Turbomachine Combustors with Reverse Flow and Single Manifold
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Solution Overview
Problem
Turbomachines face challenges in maintaining a desirable overall pressure ratio while avoiding damage from high temperatures, which can be detrimental to components.
Innovation Solution
The design incorporates a turbomachine assembly with a reverse flow combustor configuration and a single fuel manifold system that controls fuel delivery to both first and second combustors, allowing for efficient combustion and power control by directing fuel flow differently to drive distinct spools, and utilizing swirl air conduits for atomization and cooling.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stress or pressure
If features are incorporated to increase and maintain the overall pressure ratio, then the pressure ratio is improved, but the size of the turbomachine increases
Solution Approach 1:
The combustor section is divided into multiple combustors (first combustor, second combustor, third combustor) with different flow directions. This segmentation allows the system to achieve higher overall pressure ratio through multiple compression stages while managing the physical size by distributing components across different spatial orientations rather than extending a single axial path.
Solution Approach 2:
The patent introduces radial flow combustors that operate in a radial dimension rather than purely axial flow. The second combustor receives compressed air radially outwardly and discharges radially inwardly, adding a radial dimension to the flow paths. This dimensional change enables compact arrangement of multiple combustors, achieving high pressure ratios without proportionally increasing axial length.
2Stress or pressure
If high temperatures are used to maintain pressure ratio, then the pressure ratio is improved, but component damage occurs
Solution Approach 1:
The combustion process is segmented across multiple combustors operating at different stages. The first combustor operates with lower temperature air, the second combustor operates with intermediate temperature air, and the third combustor operates with higher temperature air. This segmentation distributes the thermal load across multiple components rather than concentrating extreme temperatures in a single combustor, reducing the risk of component damage while maintaining overall pressure ratio.
Solution Approach 2:
Each combustor is designed with local quality characteristics suited to its specific operating conditions. The combustors have different flow directions (axial, radial, axial) and receive air at different temperatures and pressures. This local optimization allows each combustor to operate efficiently within its specific thermal and pressure environment, avoiding the need for any single combustor to withstand extreme conditions that would cause damage.
3Stress or pressure
If multiple combustors with different flow directions are used, then temperature and pressure control is improved, but device complexity increases
Solution Approach 1:
The fuel manifold is designed as a universal component that serves multiple combustors with different flow directions. The fuel manifold receives fuel and distributes it to the first combustor (axial flow), second combustor (radial flow), and third combustor (axial flow) through a single integrated structure. This multi-functional design simplifies the overall system by using one fuel distribution system for all combustors rather than requiring separate fuel delivery systems for each combustor type.
Solution Approach 2:
The patent merges multiple combustors into a single integrated combustor section that operates as a unified system. The first, second, and third combustors are combined with a common fuel manifold and coordinated operation to achieve temperature and pressure control. This merging reduces the complexity that would arise from completely separate combustor systems while maintaining the benefits of different flow directions for thermal management.
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 effectively manages temperature and pressure ratios, reduces axial length, and allows for controlled power delivery, enhancing the turbomachine's operational efficiency and component durability.
Implementation Method 1
each including a fuel injector configured to deliver fuel to the combustion chamber and a swirl air conduit configured to introduce swirl air to the fuel
Implementation Method 2
a swirl air conduit configured to introduce swirl air to the fuel
Data Source
Figure 1
Figure 2
Figure 3~4
AI summary
A turbomachine assembly includes a first combustor (30) configured to combust fuel and compressed air and a second combustor (32) configured to combust fuel and compressed air. Flow moves through the first combustor (30) in a first direction and flow moves though the second combustor (32) in a second direction different than the first direction. The first combustor (30) is axially spaced from the second combustor (32). A corresponding operating method is also provided.