Gas Turbine Combustor Liner Cooling Structure with Acute Angle Inlet Holes
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Solution Overview
Problem
The pressure drop phenomenon in the compressed air flow for cooling the liner of a gas turbine combustor restricts efficient cooling, limiting the ability to handle increasing combustion temperatures and reduce pressure loss.
Innovation Solution
A liner cooling structure with a first flow passage for the main stream of compressed air and a second flow passage with inlet holes arranged at an acute angle to the first passage, allowing the auxiliary stream to join the main stream, reducing pressure loss and enhancing mixing efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If compressed air flows through inlet holes perpendicular to the main stream, then cooling of the liner is achieved, but pressure loss increases significantly
Solution Approach 1:
The inlet holes are arranged at an acute angle (30-60 degrees) relative to the main stream direction rather than perpendicular, creating an asymmetric flow pattern that reduces collision intensity and pressure loss while maintaining cooling effectiveness
Solution Approach 2:
The solution transitions from a single-dimensional perpendicular injection to a multi-dimensional acute-angle injection pattern, allowing the auxiliary stream to join the main stream more gradually and reduce turbulent mixing losses
2Loss of energy
If the acute angle configuration is used for inlet holes, then pressure loss is reduced, but the structural complexity of the flow sleeve increases
Solution Approach 1:
The design optimizes the acute angle parameter within a specific range (30-60 degrees) to achieve the best balance between pressure loss reduction and structural simplicity, avoiding excessive complexity while maintaining performance benefits
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 significantly reduces pressure loss and improves cooling efficiency by smoothly mixing hot and cold air streams, enabling the liner to operate effectively at higher combustion temperatures.
Implementation Method 1
the auxiliary stream of compressed air passing in the second direction joining the main stream of compressed air passing in the first direction such that the second direction forms an acute angle with the first direction
Implementation Method 2
a portion of the compressed air supplied from the compressor may be directed into the inlet holes and joins with compressed air passing through the inner annular space while in contact with outer surfaces of the liner and transition piece
Data Source
AI summary
A liner cooling structure of a duct assembly reduces pressure loss generated in the compressed air flow for cooling the liner. The duct assembly includes a liner, a transition piece, and a flow sleeve, and the transition piece and the flow sleeve form a transition piece channel through which a main stream of compressed air is introduced to the duct assembly. The liner cooling structure includes a first flow passage through which the main stream of compressed air passes in a first direction; and a second flow passage formed as a plurality of inlet holes in the flow sleeve to communicate with the first flow passage and configured to pass an auxiliary stream of compressed air in a second direction from outside the flow sleeve to inside the flow sleeve, the auxiliary stream joining the main stream such that the second direction forms an acute angle with the first direction.