Hollow Rotating Detonation Combustor for Wave Stability
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Solution Overview
Problem
Current rotating detonation engines (RDEs) suffer from instabilities, heat losses, and require high-reactivity reactant mixtures, leading to inefficient operation and potential catastrophic failures, with annular designs being large and prone to uncontrolled longitudinal pulsed detonations.
Innovation Solution
The design incorporates a combustor with a converging nozzle to generate longitudinal pulsed detonations, a diverting plate to improve mixture quality, and a hollow structure to reduce heat losses and enhance detonation wave stability, allowing for self-sustained rotating detonation waves and efficient thrust generation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional RDC designs are used, then thrust generation is achieved, but detonation wave instabilities occur leading to catastrophic failures
Solution Approach 1:
The patent removes the inner cylindrical body from the combustor design, creating a hollow combustor structure. This extraction eliminates the inner surface that generates expansion waves and boundary layer effects, thereby removing the source of detonation wave instabilities while maintaining thrust generation capability
Solution Approach 2:
Instead of using a conventional annular combustor with an inner body, the patent inverts the design by using a hollow combustor where the combustion chamber is defined solely by the outer shell. This inversion changes the flow dynamics and eliminates the harmful interactions with the inner wall surface
2Loss of energy
If annular RDC designs are used, then combustion chamber is formed, but heat losses increase due to boundary layer effects
Solution Approach 1:
The inner cylindrical body is removed from the combustor structure, eliminating the inner wall surface that causes boundary layer effects and heat losses. This simplifies the combustor structure to just the outer shell while reducing energy losses
3Stability of the object's composition
If conventional RDCs are used, then detonation occurs, but uncontrolled longitudinal pulsed detonations are generated
Solution Approach 1:
By removing the inner cylindrical body, the patent eliminates the geometric constraints that cause longitudinal pulsed detonations. The hollow structure allows for more stable rotating detonation waves without the harmful longitudinal pulsations
Solution Approach 2:
The patent changes the geometric parameters of the combustor by transitioning from an annular design with inner body to a hollow design. This parameter change fundamentally alters the detonation wave propagation characteristics, stabilizing the rotating detonations
4Loss of substance
If conventional RDC designs are used, then thrust is produced, but reactant wastage is high
Solution Approach 1:
The patent converts the harmful boundary layer effects and heat losses into a benefit by removing the inner surface that causes them. The hollow structure eliminates these losses, improving reactant utilization efficiency while maintaining or enhancing thrust production
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 solution stabilizes detonation waves, reduces heat losses, and enables efficient thrust production with lower reactant wastage, improving the overall performance and reliability of RDEs.
Implementation Method 1
Detonation is a supersonic combustion mode that produces a pressure gain across the front due to the shock wave linked to the combustion front behind it
Implementation Method 2
combustion front behind it. This type of combustion can be activated in suitable mixtures in solid, liquid, or gas phase
Data Source
AI summary
A rotating detonation combustor includes a nozzle coupled to the combustor body at or near the exhaust opening to choke the exhaust opening. A rotating detonation combustor may include a diverting plate positioned radially inward of the inlet annulus and inlet channels for diverting flow of a mixture in an axial direction. A rotating detonation combustor may include a combustor body including an outer shell at least partially defining a detonation combustion chamber and extending axially from a base toward an exhaust opening of the detonation combustion chamber. The base defines a passageway in fluid communication with the detonation combustion chamber and includes an inlet annulus for axially directing a second fluid into the passageway and a plurality of inlet channels for radially directing a third fluid into at least one of the passageway or the detonation combustion chamber, and the detonation combustion chamber is free of any inner body.