Rocket Engine Fuel Flow Control via Parallel Network
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Solution Overview
Problem
Liquid propulsion rocket engines face fluctuations in fuel flow due to the operation of thrust vector control actuators, which can alter the fuel/oxidizer mixing ratio in the main combustion chamber, requiring complex controls and hardware adjustments.
Innovation Solution
A flow control system with parallel network portions, a fueldraulic device, and a flow restriction orifice that generates a pressure differential to control fuel flow through a flow control valve, ensuring constant fuel flow to the combustion chamber independent of thrust vector control actuator operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a fueldraulic device is used to power the thrust vector control actuator, then the actuator can be hydraulically powered by fuel tapped from the main fuel supply, but operation of the actuator changes the fuel flow in the main fuel supply, altering the fuel/oxidizer mixing ratio in the main combustion chamber
Solution Approach 1:
The fuel passage network is divided into first and second network portions that are in parallel flow arrangement. The fueldraulic device is located in the first network portion while the flow control valve is located in the second network portion, allowing independent control of fuel flow to the actuator versus fuel flow to the combustion chamber.
Solution Approach 2:
A flow restriction orifice is arranged in series with, and upstream of, the fueldraulic device. The orifice generates a pressure differential that varies responsive to flow through the first network portion, and this pressure differential controls the flow control valve to maintain constant fuel flow to the combustion chamber.
2Adaptability or versatility
If fuel flow is tapped for the fueldraulic device, then the actuator can operate, but complex controls and hardware are required to adjust oxidizer flow to maintain mixing ratio
Solution Approach 1:
The flow control valve is operable responsive to the pressure differential across the flow restriction orifice to automatically control flow through the second network portion. This self-regulating mechanism maintains constant fuel flow to the combustion chamber without requiring external control systems or hardware adjustments.
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 system stabilizes fuel flow to the combustion chamber, reducing fluctuations and maintaining a consistent fuel/oxidizer mixing ratio, thereby simplifying control mechanisms and reducing the impact of thrust vector control on engine performance.
Implementation Method 1
The flow restriction orifice is operable to generate a pressure differential that varies responsive to the flow through the first network portion
Data Source
AI summary
A flow control system (22) includes a fuel passage network (34) that has first (36) and second (38) network portions that are in a parallel flow arrangement with each other. A fueldraulic device (40) is located in the first network portion. Operation of the fueldraulic device varies flow through the first network portion. A flow restriction orifice (42) is located in the fuel passage network and is arranged in series with, and upstream of, the fueldraulic device. The flow restriction orifice is operable to generate a pressure differential that varies responsive to the flow through the first network portion. A flow control valve (44) is located in the second network portion. The flow control valve is operable responsive to the pressure differential across the flow restriction orifice to control flow through the second network portion.