Jet Pump Pressure Boost for Rocket Engine Supply Lines
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Solution Overview
Problem
The existing staged combustion rocket engines face pressure drops in supply lines due to bends, leading to inefficient pump operation and requiring additional components like booster pumps, which increase complexity, weight, and cost.
Innovation Solution
Incorporating jet pumps in the supply lines to inject pressurized fluid, which increases pressure upstream of the pumps, thereby compensating for pressure drops and eliminating the need for booster pumps.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Length of moving object
If the supply lines are arranged with bends upstream of the pumps to minimize hot gas circuit length, then the hot gas reinjection circuit length is reduced, but pressure drops occur in the supply lines
Solution Approach 1:
A jet pump is introduced as an intermediary device between the supply line and the main pump. The jet pump receives high-pressure fluid from the distribution circuit and injects it into the supply line upstream of the main pump, acting as a mediator that compensates for pressure drops without requiring additional turbomachines in the main propulsion path.
Solution Approach 2:
The invention utilizes hydraulic principles by employing a jet pump that uses the kinetic energy and pressure of the fluid flow itself to drive the pressurization process. The jet pump converts the energy of the incoming fluid into pressure rise, eliminating the need for mechanical booster pumps and reducing overall system complexity.
2Stress or pressure
If booster pumps are added to compensate for pressure drops in supply lines, then sufficient pressure is maintained at pump inlet ports, but device complexity and weight increase
Solution Approach 1:
The jet pump is designed to be self-driven by the fluid flow itself. The high-pressure fluid from the distribution circuit directly drives the jet pump, which then pressurizes the supply line. This self-service mechanism eliminates the need for external booster pumps or additional power sources, reducing complexity while maintaining required pressure.
Solution Approach 2:
The jet pump is integrated into the existing supply line configuration, merging the pressurization function with the fluid transport system. By combining the jet pump with the supply line architecture, the invention avoids adding separate booster pump systems, thereby reducing overall device complexity and component count.
3Stress or pressure
If the pressure in fuel and oxidizer tanks is increased to maintain sufficient pressure at pump inlet ports, then adequate pressure is achieved, but reservoir wall thickness must increase
Solution Approach 1:
The jet pump performs preliminary pressurization of the supply line before the fluid reaches the main pump. By establishing adequate pressure upstream of the pump through the jet pump's action, the system avoids the need to increase tank pressure, thereby eliminating the requirement for thicker reservoir walls.
Solution Approach 2:
The jet pump acts as an intermediary pressurization device between the tank and the main pump. It provides the necessary pressure boost without requiring the tank itself to operate at higher pressures, thus avoiding the need to increase wall thickness while still ensuring adequate pressure at the pump inlet.
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 solution maintains sufficient pressure at the pump inlet ports, reduces complexity and weight, and prevents cavitation, ensuring stable engine operation without additional turbomachines.
Implementation Method 1
there is arranged a jet pump, and that the distribution circuit is capable of directing part of the fluid circulating in said first supply line and having been pressurized to said jet pump, and the jet pump is adapted to inject said portion of fluid so as to drive the fluid circulating in said first supply line towards an inlet port of said first pump
Data Source
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AI summary
The invention relates to a rocket engine (100), which includes an antechamber and combustion chamber (14), two supply lines (22A, 22B) for the engine, and two turbopumps (20A, 20B). The engine is a staged-combustion engine. A jet pump (102A, 102B) is arranged in at least a first supply line (12A, 12B). After being pressurized, a portion of the fluid circulating in the first supply line is directed towards the jet pump, so as to enable said pump to convey the fluid circulating in said first supply line to the intake of said first pump, thereby increasing the pressure at the supply port of the pump.