Reverse-Flow Annular Vortex Combustor for Fuel-Air Mixing
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Solution Overview
Problem
Existing turbine engines face challenges in efficiently mixing and combusting fuel and air due to limitations in vortex formation and residence time within the combustor, leading to inefficiencies and increased emissions.
Innovation Solution
The implementation of a reverse flow annular vortex combustor with contoured inner liners and strategically positioned driver openings that create multiple counter-rotating vortices, enhancing mixing and residence time, and utilizing tangentially oriented driver openings to induce bulk swirl for improved fuel-air combustion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If conventional combustor design is used, then structural simplicity is maintained, but mixing efficiency and residence time are insufficient
Solution Approach 1:
The combustor is segmented into multiple functional zones including a contoured inner liner region and an outer liner region, with driver openings strategically positioned to create distinct vortex formation zones. This segmentation allows each region to perform specific functions (mixing, combustion, flow control) thereby improving overall mixing efficiency while maintaining reasonable structural complexity
Solution Approach 2:
The inner liner is contoured with curved surfaces rather than straight cylindrical geometry. This curvature creates favorable flow patterns and vortex formation characteristics that enhance mixing efficiency. The contoured shape guides the flow more effectively compared to conventional straight-walled combustors
2Duration of action of moving object
If driver openings are added to create vortices, then residence time increases, but manufacturing complexity increases
Solution Approach 1:
Driver openings are positioned at specific locations on the inner liner rather than uniformly distributed. The openings are concentrated in regions where they most effectively influence vortex formation and residence time. This localized approach achieves the desired flow control with minimal additional manufacturing complexity
Solution Approach 2:
The driver openings have specific geometric parameters (size, shape, orientation) that are optimized to create the desired vortex strength and residence time. By carefully controlling these parameters, the design achieves extended residence time while keeping the manufacturing process relatively simple through standard fabrication techniques
3Ease of operation
If contoured inner liner is implemented, then flow transition smoothness improves, but manufacturing precision requirements increase
Solution Approach 1:
The inner liner employs contoured curved surfaces that provide smooth flow transitions. The curvature is designed to guide the flow gradually rather than abruptly, reducing turbulence and improving flow uniformity at the combustor exit
Solution Approach 2:
The contour geometry is defined by specific mathematical parameters that can be precisely controlled during manufacturing. By optimizing these geometric parameters, the design achieves smooth flow transitions while setting realistic manufacturing tolerance requirements that can be met with modern fabrication capabilities
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 design increases mixing and residence time, reduces emissions, and provides a smoother flow transition into the turbine, resulting in improved efficiency and performance.
Implementation Method 1
one or more driver openings providing a driver air flow formed of the compressed air flow, wherein the driver air flow enters the combustion chamber as a wall of air for shaping and driving a primary zone vortex
Implementation Method 2
the contoured inner liner provides a larger inner turning radius
Implementation Method 3
plurality of liner cooling holes providing liner cooling
Data Source
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AI summary
A gas turbine engine (10) including a compressor section (22) for compressing air (64, 68) flowing therethrough to provide a compressed air flow (240) and a reverse flow annular vortex combustor (200, 300, 400, 500) including a combustion chamber (224, 324, 424, 524) having a primary combustion zone (252, 352, 452, 552), the combustion chamber (224, 324, 424, 524) configured to combust a mixture of a fuel flow (250) and the compressed air flow (240) in the primary combustion zone (252, 352, 452, 552) to generate a primary zone vortex (254, 354, 454, 554). The reverse flow annular vortex combustor (200, 300, 400, 500) has a combustor liner (214, 314, 414, 514) and one or more driver openings (234, 324, 434, 534) extending through the combustor liner (214, 314, 414, 514), the one or more driver openings (234, 324, 434, 534) providing a driver air flow (240) formed of the compressed air flow (240). The driver air flow (240) enters the combustion chamber (224, 324, 424, 524) as a wall of air (64, 68) for shaping and driving the primary zone vortex (254, 354, 454, 554) in the combustion chamber (224, 324, 424, 524).