Monopropellant Injection Device with Flow Modulation
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Solution Overview
Problem
Existing liquid propellant injection devices for rocket engines are complex, non-compact, and prone to reduced combustion chamber lifespan due to mixing and combustion occurring close to the chamber wall, leading to potential runoff and fragility issues.
Innovation Solution
A compact monopropellant injection device with convergent annular channels and injection sections oriented perpendicular to the chamber axis, utilizing a movable part with radial orifices for flow modulation and stable injection speed, allowing for sealing and re-ignition, and minimizing wall exposure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If a movable part is used to modulate flow rate in existing injection devices, then flow rate modulation is achieved, but the device becomes complex and non-compact
Solution Approach 1:
The patent merges the movable part with the combustion chamber wall structure, integrating the flow modulation mechanism into the chamber wall itself rather than using a separate complex assembly. The movable part is embedded within the wall to modulate flow between the combustion chamber and propellant supply channel, achieving flow control while maintaining structural integration and compactness.
Solution Approach 2:
The movable part is nested within the combustion chamber wall structure, with the flow modulation mechanism embedded inside the wall thickness. This nesting approach allows the modulation mechanism to be contained within the existing structural envelope, achieving compact design while maintaining the flow control function.
2Productivity
If injection sections are oriented towards the chamber wall, then injection is achieved, but combustion occurs close to the wall reducing lifespan and promoting runoff
Solution Approach 1:
The patent uses asymmetric orientation of the injection sections, where the first and second annular injection sections are positioned at different angular positions and orientations within the chamber. This asymmetric arrangement directs the propellant streams to mix away from the wall rather than directly against it, reducing wall exposure to combustion while maintaining effective injection.
Solution Approach 2:
The patent transitions from traditional axial injection towards the wall to a multi-dimensional injection pattern where propellant streams are directed to intersect in the chamber volume away from the wall. By orienting sections at different angles and using three-dimensional stream interaction, the mixing zone is positioned in the chamber volume rather than at the wall surface, protecting the chamber while maintaining injection efficiency.
3Device complexity
If a single monopropellant supply channel is used, then the device becomes compact, but flow rate modulation capability is reduced
Solution Approach 1:
The patent introduces a movable part within the single supply channel structure that dynamically modulates the flow area between the combustion chamber and the propellant tank. This movable component allows the flow rate to be varied dynamically while maintaining a compact single-channel external structure, achieving both compactness and modulation capability.
Solution Approach 2:
The patent extracts the flow modulation function from a separate complex multi-channel system and implements it within the single supply channel using a movable throttling element. By taking out the modulation capability and integrating it into the single channel structure rather than using multiple independent channels, the system achieves compactness while preserving flow control.
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 solution enables stable and modulated monopropellant injection with reduced risk of chamber wall runoff and increased lifespan, achieving compactness and simplified design while preventing combustion residues and explosions.
Implementation Method 1
The moving part comprises a pilot section subjected to the effects of the flow of monopropellant fluid in the supply channel
Implementation Method 2
acting against the action of an elastic element sized for movement of the moving part into the open position when a force predetermined is exerted on the pilot section
Implementation Method 3
first and second annular channels speed-up concentric connected to the supply channels and emerging at the outlet respectively by first and second annular injection sections
Implementation Method 4
create at the output two sheets of monoer liquid gol injected creating an impact between them
Implementation Method 5
forming a predefined angle so as to create at the output two sheets of monoer liquid gol injected creating an impact between them
Data Source
Figure 1~2
AI summary
The device has a concentric annular speed-up channel (42) and an annular injection section (32) defined by a tapered fixed revolution wall (73) situated at the level of an upstream end (91) and by a secured revolution wall (55) secured to an annular movable part (5). The movable part is movable in translation relative to a tapered fixed revolution wall (94) and the wall (73). The movable part has a set of radial orifices (61) for permitting supply of liquid mono-propellant to the channel from a common supply channel (6) that feeds a concentric annular speed-up channel (41) directly.