1:
The curved interface design eliminates steps and gaps between panels that would otherwise allow leakage. The smooth curved transition from forward to aft panels creates a continuous surface that prevents gas leakage at the panel interface while maintaining secure mounting of the perimeter rails to the support shell.
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 solution improves panel durability, reduces leakage, and enhances cooling efficiency by creating a concave surface for improved airflow and heat management, while also serving as a dirt and particle separator.
Implementation Method 1
at least one of the first surface and the second surface include a cooling impingement passage
Implementation Method 2
the first surface and the second surface are angled with respect to the combustor liner shell surface and the displaced surface
Data Source
AI summary
A combustor for a gas turbine engine including a combustor liner support shell with a furrow formed therein; a forward liner panel mounted to the support shell via a multiple of studs, the forward liner panel including a forward liner panel rail the extends into the furrow; and an aft liner panel mounted to the support shell via a multiple of studs downstream of the forward liner panel, the aft liner panel including an aft liner panel rail that extends into the furrow.