Angled Injector Ring Atomizes Propellant for Hybrid Rocket
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Solution Overview
Problem
Classical hybrid rocket engines face slow solid fuel regression rates, low volumetric loading, inefficient ignition, and poor combustion efficiency due to slow polymeric fuel regression and challenges in igniting liquid propellants, which complicates manufacturing and increases engine size.
Innovation Solution
A vortex hybrid motor design featuring an injector ring with angled injector units that collide liquid propellant streams to atomize and create a swirl flow, enhancing ignition and combustion efficiency by reacting with a solid propellant within the combustion chamber.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If complex cross-sectional geometries with large wetted surface area are used to increase mass flow rate, then fuel regression rate is improved, but manufacturing difficulty increases and engine size increases
Solution Approach 1:
The injector is segmented into multiple angled injector units distributed circumferentially around the combustion chamber, each unit independently directing propellant streams to create localized atomization zones that collectively enhance fuel regression without requiring complex overall grain geometry
Solution Approach 2:
The injector units are positioned at specific injection angles (e.g., 30-60 degrees) relative to the chamber axis, and propellant streams are directed to collide at predetermined impingement points, optimizing atomization efficiency and fuel regression rate while maintaining simple cylindrical grain geometry
2Adaptability or versatility
If liquid propellants are used in hybrid rocket motors, then thrust tailoring and throttling capability are improved, but ignition efficiency deteriorates
Solution Approach 1:
The angled injector units pre-atomize the liquid propellant streams before they enter the main combustion zone by colliding them at impingement points, creating fine droplets that ignite more reliably and efficiently while maintaining the thrust control benefits of liquid propellants
Solution Approach 2:
The atomization process acts as an intermediary mechanism between liquid propellant injection and combustion, transforming the liquid into a fine spray of droplets that are more easily ignited and burned, thereby bridging the gap between liquid propellant flexibility and ignition reliability
3Reliability
If gaseous propellants or pre-gasified liquid propellants are used to improve ignition efficiency, then combustion efficiency is improved, but system weight and complexity increase
Solution Approach 1:
The system uses the kinetic energy of the injected liquid propellant streams themselves to create atomization through collision at impingement points, eliminating the need for external gasification equipment, catalyst beds, or pre-burning chambers that would add weight and complexity
Solution Approach 2:
The patent replaces mechanical gasification systems (such as catalyst beds or pre-burners) with a purely mechanical atomization mechanism where liquid streams collide and break up into droplets, achieving efficient ignition and combustion without the additional hardware weight
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 hybrid motor achieves increased solid fuel regression rates and improved combustion efficiency by atomizing liquid propellants, eliminating the need for pre-burning or catalyst decomposition, and reducing engine size and complexity.
Implementation Method 1
a first fluid stream of a liquid propellant dispensed from the first injector collides with a second fluid stream of the liquid propellant dispensed from the second injector to atomize the liquid propellant and form a spray fan formation
Implementation Method 2
at least one of the first injector and the second injector can be positioned at an injection angle relative to the sidewall such that at least one of the first fluid stream and the second fluid stream, respectively, is dispensed at the injection angle to create a swirl flow of the atomized injector fluid
Implementation Method 3
a solid propellant positioned within the combustion chamber housing and configured to react with the atomized liquid propellant to thereby create a thrust sufficient to propel at least the vortex hybrid motor
Data Source
AI summary
Various embodiments of a vortex hybrid motor are described herein. In some embodiments, the vortex hybrid motor may include a housing with a solid propellant positioned within the housing, and an injector ring positioned at a proximal end of the housing. The injector ring can include a plurality of angled injector units each including a first injector and a second injector angled towards an impingement point. A first fluid stream of a liquid propellant dispensed from the first injector can collide with a second fluid stream of the liquid propellant dispensed from the second injector to atomize the liquid propellant and form a spray fan formation. At least one of the first injector and the second injector can be positioned at an injection angle relative to the sidewall to create a swirl flow of the atomized injector fluid.