Gas Turbine Liner Cooling Device with Auxiliary Support
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Solution Overview
Problem
Related art liner cooling devices in gas turbines experience issues with compressed air forming vortices at the downstream end of the liner, leading to stagnant combustion gas.
Innovation Solution
A liner cooling device with a support portion including a support member and an auxiliary support member, featuring a cooling flow passage and a sealing portion, which prevents vortex formation by directing cooling air effectively and sealing gaps to ensure smooth airflow from the liner to the transition piece.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If compressed air is discharged through the cooling channel to cool the liner, then the liner cooling effect is improved, but vortex formation occurs at the downstream end causing combustion gas stagnation
Solution Approach 1:
The support portion is divided into a support member and an auxiliary support member, creating segmented structures that guide the cooling air flow. The auxiliary support member specifically segments the flow path to prevent vortex formation while maintaining cooling effectiveness.
Solution Approach 2:
The auxiliary support member acts as an intermediary element between the cooling air flow and the combustion gas flow. It mediates the interaction by directing the cooling air away from the combustion gas path, preventing vortex formation and stagnation.
2Area of stationary object
If the cooling channel discharges compressed air at the downstream end, then cooling coverage is improved, but airflow turbulence increases causing stagnation
Solution Approach 1:
The auxiliary support member is positioned at a specific location within the cooling channel to locally modify the flow characteristics. It creates a localized flow direction change that prevents turbulence and vortex formation in the critical downstream region.
Solution Approach 2:
The auxiliary support member introduces a dimensional element to the flow control by extending in a direction that guides the cooling air along a specific path. This dimensional addition helps maintain laminar flow and prevents three-dimensional vortex formation.
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
Prevents vortex formation and stagnation of combustion gas, allowing for efficient cooling of the liner and unobstructed flow of combustion gas to the transition piece, enhancing the operational efficiency of the gas turbine.
Implementation Method 1
a cooling flow passage through which cooling air moves to the transition piece
Implementation Method 2
cool an end portion of the liner
Data Source
AI summary
A liner cooling device for cooling a liner of a gas turbine is provided. The liner cooling device may include a support portion disposed between a liner and a transition piece of a gas turbine and configured to include a cooling flow passage through which cooling air moves to the transition piece. The support portion includes a support member disposed between the liner and the transition piece and an auxiliary support member disposed in the cooling flow passage and having a hole through which the cooling air passes.