Study of vortex throttle characteristics with adjustable resistance by rotation of the vortex chamber inlet channel
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Inna Levitsky
Abstract
The study is aimed at obtaining and analyzing the flow and cavitation characteristics of the proposed control devices, which are in demand in control systems for aircraft and rocket engines, chemical and other technological processes that require a wide range of flow control at high pressure drops. The characteristics of vortex throttling devices with cylindrical and spherical chambers were obtained, providing flow control in the range of 0.1–25 kg/s. A change in flow rate in the range of 3.5–3.8 can be achieved by changing the flow swirl intensity without throttling the flow sections. When vortex devices operate, the threshold for the occurrence of cavitation shifts to the region of small values of P out /P in, and, starting from the values of the geometric characteristic A > 4.5, cavitation is absent throughout the entire range of flow control. The pressure drop at the inlet channel of the vortex chamber does not exceed 10–30 % of the total resistance of the device. The torque on the control roller is small, 1.8–2.8 Nm, regardless of the flow rate.
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Research ethics: This research work belongs to the author’s own contribution.
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Author contributions: The author has accepted responsibility for the entire content of this submitted manuscript and has approved the submission.
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Competing interests: The author declares no conflicts of interest regarding this article.
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Research funding: This study was supported by an internal funding program of SCE – Shamoon College of Engineering to Dr. Inna Levitsky.
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Data availability: The raw data can be obtained on request from the corresponding author.
Nomenclature
- A
-
vortex chamber geometric characteristic (−)
- b
-
width of the tangential channel (m)
- D
-
chamber diameter (m, mm)
- d
-
diameter of the bypass orifice (mm)
-
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the compression ratio of the stream (−)
- F in
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area of the vortex chamber entrance channels (m2)
- F n
-
outlet nozzle area (m2)
- F p
-
pipeline area (m2)
- h
-
height of the vortex chamber (mm)
- k 1
-
dimensionless coefficient (−)
- k 2
-
dimensionless coefficient (−)
- K v
-
cavitation number (−)
- L
-
distance between the axes of the roller and the chamber (m, mm)
- l
-
length of the tangential channel (m, mm)
- m
-
mass flow rate (kg/s)
- P in
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input pressure (Pa)
- P out
-
output pressure (Pa)
- ∆P
-
pressure drop across the device (Pa)
- r
-
radius of the input edge rounding (m, mm)
- R
-
flow swirl radius (m, mm)
- r 1
-
radius of o axial velocity occurrences in the vortex chamber (m, mm)
- R c
-
radius of the vortex chamber (m, mm)
- r in
-
radius of the inlet channel (m, mm)
- r m
-
radius of the gas vortex (m, mm)
- r n
-
radius of the outlet nozzle (m, mm)
- V p
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speed of the liquid in the pipeline (m/s)
Greek symbols
- ɛ
-
stream compression ratio (−)
- ζ
-
resistance coefficient of the system (−)
- λ
-
ratio of the radius input edge nozzle rounding to its radius (−)
- µ
-
flow coefficient of the vortex chamber outlet nozzle (−)
- ρ
-
density of the liquid (kg/m3)
- φ
-
angle of the roller rotation from the position corresponding to the radial entry of the flow into the chamber (º)
- φ n
-
nozzle orifice fill factor (−)
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© 2024 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- Frontmatter
- Computational analysis of the scramjet mode of the RBCC inlet using micro vortex generators
- Predicting compressor mass flow rate using various machine learning approaches
- Performance analysis of a gas turbine engine with intercooling and regeneration process - Part 1
- Performance analysis of pulse detonation ramjet
- Investigation on flow characteristics and its effect on heat transfer enhancement in a wedge channel with combination of circular, oblong, teardrop, and pencil pin fins
- Effect of perforated wall in controlling the separation due to SWBLI at Mach no. 5 to 9
- Research on performance seeking control of turbofan engine in minimum hot spot temperature mode
- Experimental study on flow field and combustion characteristics of V-gutter and integrated flameholders
- Probabilistic analysis of blade flutter based on particle swarm optimization-deep extremum neural network
- Numerical and experimental study on the critical geometric variation based on sensitivity analysis on a compressor rotor
- Aero-engine direct thrust control based on nonlinear model predictive control with composite predictive model
- Simple model of turbine-based combined cycle propulsion system and smooth mode transition
- Effect of inlet diameter on the flow structure and performance for aluminum-based water-jet engine
- Multi-objective optimization of the aerodynamic performance of butterfly-shaped film cooling holes in rocket thrust chamber
- Application of KH-RT model in lifting flame of methanol jet atomization
- Study of vortex throttle characteristics with adjustable resistance by rotation of the vortex chamber inlet channel
- Enhancing transonic compressor rotor efficiency by flow analysis-driven blade section modification
- Performance analysis of a planar shaped strut injector based supersonic combustion chamber
- The study of cascading effect in the integration of intake with gas turbine engine bay in subsonic cruise vehicle
Artikel in diesem Heft
- Frontmatter
- Computational analysis of the scramjet mode of the RBCC inlet using micro vortex generators
- Predicting compressor mass flow rate using various machine learning approaches
- Performance analysis of a gas turbine engine with intercooling and regeneration process - Part 1
- Performance analysis of pulse detonation ramjet
- Investigation on flow characteristics and its effect on heat transfer enhancement in a wedge channel with combination of circular, oblong, teardrop, and pencil pin fins
- Effect of perforated wall in controlling the separation due to SWBLI at Mach no. 5 to 9
- Research on performance seeking control of turbofan engine in minimum hot spot temperature mode
- Experimental study on flow field and combustion characteristics of V-gutter and integrated flameholders
- Probabilistic analysis of blade flutter based on particle swarm optimization-deep extremum neural network
- Numerical and experimental study on the critical geometric variation based on sensitivity analysis on a compressor rotor
- Aero-engine direct thrust control based on nonlinear model predictive control with composite predictive model
- Simple model of turbine-based combined cycle propulsion system and smooth mode transition
- Effect of inlet diameter on the flow structure and performance for aluminum-based water-jet engine
- Multi-objective optimization of the aerodynamic performance of butterfly-shaped film cooling holes in rocket thrust chamber
- Application of KH-RT model in lifting flame of methanol jet atomization
- Study of vortex throttle characteristics with adjustable resistance by rotation of the vortex chamber inlet channel
- Enhancing transonic compressor rotor efficiency by flow analysis-driven blade section modification
- Performance analysis of a planar shaped strut injector based supersonic combustion chamber
- The study of cascading effect in the integration of intake with gas turbine engine bay in subsonic cruise vehicle
