Helicoidal Air Circulation in Gas Turbine Combustion Chamber
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Solution Overview
Problem
The existing turbomachine design requires intense aerodynamic forces to straighten and redirect air flow, leading to inefficiencies and increased production costs due to complex aerodynamic designs in the compression and turbine sections.
Innovation Solution
A combustion chamber with internal and external annular walls and fuel injection systems that maintain the natural air inclination, allowing air to enter with a rotational movement, reducing the need for intense aerodynamic forces and simplifying the design of the high-pressure turbine nozzle.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If air is straightened in the longitudinal axis using an air straightener, then the air flow is aligned for combustion, but intense aerodynamic forces are required which reduce overall efficiency
Solution Approach 1:
The combustion chamber is divided into multiple cavities (first cavity, second cavity, third cavity, fourth cavity) arranged circumferentially around the longitudinal axis. Each cavity receives air from a different direction, allowing the air flow to be distributed and stabilized without requiring intense aerodynamic forces from a single straightener component.
2Speed
If air is redirected with an inclination greater than 70° for the turbine section, then the necessary angle of attack is produced, but intense aerodynamic forces are required which reduce overall efficiency
Solution Approach 1:
The turbine section is divided into multiple distributor components (first distributor, second distributor, third distributor, fourth distributor) corresponding to each cavity. Each distributor redirects air flow from its respective cavity at the required inclination angle, distributing the aerodynamic work across multiple components rather than requiring a single high-force redirector.
3Adaptability or versatility
If successive angular modifications are made to air distribution, then the air flow is adapted for combustion and turbine operation, but complex aerodynamic designs are required which increase production costs
Solution Approach 1:
The combustion chamber and turbine section are segmented into four circumferential cavities with corresponding injection systems and distributors. This modular segmentation allows each component to be designed and manufactured independently, simplifying production while maintaining the ability to adapt air flow for both combustion and turbine operations.
Solution Approach 2:
Each cavity is equipped with localized fuel injection systems and distributors tailored to its specific function. The first and second cavities are optimized for combustion with appropriate fuel injection, while the third and fourth cavities are optimized for turbine air flow redirection. This local optimization reduces overall system complexity by assigning specific qualities to specific regions.
4Ease of operation
If intense aerodynamic forces are used to modify air distribution, then the air flow is controlled through the turbomachine, but the overall efficiency of the turbomachine is reduced
Solution Approach 1:
Air flow control is distributed across multiple cavities and distributors rather than being managed by a single high-force aerodynamic system. This segmentation reduces the intensity of forces required in each component while maintaining effective control over the entire air flow, thereby improving overall turbomachine efficiency.
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 reduces aerodynamic forces, enhances turbomachine efficiency, and simplifies the rectifier and distributor components, leading to mass savings and lower production costs while stabilizing the combustion flame across all operating speeds.
Implementation Method 1
The combustion chamber according to the invention can thus be supplied with air having a rotational movement around the longitudinal axis of the turbomachine. The natural inclination of the air leaving the compression section of the turbomachine can therefore be maintained through the combustion chamber.
Implementation Method 2
certain internal and external cavities are supplied with fuel in a substantially radial direction
Implementation Method 3
the air in the combustion chamber is then mixed with fuel so as to ensure satisfactory combustion and the gases resulting from this combustion follow a path generally along the longitudinal axis of the turbomachine
Data Source
Figure 1
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Figure 3~4
AI summary
The chamber (202) has an inner wall (212) and an outer wall (214) having inner steps (220) and outer steps (224) regularly distributed around a longitudinal axis. Each step extends longitudinally between two longitudinal ends of the walls and radially towards exterior or interior of the walls, respectively. A circumferential spacing between the two adjacent steps defines an inner cavity (222) and an outer cavity (226), respectively. The cavities are supplied with outer air to the chamber along a circumferential direction and with fuel along a radial direction.