Rotating Diode Combustion Chamber for Detonation Wave Control
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Solution Overview
Problem
Existing continuous detonation combustion systems face inefficiencies due to backflow issues and limited control over fuel introduction, leading to suboptimal performance and pressure gain in gas turbine engines.
Innovation Solution
A combustion system with a walled annular combustion chamber and fluid diodes that create rotating regions to match the speed of continuous detonation waves, allowing for precise control of fluid flow and reducing backflow by positioning regions of higher and lower pressure zones, and varying fuel introduction lag to prevent deflagrative combustion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If continuous detonation combustion is employed, then power and efficiency are improved, but backflow control becomes difficult
Solution Approach 1:
The patent employs rotating diode structures that dynamically adjust flow areas to match the rotating detonation wave. The first and second rotating regions rotate at the same speed as the detonation wave, with flow areas that vary circumferentially to control backflow dynamically throughout the combustion chamber.
Solution Approach 2:
The combustion chamber is divided into distinct pressure zones (higher pressure zone and lower pressure zone) with separate fluid diodes controlling each zone. This segmentation allows independent control of oxidant and fuel introduction, improving backflow control while maintaining detonation stability.
2Reliability
If fluid diodes are used to control flow, then backflow is reduced, but device complexity increases
Solution Approach 1:
Multiple rotating diode structures are combined into integrated fluid diode assemblies that control both oxidant and fuel flow. The first fluid diode combines the first rotating diode structure and second rotating diode structure, while the second fluid diode combines the third rotating diode structure and fourth rotating diode structure, reducing overall system complexity.
Solution Approach 2:
The rotating diode structures serve multiple functions: they control backflow, regulate fluid introduction timing, create rotating flow patterns, and synchronize with the detonation wave speed. This multi-functionality reduces the need for separate control mechanisms.
3Stability of the object's composition
If fuel introduction is delayed to prevent deflagration, then combustion stability is improved, but manufacturing precision requirements increase
Solution Approach 1:
The rotating diode structures are synchronized to rotate at the same speed as the rotating detonation wave, creating a feedback mechanism that automatically adjusts fuel and oxidant introduction timing. This self-synchronizing feedback reduces the need for high-precision manufacturing while maintaining combustion stability.
4Stress or pressure
If rotating regions are created to match detonation wave speed, then pressure gain is enhanced, but energy consumption increases
Solution Approach 1:
The rotating diode structures are driven by the flow dynamics of the combustion gases themselves, utilizing the expanding hot gases to maintain rotation. This self-service mechanism reduces external energy input requirements while maintaining the pressure gain benefits.
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 system enhances pressure gain and efficiency by minimizing backflow and deflagrative combustion, enabling higher pressure zones and improved fuel-air mixing, thus improving the performance of gas turbine engines.
Implementation Method 1
The combustion chamber is configured to contain therein a rotating continuous detonation wave
Implementation Method 2
The first fluid diode is configured to supply a fluid into the combustion chamber and is positioned flow-wise upstream of the combustion chamber
Implementation Method 3
The first rotating region is positioned adjacent to the rotating continuous detonation wave at a higher pressure zone of the rotating continuous detonation wave
Data Source
Figure 1~4
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Figure 7~7B
AI summary
A gas turbine engine comprising a combustion system configured for continuous detonation combustion process, the process employing a rotating continuous detonation wave (70).