Solid Rocket Motor Vortex Inducing Feature Combustion Efficiency
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Solution Overview
Problem
In solid rocket motors, the combustion particles tend to concentrate along the center of the bore, leading to inefficient oxygen consumption and reduced combustion efficiency due to uneven distribution of reactants.
Innovation Solution
Incorporating a vortex inducing feature, such as off-radial slots, protuberances, or helical slots, within the propellant grain structure to generate a vortex flow that redistributes particles to oxygen-rich regions, enhancing contact with oxygen and improving combustion efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If combustion particles flow along the center of the bore, then the flow path is short and particle collisions are frequent, but oxygen consumption becomes inefficient and combustion efficiency decreases
Solution Approach 1:
The patent introduces a vortex inducing feature with a curved or helical geometry that redirects the linear particle flow into a rotational vortex pattern. This curvature increases the flow path length and distributes particles radially outward toward oxygen-rich regions, improving combustion efficiency without requiring additional components
Solution Approach 2:
The vortex inducing feature creates an asymmetric flow pattern within the symmetric bore structure. By introducing asymmetry in the flow trajectory through the vortex geometry, particles are redistributed from the concentrated center region to the peripheral oxygen-rich zones, resolving the uneven combustion problem
2Productivity
If a vortex inducing feature is added to redistribute particles, then combustion efficiency improves, but the device complexity increases
Solution Approach 1:
The vortex inducing feature is integrated directly into the propellant grain structure itself, merging the combustion chamber function with the flow control function. This eliminates the need for separate flow control components and reduces overall device complexity while achieving particle redistribution
Solution Approach 2:
The vortex inducing feature is positioned at a specific location within the bore (such as near the ignition end or at a critical section) to create the vortex flow only where needed. This localized approach achieves particle redistribution without modifying the entire bore structure, minimizing added complexity
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 vortex flow reduces particle collisions at the center, increases the flow path length, and enhances combustion efficiency by directing particles to oxygen-rich outer regions, thereby improving thrust generation.
Implementation Method 1
A vortex flow of the combustion materials is generated in the axial bore using at least one vortex inducing feature
Data Source
AI summary
A solid rocket motor includes a propellant grain structure defining an axial bore and a vortex inducing feature.