2 edition of A numerical study of mixing in supersonic combustors with hypermixing injectors found in the catalog.
A numerical study of mixing in supersonic combustors with hypermixing injectors
by National Aeronautics and Space Administration, National Technical Information Center, distributor in [Washington, DC], [Springfield, Va
Written in English
|Series||NASA contractor report -- 191027., NASA contractor report -- NASA CR-191027.|
|Contributions||United States. National Aeronautics and Space Administration.|
|The Physical Object|
flow field, resulting due to fuel-air mixing and combustion. Riggins [7,8], et al. observed that, the shock waves, incomplete mixing and viscous effects are the main factors leading to the thrust loss in supersonic combustors though these effects aid mixing. Strut injectors offer a. of Supersonic combustion involves turbulent mixing, shock interaction and heat release in Supersonic flow. 2. Literature Review Kyung Moo Kim  worked on the topic “Numerical study on supersonic combustion with cavity-based fuel injection” their findings are cavity was found to increase both the total.
enhanced mixing in the near-field with the ramp and wedge injectors, while the far-field mixing was found to be similar in all cases. Simulations performed in Fluent agreed well with the experimental data. References 5, 6, and 7 have studied the mixing characteristics of various geometries with inline fuel injection, including a supersonic base-. The object of this work was to study quantitatively the effects of fuel injection parameters on the mixing of gaseous hydrogen with a supersonic air stream confined within a cylindrical duct to provide background information necessary for the design of combustors for supersonic combustion ramjets.
current activities on supersonic combustion in a scramjet engine will be addressed followed by the discussions on the review of numerical simulation on supersonic combustion phenomena related with scramjet engine combustors and ram accelerator. Emphasis was put on the grid refinement, scheme, unsteadiness and phenomenological Size: 2MB. One way to extend the time available for mixing is to inject part of the fuel upstream of the vehicle’s combustion chamber. Injection from the wall remains one of the most challenging problems in supersonic aerodynamics, including the requirement to minimize impulse losses, improve fuel-air mixing, reduce inlet∕combustor interactions, and Cited by:
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Numerical Analysis of Effects of Pseudo Shock Wave Formation on Supersonic Combustion Field Assisted by Plasma Jet JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, Vol.
59, No. Interaction Between Shock Waves, Hydrogen Flame and Plasma Jet in Supersonic FlowCited by: A numerical study was conducted to evaluate the performance of wall mounted fuel-injectors designed for potential Supersonic Combustion Ramjet (SCRAM-jet) engine applications.
The focus of this investigation was to numerically simulate existing combustor designs for the purpose of validating the numerical technique and the physical models : J.
Lee. : Numerical Studies On Supersonic Mixing and Combustion Phenomena: Scramjet and Dual-Mode Combustors (): Tarek Abdel-Salam: Books. A numerical study of mixing in supersonic combustors with hypermixing injectors. LEE; 31st Aerospace Sciences Meeting August Study of compressibility effects of three-dimensional mixing layer by numerical simulation.
AIREX: A numerical study of mixing in supersonic combustors with hypermixing injectors A numerical study was conducted to evaluate the performance of wall mounted fuel-injectors designed for potential Supersonic Combustion Ramjet (SCRAM-jet) engine by: A numerical study of mixing and combustion enhancement has been performed for a Mach 2 model scramjet (supersonic combustion ramjet) combustor.
Fuel (hydrogen) is injected at supersonic speed through the rear of a lobed strut located at the channel symmetry by: A numerical study of mixing and combustion enhancement has been performed by Gerlinger et al.
 for a Mach 2. Due to the extremely short residence time of the air in supersonic combustors, an efficient (rapid and with small losses in total pressure) fuel/air mixing is hard to achieve. Kumaran. to analyze the mixing tendency for geometry of cavity, operating conditions or the shape of the combustor.
In this study, we analyzed mixing characteristics of supersonic combustors by operatpropellant ing conditions and existence of cavity using modal decomposition mod al decomposition method. Energies10, x FOR PEER REVIEW 3 of 21 Figure 3. Transverse injection mixing study of H 2 reported in , red-to-blue denoting the percentage of H 2 species in the domain.
Strut injectors are characterized by their obstruction to the flow direction and oblique shockwaveFile Size: 2MB. In this study, a numerical solver is developed and validated to be an efficient design tool capable of simulating these complicated flow features of the supersonic combustors.
For the code validation, several test cases are considered to monitor the code ability to solve for the diffusive and turbulent fluxes, and the chemical source : Mohammed Kamel, Farouk Owis, Moumen Idres.
Get this from a library. A numerical study of mixing in supersonic combustors with hypermixing injectors. [J Lee; United States. National Aeronautics and Space Administration.].
Characteristics of supersonic mixing and combustion with hydrogen injection upstream of a cavity flameholder are investigated numerically using hybrid RANS/LES (Reynolds-Averaged. This paper describes the numerical study of the combustion enhancement with hydrogen fuel injection in a transverse aperture nozzle into a supersonic hot air stream.
Non-reacting experiments and numerical simulations have been performed to investigate the mixing characteristics in a supersonic combustor with gaseous fuel injection upstream of a flameholding cavity in a supersonic vitiated air flow with stream Mach number Using helium as simulated fuel, the acetone vapor is adulterated into the fuel by: This paper describes the numerical study of the combustion enhancement with hydrogen fuel injection in a transverse aperture nozzle into a supersonic hot air stream.
Several cavities with single and dual steps with different cavity wall angles are by: 1. Benchmark solutionsNumerical study of combustion effects on the development of supersonic turbulent mixing layer flows with WENO schemes. Numerical study of combustion effects on the development of supersonic turbulent mixing layer flows Author: Hongpeng Liu, Zhenxun Gao, Chongwen Jiang, Chunhian Lee.
Combustion cannot be initiated until mixing has been achieved at a molecular level, and, in turn, in regions where combustion has taken place, the temperature rise and the chemical composition changes modify the parameters responsible for mixing.
This close coupling cannot be, in general, separated in the supersonic combustion by: 4. An advanced method for dilution zone mixing in a reverse flow gas turbine combustor was numerically investigated. For long mixing lengths associated with reverse flow combustors (X/H > ), pattern factor was found to be mainly driven by nozzle-to-nozzle fuel flow and/or circumferential airflow variations; conventional radially injected dilution jets could not effectively mix out Cited by: 7.
The major themes are numerical simulation of transsonic and supersonic combustion phenomena, the study of supersonic reacting mixing layers, and turbulent combustion.
Emphasis is laid on hyperbolic models and on numerical simulations of hydrocarbon planes with a complete set of chemical reactions carried out in two-dimensional geometries as.
YANG, KUBOTA, AND ZUKOSKI: SHOCK-INDUCED SUPERSONIC COMBUSTION I i - ~G Q c ~) ~ Fig.3 Vorticity contours at t = for a single circular jet with M = and PLiPH = L is the length of a material element following the fluid, corresponding to a particular mass-fraction level of interest.
For combustion of hydrogen in air, the balanced chemical. 15th International Conference on Fluid Control, Measurements and Visualization MayNaples, Italy Paper ID 1 Numerical simulation of supersonic-supersonic shear flow mixing enhancement based on transverse jet Liu Yang1, *, Ma Dong1, Yu Xiao-jing2, Chai Ze-xin1 1Science and Technology on Combustion, Internal Flow and Thermo-structure Laboratory, NorthwesternFile Size: 1MB.Issue 11 - June 01 - Research on Supersonic Combustion and Scramjet Combustors at ONERA AL One can see that the position of the maxima is well respected by the computation, as well as the level inside the jet.
A small discrepancy exists outside the jet, where the computed values vanish more quickly than the experimental ones.THE problem of complete fuel-oxidant mixing in SCRAMJET combustors, given the short residence time and the inherently low mixing rates, is not a triv ial one.
To obtain the necessary mixing rates, super sonic combustors will utilize wall-mounted and/or strut .