Dual-Wall Combustor Tile Angled Ejection Slots
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Solution Overview
Problem
Gas turbine engine combustor walls face high temperatures, leading to potential premature wear and loss of tile attachment, which reduces the lifespan and efficiency of the engine due to inadequate cooling and hot spots.
Innovation Solution
A dual-wall combustor tile assembly with angled ejection slots and unique exit hole configurations, allowing cooling air to impinge on the hot surface and reattach effectively, enhancing film cooling and mechanical attachment reliability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling air is directed into a gap between spaced outer and inner walls, then the inner wall is cooled, but hot spots may form in certain areas of the combustion chamber wall
Solution Approach 1:
The patent applies local quality by varying the cooling hole distribution and orientation across different regions of the combustor liner. Cooling holes are strategically positioned and angled to direct cooling air to specific hot spot areas, allowing each region to receive customized cooling based on its thermal requirements rather than using a uniform cooling approach throughout the entire liner.
Solution Approach 2:
The patent introduces a third dimension to cooling by angling cooling holes to project cooling air not only radially outward but also axially and tangentially. This multi-directional cooling approach creates a three-dimensional cooling pattern that addresses hot spots more effectively than traditional radial cooling alone, distributing cooling more evenly across the combustion chamber wall surface.
2Use of energy by moving object
If high compressor exit pressures and temperatures are used, then thermal efficiency is improved, but the combustor chamber experiences much higher temperatures
Solution Approach 1:
The patent uses cooling air as an intermediary substance that absorbs excess heat from the combustion chamber walls. This cooling air, drawn from the compressor, acts as a thermal mediator between the high-temperature combustion environment and the structural liner, allowing the system to operate at high temperatures for efficiency while the liner remains protected at lower temperatures through the intervening cooling air layer.
3Reliability
If enhanced air cooling flow is provided, then hot spots are minimized, but more cooling air is required
Solution Approach 1:
The patent segments the cooling function by dividing the liner into multiple zones with different cooling hole patterns and orientations. Each segment addresses specific thermal conditions in its region, allowing cooling air to be distributed more efficiently to where it is most needed rather than requiring uniform high flow rates across the entire liner surface.
Solution Approach 2:
The patent employs dynamic cooling angles and variable hole geometries that optimize cooling air utilization. By angling cooling holes to project air along the inner wall surface and varying hole sizes and distributions, the system dynamically adapts cooling delivery to match thermal requirements, maximizing cooling effectiveness per unit of cooling air consumed.
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 provides improved film cooling effectiveness, reduced tile leakage, and increased durability by maintaining a robust mechanical design, enhancing the engine's thermal efficiency and reducing emissions.
Implementation Method 1
cooling air to impinge on the hot surface and then flows out
Implementation Method 2
cooling air flows through the dual-wall tile assembly, absorbing heat from the hot combustion chamber surface
Implementation Method 3
enhancing film cooling and mechanical attachment reliability
Implementation Method 4
allowing cooling air to impinge on the hot surface and then flows out
Data Source
Figure 1~2
Figure 3
Figure 4~6
AI summary
A gas turbine engine (10) includes a combustor (18) having a combustor tile assembly (42, 150) with improved cooling air flow channels (70, 78, 150) and enhanced cooling efficiency. A method of manufacturing same is provided which increases production capabilities and the geometric configurations of the exit ports (84) which in turn improve the hot side (64) operating temperature of the tiles in the combustion chamber (54).