Numerical Investigation of Transverse Hydrogen Jet into Supersonic Crossflow Using Detached-Eddy Simulation

Won, Sang Hee; Jeung, In‐Seuck; Parent, Bernard; Choi, Jeong‐Yeol

doi:10.2514/1.41165

Cited by 83 publications

(22 citation statements)

References 14 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…Therefore, simulations using RANS equations have been widely conducted. The results are comparable with experimental results and show complex flow characteristics such as separation, recirculation zones, bow shocks, and vortexes near the injector [47,48].…”

Section: Methodssupporting

confidence: 81%

A Numerical Study on the Characteristics of Air–Fuel Mixing Using a Fluidic Oscillator in Supersonic Flow Fields

et al. 2019

View full text Add to dashboard Cite

In this study, numerical simulations were conducted to confirm the possibility of improved mixing performance by using a fluidic oscillator as a fuel injector. Three-dimensional URANS non-reacting simulations were conducted to examine air-fuel mixing in a supersonic flow field of Mach 3.38. The numerical methods were validated through simulations of the oscillating flow generated from the fluidic oscillator. The results show that the mass flow rate and momentum are reduced at the outlet because the total pressure loss increases inside the fluidic oscillator, which means that higher pressure needs to be applied to supply the same mass flow rate. The simulation showed that the flow structure varies over time as the injected flow is swept laterally. With lateral injection, the fuel distribution is long and narrow, and asymmetric vortexes are generated. However, with central injection, the fuel distribution is relatively similar to the case of using a simple injector. Compared to the simple injector, the penetration length, flammable area, and mixing efficiency were improved. However, the total pressure loss in the flow field increases as well. The results showed that the supersonic fluidic oscillator could be fully utilized as a means to enhance the mixing effect, however a method to reduce the total pressure loss is necessary for practical application.It is relatively easy to improve the mixing efficiency, but there is a disadvantage of significantly increasing the total pressure loss at a high Mach number. The cavity has been studied because it helps to mix the air-fuel and it can more effectively hold the flame in empty space where a recirculation zone can be formed on the wall [7][8][9][10][11][12][13][14]. A number of studies have been conducted on experiments or numerical simulations to observe the interaction of the cavity with flow fields in the combustion chamber [13] and derive the optimum cavity shape [7][8][9]. Recent studies have been conducted to find ways to improve the mixing performance through more diverse attempts, such as variable cavities and pylons and double cavities [10,11,14].Using the cavity, a scramjet engine can efficiently mix the air-fuel and hold the flame more easily with less total pressure loss. However, combustion instability can occur due to acoustic interference, and additional systems may be needed to compensate for this. A hyper-mixer is a system where a part of the wall of a combustion chamber has a form such as a ramp or a step. The shape generally induces a counter-rotating vortex, which helps to improve the mixing efficiency and expansion of the mixed area [15][16][17][18][19][20][21]. Studies have been carried out on adjusting the angle, arrangement, and shape of the injector [23-25] and using a swirler or counterflow nozzle [26,27].Unlike passive methods, active methods actively intervene in the flow of combustion chambers. Pulsed injection [28][29][30][31][32][33] and the Hartmann-Sprenger (H-S) tube [34,35] are examples of ways to directly affect the flow through variou...

show abstract

Section: Methodssupporting

confidence: 81%

A Numerical Study on the Characteristics of Air–Fuel Mixing Using a Fluidic Oscillator in Supersonic Flow Fields

et al. 2019

View full text Add to dashboard Cite

show abstract

“…A flush-mounted fuel injector model which is a simple geometric injection system has been investigated to understand the flow physics of the jet interaction [7][8][9][10][11][12]. Since a counter-rotating vortex pair appears behind a jet, fuel-air mixing is induced by jet penetration into supersonic crossflow.…”

Section: Introductionmentioning

confidence: 99%

Effectiveness of jet location on mixing characteristics inside a cavity in supersonic flow

Ukai

Zare‐Behtash

Erdem

et al. 2014

Experimental Thermal and Fluid Science

View full text Add to dashboard Cite

“…A series of simulations by the present authors for single element rocket combustors have shown favorable agreement with available experimental results. 4,5 Other areas of success have been in the fundamental mixing of supersonic injection into cross flow studied by Won et al 6 They found good agreement with experimental results while Peterson et al 7,8 showed that separation regions are poorly predicted with a standard DES model but the predictions were still more successful than pure RANS models. Applied work on scramjet relevant geometries has also been undertaken by Choi et al 9 showing that DES is able to capture a delay in combustion that could not be captured by RANS models.…”

Section: Introductionmentioning

confidence: 91%

Comparison of a Structured-LES and an Unstructured-DES Code for Predicting Combustion Instabilities in a Longitudinal Mode Rocket Combustor

Harvanzinski

Talley

Sankaran

2015

53rd AIAA Aerospace Sciences Meeting

View full text Add to dashboard Cite

A series of three-dimensional reacting flow computational fluid dynamics (CFD) simulations is used to investigate the combustion stability characteristics of a gas-gas shear coaxial rocket injector in a longitudinal model combustion chamber. Two simulation codes are used in this study. The first is a structured explicit time-marching code that uses large eddy simulations (LES) of the turbulent flowfield, while the second is an unstructured implicit time-marching code that uses a detached eddy simulations (DES) model. Simulation results show that both codes are able to predict the key aspects of the marginally stable and unstable operating points. With comparable mesh resolution, the two sets of simulations are qualitatively similar but there are some quantitative differences. Overall, the structured-LES code appears to capture more detailed flow features particularly in the reacting shear layer, but it also seems to over-predict the mean chamber pressure compared to the DES code.

show abstract

Numerical Investigation of Transverse Hydrogen Jet into Supersonic Crossflow Using Detached-Eddy Simulation

Cited by 83 publications

References 14 publications

A Numerical Study on the Characteristics of Air–Fuel Mixing Using a Fluidic Oscillator in Supersonic Flow Fields

A Numerical Study on the Characteristics of Air–Fuel Mixing Using a Fluidic Oscillator in Supersonic Flow Fields

Effectiveness of jet location on mixing characteristics inside a cavity in supersonic flow

Comparison of a Structured-LES and an Unstructured-DES Code for Predicting Combustion Instabilities in a Longitudinal Mode Rocket Combustor

Contact Info

Product

Resources

About