Design of a pintle injector

Download

index.pdf

Date

2019

Author

Erkal, Berksu

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

325
views

204
downloads

Pintle injector design methodology for liquid oxygen/gaseous methane rocket engine is investigated with this study. Cold flow experimental work is conducted with water and air to investigate the characteristics of designed injectors by observing spray formations. 750N at maximum thrust with 3:1 throttle ability is chosen as mission requirement. 3 different reservoir geometries are manufactured and experimental investigation is conducted to ensure uniform and axisymmetric spray cone. After decision of the final reservoir, 6 different injectors are designed which are combination of 3 different pintle angles and 2 different annular gap thickness. Non-dimensional parameters from literature are used to determine water and air mass flow rates of cold flow experiments. Phase Doppler Particle Analyzer (PDPA) is utilized to obtain droplet Sauter mean diameters (SMD) and velocity profile in axial and radial direction within the spray. These experiments are carried out for 3 different throttle level for all injectors designed. Spray half cone angles are measured by high speed camera and high contrast images are obtained for post processing observations. At studied flow rates recirculation zone is obtained only for 20° instead of 30° and 40° pintle angles and Sauter Mean Diameter (SMD) increase is experienced at the end of these recirculation zones. Moreover, wider spray half angles up to 58° are obtained with the pintle angle of 20°. SMD values are in the range of 20-50 μm for all injector types at recirculation zones and injectors with 20° pintle angle have the lowest SMD values compared with the other injectors.

Subject Keywords

Injectors., Pintle Injectors, Throttling, Phase Doppler Particle Analyzer.

URI

http://etd.lib.metu.edu.tr/upload/12624543/index.pdf
https://hdl.handle.net/11511/44654

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

Design of a test setup for altitude simulation Aydoğdu, Ataman; Ulaş, Abdullah; Department of Mechanical Engineering (2019) Altitude simulation testing is an important concept in missile systems, especially in terms of aerothermal ground testing and high speed air breathing engine free-jet testing. Those tests of the missile systems at supersonic speeds need High Altitude Test System (HATS) which simulates Mach number, total pressure and total temperature of the flow on the test article mounted in the test chamber by using free-jet nozzle. To start the free-jet nozzle operation which simulates high altitude conditions, test cham...
Improved combustion model of boron particles for ducted rocket combustion chambers Kalpakli, Bora; Acar, Emir Bedig; Ulaş, Abdullah (Elsevier BV, 2017-5) A combustion model of boron particles for detailed Computational Fluid Dynamics (CFD) based simulations of ducted rocket combustion chambers is studied. It is aimed to construct a model for combustion of boron containing gas mixtures ejected from a solid propellant gas generator. This model includes all main physical processes required to define an accurate particle combustion simulation. The reaction rate modeling in similar, previous studies are improved for ramjet combustion chambers and this model provi...
Assessment of a frequency-domain linearised Euler solver for turbofan aft radiation predictions and comparison with measurements Özyörük, Yusuf (2010-03-31) This paper presents a frequency-domain computational aeroacoustics tool for predicting aft noise radiation through turbofan ducts and jets and its application to two realistic engine exhaust configurations which have been experimentally tested. The tool is based on the discretised axisymmetric form of the linearised Euler equations in conjunction with perfectly matched layer equations at the inlet and far-field boundaries using high-order finite differences. The resultant linear system of equations is inver...
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, ...
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...

Citation Formats

B. Erkal, “Design of a pintle injector,” Thesis (M.S.) -- Graduate School of Natural and Applied Sciences. Mechanical Engineering., Middle East Technical University, 2019.