Oblique Rotating Detonation Engine Wave Stabilization at Mach 5-6
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Solution Overview
Problem
Existing technologies have not adequately addressed the need for a system and method for producing and maintaining a SORDE, which is capable of achieving a supersonic oblique rotating detonation wave for supersonic to hypersonic propulsion.
Innovation Solution
A novel structure and method for a supersonic oblique rotating detonation engine (SORDE) that includes a detonation chamber with an oxidizer inlet and fuel injector, configured to deliver fuel and oxidizer at specific equivalence ratios and speeds to create and maintain a supersonic oblique rotating detonation wave, utilizing an annular wedge and cylindrical center body to stabilize the detonation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If conventional detonation systems are used, then simple structure is maintained, but supersonic to hypersonic propulsion capability is not achieved
Solution Approach 1:
The patent changes critical parameters including oxidizer injection speed (0.2-1.0 times wave speed), equivalence ratio (0.1-3.0), and detonation chamber geometry to achieve supersonic oblique rotating detonation waves. These parameter modifications enable the system to reach Mach 5-6 propulsion speeds while maintaining structural feasibility through calculated design choices.
Solution Approach 2:
The patent introduces an intermediary oxidizer injection system that acts as a mediator between the fuel source and the detonation wave. By controlling oxidizer delivery at specific speeds and ratios, the system enables stable supersonic oblique rotating detonation without requiring overly complex direct fuel injection mechanisms.
2Speed
If oxidizer is delivered at high speed to maintain supersonic flow, then propulsion speed is improved, but detonation stability deteriorates
Solution Approach 1:
The patent identifies an optimal parameter range where oxidizer delivery speed is set to 0.2-1.0 times the wave speed, with equivalence ratio controlled at 0.1-3.0. Within this parameter window, the system achieves both supersonic propulsion capability and stable detonation wave propagation, resolving the contradiction between speed and stability.
Solution Approach 2:
The patent employs dynamic control of oxidizer injection speed relative to the detonation wave speed. The oxidizer is delivered at a controlled fraction (0.2-1.0 times) of the wave speed, creating a dynamic balance that maintains detonation stability while enabling supersonic flow conditions for propulsion.
3Use of energy by moving object
If equivalence ratio is optimized for complete combustion, then energy efficiency is improved, but detonation wave formation is hindered
Solution Approach 1:
The patent specifies an equivalence ratio range of 0.1-3.0 (oxidizer to fuel mass ratio), which is broader than conventional stoichiometric combustion. This extended range allows the system to maintain reliable detonation wave formation while achieving adequate energy efficiency, as the oblique rotating detonation mechanism sustains combustion within this expanded parameter window.
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 SORDE achieves a supersonic oblique rotating detonation wave with speeds between Mach 5 and Mach 6, enhancing thermodynamic cycle efficiencies and enabling supersonic to hypersonic propulsion.
Implementation Method 1
The fuel injector and oxidizer inlet are configured to deliver the fuel and the oxidizer to the detonation chamber in an equivalence ratio of about 0.1 to about 3.0 or about 0.2 to about 2.5 to create a detonation wave
Implementation Method 2
the oxidizer inlet is configured to direct the oxidizer to the detonation chamber at a speed that is less than, but greater than or equal to 0.2 times a wave speed of the created detonation wave
Implementation Method 3
Detonation, a shock coupled reaction, is a key enabling technology for maintaining technological superiority of Department of Defense (DoD) high-speed propulsion and power systems
Implementation Method 4
This disclosure, however, is directed to the first ever supersonic oblique rotating detonation for supersonic to hypersonic propulsion
Data Source
AI summary
The present disclosure is directed to a supersonic oblique rotating detonation wave engine (SORDE) and systems and methods for generating a supersonic oblique rotating detonation wave. The SORDE is configured to produce and sustain a supersonic oblique rotating detonation wave through the injection of fuel at supersonic speeds into an inlet air flow between Mach 1 and Mach 7. The SORDE and method include injecting fuel into the inlet air in an amount to generate an equivalence ratio of 0.2 to 2.5. Some embodiments include a plurality of fuel injector ports each having a diameter of about 0.010 inches to about 0.040 inches; an annular wedge disposed in or upstream of the detonation chamber with an angle of about 5 degrees to about 40 degrees relative to a longitudinal axis of the engine; and/or a cylindrical center body disposed in or upstream of the detonation chamber.