Arcuate-to-Annular Diffuser for Rotating Detonation Engines
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Solution Overview
Problem
Traditional diffusers for rotating detonation engines limit design space and are inefficient in transitioning supersonic airflow to subsonic conditions.
Innovation Solution
A diffuser design with radially inner and outer walls that increase in arc angle and decrease in distance as it extends axially, transitioning from an arcuate inlet to an annular outlet, increasing the cross-sectional area, which includes a transition portion between the inlet and the outlet, providing additional design space for fuel, payload, or payload, and enhancing the range and payload capacity, and the diffuser is configured to receive air flow from the inlet and transition supersonic airflow to subsonic airflow.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a typical radial duct diffuser is used, then the structure is simple, but the design space is limited and airflow transition efficiency is poor
Solution Approach 1:
The diffuser transitions from a simple two-dimensional radial duct to a three-dimensional structure with arcuate walls that wrap around the engine. The radially inner and outer walls extend in the arcwise direction with increasing arc angles, creating additional spatial dimensions for design flexibility while maintaining structural efficiency for airflow transition.
Solution Approach 2:
The diffuser is divided into multiple functional sections: an inlet portion, a transition portion with increasing arc angles, and an outlet portion. The radially inner and outer walls are segmented into discrete panels that can be independently configured, allowing optimization of each section for its specific airflow requirements while contributing to overall design space expansion.
2Volume of moving object
If the diffuser arc angle increases axially, then design space and fuel capacity increase, but the structural complexity increases
Solution Approach 1:
The diffuser employs arcuate radially inner and outer walls that curve in the arcwise direction, replacing straight linear geometry with curved surfaces. This curvature naturally increases the enclosed volume and design space while the smooth continuous arcs maintain structural simplicity compared to complex angular transitions.
Solution Approach 2:
The arc angle is defined as a varying parameter that increases axially from the inlet to the outlet portion. By treating the arc angle as a continuous function rather than a fixed value, the design achieves increased volume and fuel capacity while the systematic parameter variation maintains manufacturing feasibility and structural regularity.
3Productivity
If the diffuser distance between radially inner and outer walls decreases axially, then supersonic to subsonic transition efficiency improves, but the cross-sectional area for airflow reduces
Solution Approach 1:
The diffuser resolves the area reduction problem by expanding in the arcwise dimension. While the radial distance between walls decreases to improve compression and airflow transition, the arc length of the radially inner and outer walls increases, maintaining or increasing the overall cross-sectional area through growth in the third dimension (arcwise direction).
Solution Approach 2:
Different sections of the diffuser have locally optimized geometries: the radial wall distance decreases in the compression section to improve supersonic-to-subsonic transition efficiency, while the arc length increases simultaneously to maintain adequate cross-sectional area for mass flow. Each local region is optimized for its specific function while contributing to overall performance.
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 diffuser effectively transitions supersonic airflow to subsonic conditions while providing additional design space within the airframe, allowing for increased fuel capacity and payload.
Implementation Method 1
a diffuser to feed the rotating detonation engine. The diffuser may be configured to reduce a flow from a supersonic inlet to subsonic conditions
Implementation Method 2
the cross-sectional area increases as the diffuser extends axially
Data Source
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AI summary
A diffuser (300) may comprise an inlet (310) and an outlet (340). The inlet may comprise an arcuate shape. The outlet may comprise an annular shape. The diffuser may transition from the arcuate shape at the inlet to the annular shape at the outlet. The diffuser may comprise a radially inner wall (320) and a radially outer wall (330) disposed opposite the radially inner wall. The radially inner wall and the radially outer wall may partially define a duct.