Compact Cyclone Combustion Torch Igniter for Rocket Engines
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Solution Overview
Problem
Spark igniters in bipropellant rocket engines are prone to spark-quenching at elevated operating pressures, which affects reliable ignition and stable combustion.
Innovation Solution
A method involving axially flowing a first stream of gaseous oxidizer through the torch throat and vortically flowing a second stream within the combustion chamber, combined with fuel injection to create a combustible mixture, which is then ignited and directed through the torch throat, utilizing a cyclone combustor design to achieve high combustion intensity and self-sustaining ignition.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If spark igniters are used in bipropellant rocket engines, then multiple sparks can be delivered in rapid discharge rates, but spark-quenching occurs at elevated operating pressures
Solution Approach 1:
The patent changes the ignition mechanism from electrical spark to chemical combustion. The cyclone combustor uses a pyrotechnic composition that burns at controlled rates to produce a sustained high-temperature flame, eliminating dependence on electrical spark performance at high pressures. This parameter change from electrical to chemical ignition source resolves the spark-quenching problem while maintaining high ignition reliability.
Solution Approach 2:
The patent replaces the electrical spark ignition system with a chemical combustion-based cyclone igniter. The mechanical/electrical spark generation system is substituted with a chemically-driven combustion wave that propagates through the cyclone combustor, providing reliable ignition without the limitations of electrical discharges at elevated pressures.
2Reliability
If high combustion intensity is achieved through cyclone combustor design, then reliable ignition is provided, but additional cooling fluids are typically required
Solution Approach 1:
The cyclone combustor design uses the combustion process itself to cool critical components. The high-velocity combustion gases flow through the cyclone structure, creating a cooling effect on the combustor walls and internal components through adiabatic expansion and heat transfer. This self-cooling mechanism eliminates or reduces the need for separate cooling fluid systems, simplifying the overall device while maintaining reliable high-intensity combustion.
Solution Approach 2:
The patent utilizes phase transitions of the propellants and combustion products to manage thermal loads. The rapid expansion and cooling of combustion gases as they exit the cyclone combustor throat creates a cooling effect that protects downstream components. Additionally, the phase change from liquid/gas propellants to combustion products and back provides inherent thermal management without requiring external cooling fluids.
3Volume of moving object
If compact size is achieved for the igniter system, then integration is improved, but combustion stability may be compromised
Solution Approach 1:
The cyclone combustor is designed as a compact, integrated unit that combines the fuel/oxidizer mixing chamber, combustion zone, and exhaust throat into a single compact structure. The cyclone geometry itself creates segmented flow patterns with a central low-pressure core and outer high-velocity shear layer, enabling stable combustion within a small volume. This segmentation of flow paths maintains combustion stability while achieving compact dimensions suitable for rocket engine integration.
Solution Approach 2:
The patent utilizes three-dimensional cyclonic flow patterns to achieve stable combustion in a compact volume. By introducing rotation and creating a three-dimensional vortex structure, the combustor increases the effective combustion path length and surface area for heat transfer without increasing the overall linear dimensions. This dimensional approach allows stable high-intensity combustion within a compact geometry that can be easily integrated into rocket engines.
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
This approach ensures consistent operation across varying mixture ratios, provides reliable ignition, and maintains stable combustion with high effluent combustion product temperatures exceeding 3000°F, eliminating the need for additional cooling fluids and enhancing robustness.
Implementation Method 1
Vortically flowing a second stream of the gaseous oxidizer within the combustion chamber
Implementation Method 2
Vortically flowing a second stream of the gaseous oxidizer within the combustion chamber. Communicating a fuel into the combustion chamber to yield a mixture with the second stream
Implementation Method 3
Igniting the mixture to yield a combusting mixture and communicating the combusting mixture through the torch throat
Implementation Method 4
Axially flowing a first stream of gaseous oxidizer through the torch throat
Data Source
AI summary
A torch igniter and method of cooling the torch igniter includes axially flowing a first stream of gaseous oxidizer through a torch throat and vortically flowing a second stream of the gaseous oxidizer within a combustion chamber.