Experimental study of interaction between supersonic duct flow and jets surrounded by the porous cavity

Kuniyoshi, Nao; Yaga, Minoru; Koda, Akito; Teruya, Isao; Ishikawa, Masaaki

doi:10.1016/j.expthermflusci.2012.03.011

Cited by 10 publications

(6 citation statements)

References 14 publications

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“…In this experiment, the heat detectors can only detect a streamwise flow direction in the cavity. And it was proved that the thermal tuft probe used in the experiment does not disturb the flow [9].…”

Section: Thermal Tuft Probementioning

confidence: 95%

Study of Interaction between Supersonic Flow and Rods or Jets Surrounded by Porous Cavity

Kuniyoshi¹,

Yaga²,

Koda³

et al. 2012

OJFD

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In this experiment, the effects of the combination of jets or rods and a porous cavity on the supersonic flow field are studied by means of visualization of schlieren method and the measurements of wall static pressures and the flow direction in the cavity with the thermal tuft probe. Three cases of jets or rods arrangements are tested in the experiments. As a result, a bow shock wave which is generated by the jets or rods is observed by mean of schlieren method. And it is confirmed that the expansion region appears downstream of the rods but is not in case of the jets pattern. Moreover the pressure ratios of starting shock wave passing through porous cavity for jets pattern differ from that of rods pattern. In the cavity, the flow direction at the measurement position in the cavity is always opposite to the main flow, as long as the starting shock wave is located upstream of the porous cavity for all cases. Difference in the backward flow ratio between the jets and rods patterns is observe after the starting shock wave passes through the porous cavity.

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Section: Thermal Tuft Probementioning

confidence: 95%

Study of Interaction between Supersonic Flow and Rods or Jets Surrounded by Porous Cavity

Kuniyoshi¹,

Yaga²,

Koda³

et al. 2012

OJFD

Self Cite

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“…This flow field has experimentally investigated with Schlieren method, pressure measurements, and a thermal tuft probe which can detect flow directions. [9][10][11][12] As a result, it is found that the cavity flow is affected by the jets arrangements, which concerns the three dimensional structure of the bow shock wave. In the experiments, it is difficult to clarify the detailed three-dimensional flow around the cavity and the circulation between the main flow and the cavity flow at the same time.…”

Section: Introductionmentioning

confidence: 99%

Numerical Study of Injected Jets into Supersonic Main Flow from a Porous Cavity

Kuniyoshi

Yaga

Teruya

et al. 2016

AEROSPACE TECHNOLOGY JAPAN

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This paper investigates jets injection into supersonic main flow, where the jets are surrounded by the porous cavity. This application of the porous cavity to the jet injection aims for the supersonic mixing enhancement. Supersonic mixing technique is important for scramjet engines to improve combustion efficiency. This method using porous cavity has been experimentally studied. However, it is difficult experimentally to measure the mixing efficiency, total pressure loss, and a circulation between the main flow and the cavity flow. Therefore, this paper numerically studies this flow field. In the calculation, Navier-Stokes equations were solved using AUSMDV scheme with 3rd order MUSCL scheme and the four stage Runge-Kutta scheme. Two cases, with the porous cavity and without the porous cavity, were calculated. As a result, a circulation between the main flow and the porous cavity is confirmed. Moreover, it is found that the bow shock wave and the dead water region of the jet were the important factors of this circulation. In addition to the circulation, total pressure loss due to the porous cavity was revealed.

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“…Generally, the passive case can occur in scramjet engines, pulse detonation engines, and shock tubes1213141516. For example, the fuel spray in supersonic cross air flow in scramjet engines is the passive case discussed above1718. While the active cases occur in the supersonic spray or droplets which generate the induced shock waves, which are induced by supersonic body1920.…”

mentioning

confidence: 99%

Experimental investigation on the characteristics of supersonic fuel spray and configurations of induced shock waves

Wang

2017

Sci Rep

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The macro characteristics and configurations of induced shock waves of the supersonic sprays are investigated by experimental methods. Visualization study of spray shape is carried out with the high-speed camera. The macro characteristics including spray tip penetration, velocity of spray tip and spray angle are analyzed. The configurations of shock waves are investigated by Schlieren technique. For supersonic sprays, the concept of spray front angle is presented. Effects of Mach number of spray on the spray front angle are investigated. The results show that the shape of spray tip is similar to blunt body when fuel spray is at transonic region. If spray entered the supersonic region, the oblique shock waves are induced instead of normal shock wave. With the velocity of spray increasing, the spray front angle and shock wave angle are increased. The tip region of the supersonic fuel spray is commonly formed a cone. Mean droplet diameter of fuel spray is measured using Malvern’s Spraytec. Then the mean droplet diameter results are compared with three popular empirical models (Hiroyasu’s, Varde’s and Merrigton’s model). It is found that the Merrigton’s model shows a relative good correlation between models and experimental results. Finally, exponent of injection velocity in the Merrigton’s model is fitted with experimental results.

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Experimental study of interaction between supersonic duct flow and jets surrounded by the porous cavity

Cited by 10 publications

References 14 publications

Study of Interaction between Supersonic Flow and Rods or Jets Surrounded by Porous Cavity

Study of Interaction between Supersonic Flow and Rods or Jets Surrounded by Porous Cavity

Numerical Study of Injected Jets into Supersonic Main Flow from a Porous Cavity

Experimental investigation on the characteristics of supersonic fuel spray and configurations of induced shock waves

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