Non-linear Combustor Panel Endrail Interface for Gas Turbine Cooling
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Solution Overview
Problem
Combustor panels in gas turbine engines are susceptible to structural damage and oxidation due to high temperatures, leading to reduced operational life and potential cracking.
Innovation Solution
The design incorporates a configuration of combustor panels with a non-linear channel between adjacent panels, featuring bends and heat transfer pins, along with impingement and effusion holes, to obstruct direct line-of-sight and enhance convective cooling, thereby protecting the panels from high temperatures.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If combustor panels are exposed to hot combustion gases for high temperature operation, then power output and efficiency are improved, but structural damage and oxidation occur reducing panel life
Solution Approach 1:
A channel filled with cooling air is introduced as an intermediary between the hot combustion gases and the combustor panel. The channel obstructs direct line-of-sight exposure to hot gases, allowing the panel to operate at high temperatures without direct thermal contact, thus maintaining durability while enabling high temperature operation
Solution Approach 2:
Cooling air is introduced through the channel to provide convective cooling to the combustor panel. The pneumatic flow of cooling air creates a protective barrier that reduces heat transfer to the panel, allowing high temperature combustion gases to be utilized without compromising panel structural integrity
2Loss of energy
If a linear channel provides direct cooling path, then cooling efficiency is improved, but direct line-of-sight exposure to hot gases occurs reducing protection effectiveness
Solution Approach 1:
The channel is designed with a non-linear, curved path between the cooling air source and the combustor panel. This curvature obstructs direct line-of-sight from hot combustion gases to the panel while maintaining an effective cooling air flow path, thereby reducing direct thermal exposure while preserving cooling efficiency
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 improves heat transfer and durability, prolongs the operational life of combustor panels, and allows for higher temperature operation by creating a protective air film and enhancing cooling efficiency.
Implementation Method 1
enhance convective cooling, thereby protecting the panels from high temperatures
Implementation Method 2
improves heat transfer and durability, prolongs the operational life of combustor panels
Implementation Method 3
allows for higher temperature operation by creating a protective air film and enhancing cooling efficiency
Data Source
AI summary
A combustor (56) of a gas turbine engine (20) may include a combustor shell (104), a first combustor panel (111) coupled to the combustor shell (104), and a second combustor panel (112) coupled to the combustor shell (104). The first combustor panel (111) may have a first endrail (121) and the second combustor panel (112) may have a second endrail (122). An annular cooling cavity (117) may be defined between the combustor shell (104) and the first and second combustor panels (111, 112) and a channel (130) may be defined between the first endrail (121) and the second endrail (122), wherein direct line-of-sight through the channel (130) from the annular cooling cavity (117) to a combustor chamber (102) is obstructed. Said differently, the interface between the adjacent endrails (121, 122) may be non-linear, in a direction from the annular cooling cavity (117) to the combustor chamber (102).