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Cavitating Venturi as a Mass Flow Controller in a Deep Throttling Liquid Rocket Engine

Michał Sekrecki
Michał Sekrecki
   | 13 wrz 2023
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Article Category: Research Article
Data publikacji: 13 wrz 2023
Zakres stron: 72 - 86
Otrzymano: 27 wrz 2022
Przyjęty: 27 lip 2023
DOI: https://doi.org/10.2478/tar-2023-0018
Słowa kluczowe
© 2023 Michał Sekrecki, published by Sciendo
This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Figure 1.

Cavitating venturi model and manufactured valve breadboard.
Cavitating venturi model and manufactured valve breadboard.

Figure 2.

Needle profile calculated (second-order curve—linear position control) and linearised (as manufactured—nonlinear position control).
Needle profile calculated (second-order curve—linear position control) and linearised (as manufactured—nonlinear position control).

Figure 3.

Venturi (dark grey) and needle (light grey) positioning in the valve.
Venturi (dark grey) and needle (light grey) positioning in the valve.

Figure 4.

Test setup.
Test setup.

Figure 5.

Cavitation end determination (ethanol); circle marks cavitation end; Valve_IN_raw denotes raw data from valve inlet; Valve_IN_filt_50Hz shows valve inlet data filtered with a 50Hz filter; Valve_OUT_raw denotes raw data from the valve outlet; Valve_out_filt_50Hz indicates valve outlet data filtered with a 50Hz filter.
Cavitation end determination (ethanol); circle marks cavitation end; Valve_IN_raw denotes raw data from valve inlet; Valve_IN_filt_50Hz shows valve inlet data filtered with a 50Hz filter; Valve_OUT_raw denotes raw data from the valve outlet; Valve_out_filt_50Hz indicates valve outlet data filtered with a 50Hz filter.

Figure 6.

Calculated vs. measured mass flow (HTP); needle position as a% of nominal stroke (0% valve closed). HTP, high-test peroxide.
Calculated vs. measured mass flow (HTP); needle position as a% of nominal stroke (0% valve closed). HTP, high-test peroxide.

Figure 7.

Mass flow rate (ethanol) vs. pressure ratio. Cavitation end determination for low mass flow; solid line is the mass flow calculated from measurement points and the grey area denotes the points measured during the test.
Mass flow rate (ethanol) vs. pressure ratio. Cavitation end determination for low mass flow; solid line is the mass flow calculated from measurement points and the grey area denotes the points measured during the test.

Figure 8.

Mass flow rate (ethanol) vs. pressure ratio. Cavitation end determination for high mass flow; solid line is the mass flow calculated from measurement points and grey area marks the points measured during the test.
Mass flow rate (ethanol) vs. pressure ratio. Cavitation end determination for high mass flow; solid line is the mass flow calculated from measurement points and grey area marks the points measured during the test.

Figure 9.

Comparison of different geometry modifications on the pressure ratio. When the mass flow is steady, it means that cavitation occurs.
Comparison of different geometry modifications on the pressure ratio. When the mass flow is steady, it means that cavitation occurs.

Figure 10.

Cavitation zone comparison for baseline and modified geometry at the same outlet pressure.
Cavitation zone comparison for baseline and modified geometry at the same outlet pressure.

Figure 11.

Mass flow vs. needle position calculated for an optimised valve design for the engine test.
Mass flow vs. needle position calculated for an optimised valve design for the engine test.

Figure 12.

Mass flow calculated vs. mass flow obtained during the test.
Mass flow calculated vs. mass flow obtained during the test.

Figure 13.

Valve performance during the 19 s test of LRE at a 110% thrust set; P601 indicates inlet pressure (measured by a 50 barA pressure transducer); P602 is the outlet pressure (filtered); P603 is the inlet pressure (measured by 500 barG pressure transducer); Mflow denotes the mass flow (Coriolis flowmeter); and Vflow is the mass flow (turbine flowmeter). LRE, liquid rocket engine.
Valve performance during the 19 s test of LRE at a 110% thrust set; P601 indicates inlet pressure (measured by a 50 barA pressure transducer); P602 is the outlet pressure (filtered); P603 is the inlet pressure (measured by 500 barG pressure transducer); Mflow denotes the mass flow (Coriolis flowmeter); and Vflow is the mass flow (turbine flowmeter). LRE, liquid rocket engine.

Figure 14.

Valve performance during the 5 s test of LRE at 35% thrust set; P601 is the inlet pressure (measured by a 50 barA pressure transducer); P602 denotes outlet pressure (filtered); P603 is the inlet pressure (measured by a 500 barG pressure transducer); Mflow is the mass flow (Coriolis flowmeter); Vflow denotes mass flow (turbine flowmeter). LRE, liquid rocket engine.
Valve performance during the 5 s test of LRE at 35% thrust set; P601 is the inlet pressure (measured by a 50 barA pressure transducer); P602 denotes outlet pressure (filtered); P603 is the inlet pressure (measured by a 500 barG pressure transducer); Mflow is the mass flow (Coriolis flowmeter); Vflow denotes mass flow (turbine flowmeter). LRE, liquid rocket engine.

Propellant parameters.

  Nominal inlet pressure (barA) Nominal mass flow (kg/s) Density (kg/m3) Viscosity (mPa · s) Vapour pressure (Pa)
HTP 40 1.9 1,435 1.25 200
Ethanol 40 0.5 805.7 1.074 5,950

Cavitating venturi parameters under consideration—considered range.

Parameter Throat length (mm) Divergent angle (°) Needle extension (mm)
Baseline 5 15 0
Considered range Min. 0.5 6 0
Max. 5 20 8
eISSN:
2545-2835
Język:
Angielski
Częstotliwość wydawania:
4 razy w roku
Dziedziny czasopisma:
Engineering, Introductions and Overviews, other, Geosciences, Materials Sciences, Physics
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