Centripetal Annular Combustion Chamber Flow Guidance
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Solution Overview
Problem
Conventional gas turbine combustion chamber designs are complex, heavy, and costly, with inefficient flow guidance leading to increased engine consumption and pollutant emissions due to excessive flow deflection and complex guide vane systems.
Innovation Solution
A guide vane arrangement deflects air from the centrifugal compressor at a reduced angle, introducing it into the combustion chamber with a twist, forming a spiral flame and reducing overall flow deflection to 175°, which simplifies the design, enhances combustion efficiency, and reduces the number of guide vanes needed in the turbine vane ring.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a multi-stage radial-axial guide wheel system is used to decelerate and redirect flow, then the flow can be properly guided to the combustion chamber, but the device complexity and weight increase significantly
Solution Approach 1:
The patent extracts and eliminates the complex multi-stage radial-axial guide wheel system from the conventional design. Instead of using multiple guide vanes to achieve flow redirection, the invention uses a simplified approach where the combustion chamber itself is designed to receive and properly guide the radial flow directly, removing the need for intermediate guide wheel stages.
Solution Approach 2:
The combustion chamber is designed to perform multiple functions: it serves as both the combustion zone and the flow guidance structure. The chamber geometry itself directs the radial flow from the compressor into the combustion area, eliminating the need for separate dedicated guide vanes and reducing overall system complexity.
2Ease of operation
If a multi-stage radial-axial guide wheel system is used to decelerate flow to Mach 0.15, then the flow can be properly controlled, but the weight and complexity increase
Solution Approach 1:
The patent removes the heavy multi-stage guide wheel system that would normally be required to decelerate the flow to Mach 0.15. Instead, the combustion chamber geometry is designed to directly handle and control the radial flow, eliminating the need for separate deceleration stages and reducing overall weight.
Solution Approach 2:
The combustion chamber serves dual purposes: it is both the combustion zone and the flow control structure. The chamber's geometric design inherently provides flow deceleration and direction control, removing the need for separate heavy guide wheel components.
3Ease of operation
If flow is deflected through the combustion chamber by approximately 300°, then the flow can be redirected to the turbine, but additional flow losses and engine consumption increase
Solution Approach 1:
Instead of deflecting the flow through the full 300° required by conventional designs, the patent uses a partial deflection approach. The combustion chamber geometry is designed to handle the radial flow with a smaller, more efficient deflection angle, reducing the energy losses associated with excessive flow redirection while still achieving the necessary flow direction change for turbine entry.
4Ease of operation
If a complicated combustion chamber construction is used to handle radial flow, then the flow can be properly managed, but the manufacturing cost and complexity increase
Solution Approach 1:
The patent extracts the complex multi-component flow management system from the combustion chamber assembly. By eliminating the need for separate guide vanes, flow control stages, and complex internal structures, the design simplifies to a more straightforward combustion chamber geometry that is easier and more cost-effective to manufacture.
Solution Approach 2:
The combustion chamber is designed as a universal component that handles both combustion and flow management functions. This multi-functionality eliminates the need for separate dedicated flow control components, simplifying the overall construction and reducing manufacturing complexity and costs.
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 design results in a more compact, cost-effective, and efficient combustion chamber with reduced weight, lower pressure losses, and improved combustion and mixing ratios, while maintaining efficient acceleration of combustion gases to the speed of sound.
Implementation Method 1
a guide vane arrangement is provided between the centrifugal compressor and the annular combustion chamber, which is designed such that the air flowing out of the centrifugal compressor is deflected at an angle of between 20° and 30°, preferably 25°, to the engine axis
Implementation Method 2
The hot combustion gases are accelerated to the speed of sound by a film-cooled turbine vane ring
Data Source
Figure 1
Figure 2
Figure 3~4
AI summary
The invention relates to a gas turbine combustion chamber arrangement having at least one centrifugal compressor 1 and having a centripetal annular combustion chamber, wherein between the centrifugal compressor 1 and the annular combustion chamber there is arranged a guide blade arrangement 2, characterized in that the guide blade arrangement 2 is designed such that the air flowing out of the centrifugal compressor 1 is diverted at an angle α of 20° to 30°, preferably 25°, with respect to the power unit axis 9, in that the air flow is supplied to the combustion chamber at substantially said angle α, in that the inflow region into the combustion chamber is designed for supplying the air at an angle of 20° to 30°, preferably 25°, with respect to the meridian plane 12, and in that the central axes 10 of the burners 4 or of the injection nozzles of the combustion chamber are arranged so as to be inclined at an angle β of 30° to 40°, preferably 35°, with respect to a meridian plane 12 running through the power unit axis 9.