Vortex Hybrid Rocket Motor Combustion Efficiency
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Solution Overview
Problem
Classical hybrid rocket engines suffer from slow solid fuel regression rates, low volumetric loading, and poor combustion efficiency, which can be addressed by employing complex fuel grain geometries but result in increased engine size and manufacturing difficulties.
Innovation Solution
A vortex hybrid motor design featuring a housing with tangential and central oxidizer injection ports, a fuel core with radial fuel gradients and additives, and a support structure to enhance combustion efficiency and thrust profiles, including a submerged nozzle for compactness.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If complex cross-sectional geometries of fuel grain with large wetted surface areas are employed to increase mass flow rate, then fuel regression rate is improved, but manufacturing difficulty increases and engine size increases
Solution Approach 1:
The oxidizer injection system is segmented into multiple injection ports positioned at different locations and orientations around the fuel grain. This includes axial injection ports for central oxidizer delivery and radial injection ports for tangential oxidizer delivery, allowing independent optimization of different combustion zones without complicating the fuel grain geometry itself
Solution Approach 2:
A vortex flow structure is introduced as an intermediary mechanism between the oxidizer injection and fuel regression processes. The tangential injection ports create a vortex flow that enhances mixing and heat transfer to the fuel grain surface, achieving high regression rates without requiring complex fuel grain geometries
2Productivity
If complex cross-sectional geometries of fuel grain with large wetted surface areas are employed to increase mass flow rate, then fuel regression rate is improved, but engine size increases
Solution Approach 1:
The combustion chamber is segmented into distinct zones with different injection characteristics - a central axial injection zone and an outer radial injection zone. This allows efficient utilization of fuel grain surface area without requiring an oversized chamber, achieving high mass flow rate in a compact volume
Solution Approach 2:
The injection parameters are optimized by controlling the oxidizer injection pressure, flow rate, and angular distribution through the multiple injection ports. This enables high regression rates and efficient combustion in a compact engine configuration without requiring large wetted surface areas
3Ease of operation
If classical hybrid rocket engine design is used, then simplicity of operation is maintained, but combustion efficiency deteriorates
Solution Approach 1:
Multiple oxidizer injection methods (axial and radial injection) are merged into a single hybrid engine design. The axial injection ports provide stable central combustion while the radial injection ports create vortex flow for enhanced mixing, achieving high combustion efficiency while maintaining the operational simplicity of a single-phase liquid propellant system
Solution Approach 2:
The oxidizer is injected as a liquid through controlled hydraulic injection ports, using fluid dynamics principles to create vortex flow patterns. This hydraulic approach enables efficient atomization and mixing with the fuel grain, achieving high combustion efficiency while maintaining simple liquid-propellant operation
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 rapid ignition, vigorous combustion, and high thrust with adjustable oxidizer-to-fuel ratios, optimizing specific impulse and fuel regression rates while maintaining a compact design.
Implementation Method 1
a first injection port positioned proximate to the sidewall and configured to deliver a first amount of the oxidizer into the housing in a direction that is approximately tangent to the sidewall
Implementation Method 2
a fuel core positioned within the housing and configured to react with an oxidizer to thereby create a thrust sufficient to propel at least the vortex hybrid motor
Implementation Method 3
a second injection port positioned proximate to the proximal end of the housing and configured to deliver a second amount of the oxidizer into a center of the housing
Data Source
AI summary
Various embodiments of a vortex hybrid motor are described herein. In some embodiments, the vortex hybrid motor may include a combustion zone defined by a fuel core and/or motor housing. The combustion zone may include an upper zone and a central zone that each contribute to thrust created by the vortex hybrid motor. In some embodiments, an injection port configuration is described that includes a proximal injection port that may be controlled for modulating a delivery of an amount of oxidizer for adjusting an oxidizer-to-fuel ratio. In some embodiments, a fuel core configuration is described that provides radially varying gradients of fuel in order to achieve desired thrust profiles. In some embodiments, the fuel core may include a support structure and/or a proximal end of a nozzle of the vortex hybrid motor may extend into the fuel core.