Show/Hide Menu
Hide/Show Apps
Logout
Türkçe
Türkçe
Search
Search
Login
Login
OpenMETU
OpenMETU
About
About
Open Science Policy
Open Science Policy
Open Access Guideline
Open Access Guideline
Postgraduate Thesis Guideline
Postgraduate Thesis Guideline
Communities & Collections
Communities & Collections
Help
Help
Frequently Asked Questions
Frequently Asked Questions
Guides
Guides
Thesis submission
Thesis submission
MS without thesis term project submission
MS without thesis term project submission
Publication submission with DOI
Publication submission with DOI
Publication submission
Publication submission
Supporting Information
Supporting Information
General Information
General Information
Copyright, Embargo and License
Copyright, Embargo and License
Contact us
Contact us
Passive flow control in liquid-propellant rocket engines with cavitating venturi
Date
2006-04-01
Author
Ulaş, Abdullah
Metadata
Show full item record
This work is licensed under a
Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License
.
Item Usage Stats
309
views
0
downloads
Cite This
In a companion liquid rocket engine development project, due to the overall weight constraint of the propulsion system, a cavitating venturi is selected to control the liquid fuel and liquid oxidizer mass flow rates. Two cavitating venturis, one for the fuel and the other for the oxidizer, are designed to deliver the desired mass flow rates for a specified operating inlet pressure, temperature, and inlet cross-sectional area. The converging and diverging angles of the venturis are selected from the literature for minimum pressure losses. An experimental setup is designed to verify that the cavitating venturis can deliver the specified flow rates. Two different techniques are used to pressurize the system: in the first method, pressurized nitrogen as is used, and in the second method, high pressure combustion gases generated from a solid propellant gas generator are used. Transient mass flow rates could not be measured using standard methods due to the short duration of the water tests; instead, average mass flow rates are calculated. The results verify that the designed cavitating venturis can indeed provide the desired mass flow rates.
Subject Keywords
Modelling and Simulation
,
Instrumentation
,
Electrical and Electronic Engineering
,
Computer Science Applications
URI
https://hdl.handle.net/11511/62334
Journal
FLOW MEASUREMENT AND INSTRUMENTATION
DOI
https://doi.org/10.1016/j.flowmeasinst.2005.10.003
Collections
Department of Mechanical Engineering, Article
Suggestions
OpenMETU
Core
Ultrafast spectroscopy diagnostic to measure localized ion temperature and toroidal velocity fluctuations
Uzun Kaymak, İlker Ümit; McKee, G. R.; Schoenbeck, N.; Smith, D.; Winz, G.; Yan, Z. (AIP Publishing, 2010-10-01)
A dual-channel high-efficiency, high-throughput custom spectroscopic system has been designed and implemented at DIII-D to measure localized ion thermal fluctuations associated with drift wave turbulence. A large-area prism-coupled transmission grating and high-throughput collection optics are employed to observe C VI emission centered near lambda = 529 nm. The diagnostic achieves 0.25 nm resolution over a 2.0 nm spectral band via eight discrete spectral channels. A turbulence-relevant time resolution of 1 ...
NUMERICAL INVESTIGATION OF BUBBLING FLUIDIZED BED TO BE USED AS THERMAL ENERGY STORAGE INTEGRATED TO HIGH-TEMPERATURE CONCENTRATED SOLAR POWER
HİÇDURMAZ, SERDAR; Tarı, İlker (Begell House, 2018-01-01)
A thermal energy storage unit designed to be used in a solid particle concentrated solar energy system is analyzed with the help of ANSYS Fluent 17.0. Hydrodynamics of the bubbling fluidized sand bed of 0.28 m × 1 m × 0.025 m dimensions to be used as a direct contact heat exchanger is modeled and validated. Geldart B-type particles with diameter of 275 micrometers and density of 2500 kg/m3 are used in modeling of bubbling fluidized sand bed. A Syamlal−O'Brien drag model with restitution coefficient of 0.99 ...
Numerical analysis of regenerative cooling in liquid propellant rocket engines
Ulaş, Abdullah (2013-01-01)
High combustion temperatures and long operation durations require the use of cooling techniques in liquid propellant rocket engines (LPRE). For high-pressure and high-thrust rocket engines, regenerative cooling is the most preferred cooling method. Traditionally, approximately square cross sectional cooling channels have been used. However, recent studies have shown that by increasing the coolant channel height-to-width aspect ratio and changing the cross sectional area in non-critical regions for heat flux...
Analysis of regenerative cooling ın liquid propellant rocket engines
Boysan, Mustafa Emre; Ulaş, Abdullah; Department of Mechanical Engineering (2008)
High combustion temperatures and long operation durations require the use of cooling techniques in liquid propellant rocket engines. For high-pressure and high-thrust rocket engines, regenerative cooling is the most preferred cooling method. In regenerative cooling, a coolant flows through passages formed either by constructing the chamber liner from tubes or by milling channels in a solid liner. Traditionally, approximately square cross sectional channels have been used. However, recent studies have shown ...
Comparison of different aspect ratio cooling channel designs for a liquid propellant rocket engine
Boysan, M. E.; Ulaş, Abdullah; Toker, K. A.; Seckin, B. (2007-06-16)
High combustion temperatures and long operation durations require the use of cooling techniques in liquid propellant rocket engines. For high-pressure and high-thrust rocket engines with long operation times, regenerative cooling is the most preferred cooling method. In regenerative cooling, a coolant flows through passages formed either by constructing the chamber liner from tubes or by milling channels in a solid liner. Traditionally, approximately square cross sectional channels have been used. However, ...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
A. Ulaş, “Passive flow control in liquid-propellant rocket engines with cavitating venturi,”
FLOW MEASUREMENT AND INSTRUMENTATION
, pp. 93–97, 2006, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/62334.