Pogo Effect Corrector System Using Venturi Suction
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Solution Overview
Problem
Existing pogo effect corrector systems for liquid propellant rocket engines face challenges in systems with pipe bends, microgravity operations, and low power conditions, leading to unstable hydrodynamic suction and difficulties in additive manufacturing, resulting in potential damage and propellant overconsumption.
Innovation Solution
A pogo effect corrector system utilizing a hydraulic accumulator with a feed pipe portion that includes a constriction segment, where the flow section is reduced to create a Venturi effect, generating suction at rejection orifices for effective gas drainage, even in microgravity or low power conditions, without a projecting tube that disturbs propellant flow and allowing for easier additive manufacturing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a rejection tube with orifices is used to generate hydrodynamic suction, then gas drainage is improved, but the system becomes unstable in pipe bends and difficult to manufacture with additive manufacturing
Solution Approach 1:
The invention extracts the problematic projecting tube portion from the system and replaces it with a rejection passage opening directly into the feed pipe portion at the constriction segment. This eliminates the manufacturing difficulties associated with projecting tubes while maintaining the gas drainage function through the constriction segment's inherent flow characteristics.
Solution Approach 2:
The invention merges the rejection passage with the feed pipe portion structure, integrating the gas drainage function into the existing pipe geometry. The rejection passage opens directly into the feed pipe portion at the constriction segment, combining the flow control and gas drainage functions in a single integrated structure that is easier to manufacture.
2Power
If a projecting tube with orifices is used, then hydrodynamic suction is generated, but the tube shortening required by bends reduces suction effectiveness
Solution Approach 1:
The invention applies local quality by creating a constriction segment with a specific reduced flow section at a localized position in the feed pipe portion. This localized constriction generates the necessary suction effect without requiring a long projecting tube, as the constriction segment itself provides the flow control and suction generation function.
3Reliability
If hydrostatic suction is used in microgravity, then gas drainage is improved, but suction is eliminated or reduced in microgravity conditions
Solution Approach 1:
The invention replaces the gravity-dependent hydrostatic suction mechanism with a constriction-based flow control mechanism. The constriction segment creates suction through local flow acceleration and pressure differential, which is independent of gravitational effects, thereby enabling effective gas drainage in both Earth gravity and microgravity conditions.
4Reliability
If a drain is used to reject excess gas, then gas drainage is achieved, but propellant is overconsumed during pressure rise stages
Solution Approach 1:
The invention implements a feedback mechanism where the constriction segment automatically adjusts the gas drainage rate based on real-time pressure and flow conditions. As propellant pressure rises, the constriction segment's flow characteristics naturally modulate the suction effect, preventing excessive gas rejection and propellant loss while maintaining effective drainage during normal operation.
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 effectively drains excess gas, stabilizes propellant flow, reduces mechanical resonance, and enhances mechanical strength, while being compact and adaptable to bend configurations, thus preventing oscillations and minimizing propellant loss.
Implementation Method 1
the flow section of the feed pipe portion is less than the flow section of the take-off segment, and wherein said at least one rejection passage opens out into the feed pipe portion at the constriction segment
Implementation Method 2
a hydraulic accumulator comprising a tank provided with a gas feed and connected firstly to the feed pipe portion via at least one take-off passage opening out into a take-off segment of the feed pipe portion
Data Source
AI summary
A pogo effect corrector system for a liquid propellant feed system of a rocket engine includes a liquid propellant feed pipe portion, and a hydraulic accumulator including a tank connected firstly to the feed pipe portion firstly via at least one take-off passage opening out into a take-off segment of the feed pipe portion, and secondly via at least one rejection passage opening out into the tank at an intermediate level lying between the at least one take-off passage and the top of the tank, wherein the feed pipe portion possesses a constriction segment where the flow section of the feed pipeline portion is less than the flow section of the take-off segment, and wherein at least one rejection passage opens out into the feed pipeline portion in the constriction segment.