Rocket Injector Element Segmentation for Reliable Hydrocarbon Ignition
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Solution Overview
Problem
Liquid propellant rocket engines face challenges in efficiently igniting hydrocarbon fuels with oxygen, as existing ignition systems may not ensure optimal combustion initiation and mixing of propellants.
Innovation Solution
The design of an injector element with a central oxidizer conduit, coaxial first and second annuli, and a feed system that connects these annuli to facilitate the introduction of ignition fluid and fuel into a combustion chamber, enabling efficient mixing and combustion through a monolithic, additive manufacturing process.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a conventional ignition system is used to ignite hydrocarbon fuel with oxygen, then combustion initiation can be achieved, but optimal combustion initiation and mixing of propellants cannot be ensured
Solution Approach 1:
The injector element is segmented into multiple functional zones: a central cavity for oxidizer injection, a first annulus for ignition fluid injection, and a second annulus for fuel injection. This segmentation allows each zone to perform its specific function optimally, ensuring reliable combustion initiation while maintaining efficient propellant mixing.
Solution Approach 2:
The ignition fluid is injected into the central cavity before the main fuel and oxidizer combustion occurs. This preliminary action of introducing a reactive ignition fluid into the oxidizer stream ensures reliable combustion initiation, which then triggers the efficient burning of the main propellants.
2Ease of manufacture
If multiple separate components are used for oxidizer conduit, annuli, and feed chambers, then assembly and modification may be easier, but manufacturing precision and structural integrity are compromised
Solution Approach 1:
The oxidizer conduit, first annulus, second annulus, and feed chambers are merged into a single monolithic injector element. This integration ensures precise alignment and tight tolerances between all fluid passages and injection surfaces, achieving high manufacturing precision while maintaining ease of manufacture through additive manufacturing processes.
Solution Approach 2:
The invention utilizes additive manufacturing technology to change the manufacturing process parameters, enabling the production of complex monolithic structures with internal fluid passages that would be difficult or impossible to achieve with traditional machining or assembly methods.
3Ease of operation
If ignition fluid and fuel are injected separately without a feed port connection, then injection independence is maintained, but efficient mixing and spontaneous combustion initiation are hindered
Solution Approach 1:
The feed port acts as an intermediary connection between the first annulus (ignition fluid) and the second annulus (fuel). This intermediary passage allows the ignition fluid to flow into the fuel stream, creating a premixed reactive mixture that ensures reliable spontaneous combustion initiation when injected into the oxidizer-containing central cavity.
Solution Approach 2:
The feed port utilizes fluid pressure differentials to control the flow of ignition fluid from the first annulus through the feed port into the second annulus, and subsequently into the central cavity. This hydraulic connection ensures proper mixing ratios and timing for reliable combustion initiation.
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 configuration ensures efficient ignition and combustion by allowing for precise fluid mixing and spontaneous combustion initiation, enhancing thrust generation in liquid propellant rocket engines.
Implementation Method 1
a first annulus at least partially surrounding the oxidizer conduit, and fluidly connected to the oxidizer conduit... a second annulus at least partially surrounding the oxidizer conduit, and fluidly connected between the first annulus and the central cavity
Implementation Method 2
one or more of the inlet ports is sloped with respect to a central axis of the oxidizer conduit
Data Source
AI summary
An injector element for a liquid propellant rocket engine includes an oxidizer conduit, a central cavity that is fluidly coupled with the oxidizer conduit downstream of the oxidizer conduit, a first annulus that at least partially surrounds the oxidizer conduit and is fluidly coupled with an ignition fluid supply downstream of the ignition fluid supply, and a second annulus that at least partially surrounds the oxidizer conduit and is fluidly coupled with a fuel supply downstream of the fuel supply. The second annulus is fluidly coupled between the first annulus and the central cavity.