Last edited by JoJogor
Tuesday, May 19, 2020 | History

3 edition of LOX/hydrogen coaxial injector atomization test program found in the catalog.

LOX/hydrogen coaxial injector atomization test program

LOX/hydrogen coaxial injector atomization test program

Written in English

Subjects:
• Atomizing.,
• Drop size.,
• Fuel sprays.,
• Injectors.,
• Liquid propellant rocket engines.,
• Mathematical models.,
• Velocity distribution.

• Edition Notes

The Physical Object ID Numbers Statement M. Zaller. Series NASA contractor report -- 187037., NASA contractor report -- NASA CR-187037. Contributions Lewis Research Center. Format Microform Pagination 1 v. Open Library OL17725190M

to Transcritical Injection In this section, the behavior of relevant thermophysical properties is dis-cussed. For coaxial injection of O 2 and H 2 in a liquid rocket engine, the oxygen is typically injected at a cold, subcritical temperature, with a liquid-like density through the center post, while the hydrogen, which. Research items addressed on the Mascotte test rig include: injector concepts; liquid oxygen jet atomization and combustion, new propellant combinations (methane instead of hydrogen), ignition, heat transfer at the chamber walls, high frequency instabilities, flow-separation in an over-expanded nozzle, plume and infrared signature. IntroductionCited by: 1.

fabricate than coaxial injectors, they are also an atmactive candidate for use in LOX/hydrogen engines. There is also a current interest in engines where both propellants are injected as gas; here, the impinging jet injector system would also be favored over coaxial jets due to its superior mixing by: 3. Figure 1. a) XCOR test firing of a 7, pound-thrust LOX/methane engine b) Purdue students designed an built a 17kN LOX/CH4 combustion chamber as part of NASA's Project Morpheus.c) Aerojet lbf LOX/LCH4 reaction control engine in test at NASA GRC.d) Firefly Space Systems was developing a LOX/methane engine for a light satellite launch vehicle.

Michael M Micci and D. Gandlihon, , "Shear Coaxial Injector LOX Droplet Measurements as a Function of Hydrogen Injection Temperature", Atomization and Sprays Michael M Micci, , "On the Inability of the Magnetic Flowmeter Burner to Measure the Imaginary Part of a Solid Propellant Response", Journal of Propulsion and Power. The present work focuses on the numerical modeling of combustion in liquid-propellant rocket engines. Pressure and temperature are well above thermodynamic critical points of both the propellants and then the reactants show liquid-like characteristics of density and gas-like characteristics for diffusivity. The aim of the work is an efficient numerical description of the phenomena and RANS Cited by:

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A test program is being conducted at the NASA Lewis Research Center to obtain hot fire atomization data in liquid oxygen (LOX)/gaseous hydrogen coaxial injector sprays.

Before hot fire testing is attempted, non-reacting, supercritica[ pressure, vaporizing sprays will be studied to determine the feasibility of making measurements in such Size: KB.

Get this from a library. LOX/hydrogen coaxial injector atomization test program. [Michelle M Zaller; Lewis Research Center.]. The mean drop size predictions for a single element coaxial injector range from to microns, emphasizing the need for additional studies of the atomization process in LOX/H2 engines.

Selection of cold flow simulants, measurement techniques, and hardware for LOX/H2 atomization. LOX/hydrogen coaxial injector atomization test program. Quantitative information about the atomization of injector sprays is needed to improve the accuracy of computational models that predict the performance and stability margin of liquid propellant rocket engines.

To obtain this data, a facility for the study of spray atomization is Author: M. Zaller. In this paper a mixed Euler-Lagrange approach is used for a 3D simulation of a LOX/H2 model rocket combustor with a single shear coaxial injector.

The specific test case presented is the MASCOTTE combustor at 10 bar pressure in the so called A by: 1. LOX/Hydrogen Coaxial Injector Atomization Test Program.

Quantitative information about the atomization of injector sprays is needed to improve the accuracy of computational models that predict the performance and stability margin of liquid propellant rocket engines. To obtain this data, a facility for the study of spray atomization is.

Experimental investigations of reactive sprays with original propellants, liquid oxygen as oxidizer and hydrogen and methane as fuels, are presented and the influence of the injection conditions. liquid oxygen.

Experimental investigations of reactive sprays with original propellants, liquid oxygen as oxidizer and hydrogen and methane as fuels, are presented and the influence of the injection conditions and of the fuel on the atomization and spray flame is discussed.

INTRODUCTIONFile Size: KB. The results for LOX/H2- and LOX/CH4-spray combustion are compared, also the influence of the injection conditions of the propellants on atomization and spray flame is discussed. chamber with a single coaxial injector which uses gaseous hydrogen as the fuel and liquid oxygen as the oxidizer with the help of CFD software package FLUENT.

For the GH2/LOX turbulent flame, the obtained results are compared with results from literature to verify the model and the numerical scheme. The atomization experimental platform used in this research is shown in Fig.

nitrogen resource works as pressurization bottle. Due to bad atomization characteristics of liquid/liquid pintle injectors, the gaseous methane rather than liquid methane was chosen as fuel, mainly because the gaseous methane can improve the atomization characteristics of the pintle by: A test program is being conducted at the NASA Lewis Research Center to obtain hot fire atomization data in Liquid oxygen (LOX)/gaseous hydrogen coaxial injector sprays.

Before hot fire testing is attempted, non- reacting, supercriticaL pressure, vaporizing sprays will be studied to determine the feasibility of making.

Study on the Design Criteria of the Coaxial Injector for a LOX/Hydrogen Rocket Engine The features of this model are that it allows calculation of the local rate of atomization of the LOX jet and deals with droplet size distribution of the LOX spray.

Additionally the model applies the burning rate constant of LOX/hydrogen combustion derived Cited by: 4. Porous injectors represent an alternative injection concept to coaxial injectors for rocket engine applications using gas/liquid propellant combinations such as liquid oxygen (LOX)/hydrogen (H 2).

This paper summarizes the main design features of porous injectors and proposes a mechanism of atomization for porous injectors that is considerably different to the atomization mechanism for coaxial : J.

Deeken, D. Suslov, M. Oschwald, S. Schlechtriem, O. Haidn. varying the injection duration. The engine was started on gasoline and the throttle was adjusted to get the desired load at the idesired engine speed. Although it was possible to s~art the engine directly on hydrogen, starting on gasoline was preferred to conserve hydrogen fuel during warm-up and initial test setting.

The engine was then switched. Zaller, M.: LOX/Hydrogen Coaxial Injector Atomization Test Program. NASA CR, To be published in the proceedings of the 27th JANNAF Combustion. The theoretical model and numerical scheme established in the preceding sections are implemented to study the coaxial injection and combustion of LOX and methane under supercritical conditions.

Table 1 summarizes the flow conditions considered herein. In Case 1, liquid oxygen and methane are injected at temperatures of and K, by: This paper reports the results of a test campaign of a laser-ignited combustion chamber with 15 shear coaxial injectors for the propellant combination LOX/methane.

ignition tests were performed for sea-level conditions. The igniter based on a monolithic ceramic laser system was directly attached to the combustion chamber and delivered 20 pulses with individual pulse energies of { \pm Cited by: 7.

The processes of mixing and combustion in the jet of a shear-coaxial injector are investigated. Two test cases (nonreacting and reacting) are simulated using the commercial computational fluid dynamics code ANSYS CFX.

The first test case is an experiment on the mixing in a nonreacting coaxial jet carried out with the use of planar laser induced fluorescence (PLIF).Cited by: 1. Mechanisms of Combustion Instabilities in Liquid Rocket Engines • Most extensive recent references: Harrje, D.T.

and, Reardon, F.H. (Editors) () Liquid Propellant Rocket Combustion Instability, NASA SP Yang, V. and Anderson, W. (Editors) () Liquid Rocket Engine Combustion Instability, Vol.

AIAA Progress in Aeronautics and Size: 7MB. ResearchArticle Numerical Simulations of the Flame of a Single Coaxial Injector andMarkusFeil InstituteofSpacePropulsion,GermanAerospaceCenter(DLR),LangerGrund,Hardthausen,GermanyCited by: 1.You can write a book review and share your experiences.

Other readers will always be interested in your opinion of the books you've read. Whether you've loved the book or not, if you give your honest and detailed thoughts then people will find new books that are right for them.

Free ebooks since The injector assembly contains a single gas-gas shear coaxial injector and is shown in Fig. 3. Oxygen flows through the center tube surrounded by an annulus of hydrogen.

The injector is of a modular design that allows the inner tube and the injector face plate to be modified, which allows the propellant injection velocities to.