Quench Aperture Configuration for Gas Turbine Combustor Hotspot Reduction
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Gas turbine engine combustors experience reduced efficiency due to significant thermal hotspots in the exhausted combusted mixture, which are not adequately addressed by existing quench aperture configurations.
Innovation Solution
The combustor design features a forward bulkhead with circumferentially disposed injector apertures and radial combustor walls with quench aperture sets, where the inner radial wall includes first and second inner quench apertures separated by an intraset distance, and adjacent sets are separated by an interset distance greater than the intraset distance, creating specific flow patterns to influence and mix the axial air and fuel flow.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If conventional quench aperture configurations are used, then the combustor structure is simple, but thermal hotspots remain significant in the exhausted combusted mixture
Solution Approach 1:
The quench apertures are segmented into multiple sets (first quench aperture set, second quench aperture set, etc.) with different spacing patterns. Each set provides a specific flow pattern contribution, and the combination of these segmented sets creates a comprehensive quenching effect that eliminates thermal hotspots while maintaining structural organization.
Solution Approach 2:
Different regions of the combustor wall are assigned different quench aperture configurations. The intraset distance and interset distance are varied locally to create specific flow patterns in different axial regions, optimizing the quenching effect at each location while addressing the overall thermal hotspot problem.
2Manufacturing precision
If quench apertures are spaced uniformly, then the manufacturing is simple, but the axial air flow and thermal profile are not sufficiently uniform
Solution Approach 1:
The quench apertures are arranged with asymmetric spacing patterns where the intraset distance differs from the interset distance. This asymmetric configuration creates varied flow patterns that promote uniform mixing and thermal profiles, overcoming the limitations of uniform spacing while remaining manufacturable through standardized drilling patterns.
Solution Approach 2:
The spacing parameters (intraset distance and interset distance) are optimized to achieve the desired flow patterns. By carefully selecting these dimensional parameters, the design achieves uniform axial air flow and thermal profiles while maintaining manufacturability through precise but achievable dimensional tolerances.
3Productivity
If the intraset distance is large, then the quench air flow is sufficient, but the mixing efficiency decreases
Solution Approach 1:
The quench aperture configuration creates dynamic flow patterns where the relative positioning of aperture sets generates vortex flows and enhances turbulence. This dynamic interaction between air streams improves mixing efficiency while maintaining adequate quench air flow through the optimized spacing geometry.
Solution Approach 2:
The problem is solved by introducing a second spacing dimension (interset distance) in addition to the intraset distance. This two-dimensional spacing configuration allows optimization of both quench air flow and mixing efficiency by creating three-dimensional flow patterns that enhance turbulence and mixing while maintaining sufficient air supply.
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 promotes a more uniform axial air flow and thermal profile around the combustor circumference, enhancing engine efficiency by ensuring better mixing and distribution of the fuel-air mixture, thereby reducing thermal hotspots.
Implementation Method 1
The quench air performs two functions: it provides oxygen for completion of combustion, and it is used to affect the shape of the thermal profile
Implementation Method 2
thermal hotspot is a region in a thermal profile where the temperature is significantly elevated as compared to the surrounding area of the profile
Data Source
Figure 1
Figure 2~3
Figure 4~5
AI summary
A combustor (20) for a gas turbine engine includes a forward bulkhead (22), an inner radial combustor wall (26) and an outer radial combustor wall (28). The forward bulkhead has a plurality of circumferentially disposed injector apertures (34). The inner radial combustor wall is attached to and extends axially out from the forward bulkhead. The outer radial combustor wall is attached to and extends axially out from the forward bulkhead. At least one of the inner radial combustor wall and the outer radial combustor wall includes a plurality of quench aperture sets. Each quench aperture set includes a plurality of quench apertures. Adjacent quench apertures included within each quench aperture set are separated by an intraset distance. Adjacent quench aperture sets are separated by an interset distance. The intraset distance is different than the interset distance. The outer radial combustor wall is disposed radially outside the inner radial combustor wall, thereby defining an annular combustion region therebetween.