Gas Turbine Liner Panel with Intermediate Rail and Heat Transfer Augmentors
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Solution Overview
Problem
In gas turbine engines, the large tolerances between cast liner panels and sheet metal shells complicate effective sealing, especially under conditions of higher operational temperatures and lower emissions requirements, which can lead to reduced durability and increased emissions.
Innovation Solution
The introduction of a liner panel with an intermediate rail and heat transfer augmentors forming a gothic arch architecture, which extend from the liner panel towards the support shell, creating convergent passages that enhance cooling and sealing by directing cooling air and promoting turbulence for improved heat transfer and film cooling.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If large tolerances are used between cast liner panels and sheet metal shell, then manufacturing ease is improved, but sealing effectiveness deteriorates
Solution Approach 1:
A sealing member is introduced as an intermediary component between the liner panel and support shell. This sealing member includes a body portion that fills the gap created by large tolerances and a sealing surface that contacts both the liner panel and support shell to prevent combustion gas leakage, thus resolving the contradiction between ease of manufacture and sealing effectiveness
Solution Approach 2:
The sealing member is designed with specific geometric parameters including a body portion height that corresponds to the gap between components and a sealing surface configuration that optimizes contact pressure distribution. These parameter adjustments enable effective sealing despite large assembly tolerances
2Temperature
If cooling air is directed to impingement cavities between support shell and liner panels, then heat transfer is improved, but sealing effectiveness may deteriorate due to pressure equalization
Solution Approach 1:
The sealing member is positioned specifically at locations where combustion gas leakage is most likely to occur, providing localized sealing rather than uniform sealing throughout. The sealing surface is configured to contact specific regions of the liner panel and support shell to maintain sealing while allowing controlled cooling airflow
Solution Approach 2:
The sealing member acts as an intermediary that separates the cooling air flow path from the combustion gas path. It allows cooling air to pass through impingement cavities for heat transfer while preventing combustion gases from leaking through the same path, thus resolving the contradiction between heat transfer and sealing effectiveness
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 sealing efficiency, reduces emissions, and increases the durability of the combustor components by effectively managing heat transfer and airflow, thereby enhancing the operational reliability of the gas turbine engine.
Implementation Method 1
promoting turbulence for improved heat transfer
Implementation Method 2
directing cooling air and promoting turbulence for improved heat transfer
Implementation Method 3
effusion cool the passages and film cool a hot side of the liner panels
Data Source
AI summary
A liner panel is provided for use in a gas turbine engine. The liner panel includes an intermediate rail that extends from a cold side of a liner panel. The liner panel also includes a multiple of heat transfer augmentors, which generally decrease in height with respect to a distance from the intermediate rail.