Fuel Injector Assembly With High Shear Swirler
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Solution Overview
Problem
Existing fuel injector assemblies for turbine engines face challenges in improving fuel-air mixing and reducing combustor dynamics and undesirable combustor tones.
Innovation Solution
A fuel injector assembly with a high shear swirler configuration, featuring a multi-segment swirler with upstream, intermediate, and downstream segments, and a fuel injector nozzle that impinges fuel jets onto the swirler inner wall to form a thin fuel film, enhancing atomization through shear forces and optimized geometry for improved mixing and tone reduction.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If a conventional fuel injector assembly is used, then the structure is simple, but fuel-air mixing is insufficient and combustor tones are high
Solution Approach 1:
The swirler is divided into multiple segments (upstream, intermediate, downstream) that can be assembled together, allowing for complex flow control functionality while maintaining manufacturing feasibility through modular construction
Solution Approach 2:
Different segments of the swirler have different vane configurations and geometries optimized for specific local functions - upstream segments create initial swirl, intermediate segments enhance mixing, and downstream segments control final flow characteristics, allowing each region to perform its specialized function
2Productivity
If a high shear swirler with multi-segment configuration is implemented, then fuel-air mixing is improved, but device complexity increases
Solution Approach 1:
The swirler is divided into multiple segments (upstream, intermediate, downstream) that can be assembled together, allowing for complex flow control functionality while maintaining manufacturing feasibility through modular construction
Solution Approach 2:
The multi-segment swirler configuration serves multiple functions simultaneously - creating swirl flow, enhancing fuel-air mixing, controlling combustion dynamics, and reducing combustor tones - all within a single integrated component assembly
3Productivity
If fuel jets are impinged onto the swirler inner wall to form a thin fuel film, then atomization is enhanced, but manufacturing precision requirements increase
Solution Approach 1:
The swirler inner wall features locally optimized geometry including specific curvature radii, surface roughness characteristics, and angular configurations that naturally control fuel film formation and thickness distribution, reducing reliance on tight manufacturing tolerances
Solution Approach 2:
The design optimizes parameters such as swirl number, fuel injection pressure, and swirler geometry to achieve the desired thin fuel film formation through controlled physical processes rather than precise manufacturing alone
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 assembly achieves improved fuel-air mixing and reduced combustion dynamics, leading to enhanced combustion efficiency and minimized combustor tones by optimizing fuel film thickness and air swirl velocities.
Implementation Method 1
A fuel injector nozzle is cantilevered from the fuel injector stem and projects along the axis into the inner passage. A tip of the fuel injector nozzle is disposed within the inner passage upstream of the inner nozzle outlet. The fuel injector assembly is configured such that a ratio of the axial distance D to the outer passage exit diameter Dsw-ex is between 0.50 and 0.75. Further, the fuel injector assembly is configured such that a ratio of the axial distance (D-d) to the outer passage exit diameter Dsw-ex is between 0.25 and 0.80, wherein d is a distance from the distal outer wall end to the distal inner wall end of the swirler. High shear swirler atomization enables improved fuel/air mixing and reduced combustion dynamics
Implementation Method 2
A fuel injector assembly with a high shear swirler configuration, featuring a multi-segment swirler with upstream, intermediate, and downstream segments
Implementation Method 3
enhancing atomization through shear forces and optimized geometry for improved mixing and tone reduction
Data Source
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AI summary
An assembly is provided for a turbine engine. This assembly includes a swirler (64) and a fuel nozzle (154). The swirler (64) is configured with an outer wall (80), an inner wall (82), an outer passage (86) and an inner passage (84). The outer wall (80) circumscribes the inner wall (82) and extends axially along an axis (70) to a distal outer wall end (138). The inner wall (82) extends axially along the axis (70) to a distal inner wall end (118) that is axially recessed within the swirler (64) from the distal outer wall end (138). The outer passage (86) is formed by and radially between the inner wall (82) and the outer wall (80). The inner passage (84) is formed by and radially within the inner wall (82). The fuel nozzle (154) projects into the inner passage (84). The fuel nozzle (154) is configured with a plurality of orifices (158) axially aligned with the inner wall (82) and arranged circumferentially about the axis (70).