Development and verification of a supersonic nozzle with a rectangular cross section at a Mach number of 2.8 for a scramjet model combustor

Yamaguchi, Tatsuya; Hizawa, Tomohiro; Taro, Ichikawa; Kudo, Taku; Hayakawa, Akihiro; Kobayashi, Haruo

doi:10.1299/jtst.2018jtst0032

Cited by 5 publications

(3 citation statements)

References 10 publications

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“…In this facility, high-pressure dry air generated by the compressor passes through a storage heater and rises to a maximum of about 870 K. Dry air passes through the stilling chamber and the supersonic nozzle, and an airflow of Mach number 2.8 is formed at the supersonic nozzle outlet. 7) A schematic of the test section perimeter is shown in Fig. 4.…”

Section: Supersonic Combustion Test Facilitymentioning

confidence: 99%

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Flow Field and Combustion Field Control Using Pylons Installed Upstream of a Cavity in Supersonic Flow

Hizawa

Yamaguchi

Murata

et al. 2020

Trans. Japan Soc. Aero. S Sci.

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This study clarifies the flow field and flame structure of a cavity flameholder with pylons in a Mach 2.8 airflow. A burned hydrogen/air gas mixture, rich in fuel, was injected in supersonic combustion experiments because self-ignition of fuel is difficult in a mainstream with low enthalpy. Experimental data were collected using the shadowgraph method, direct photography of the flame, wall pressure measurement, and OH Planer Laser-induced Fluorescence (OH-PLIF) measurement. In addition, three-dimensional numerical simulation was conducted. When one pylon was installed upstream of the jet flow, the penetration height of the jet increased, and a flame was formed in the mainstream center. When two pylons were installed at the front edge of the cavity, the flow field inside the cavity differed depending on the distance between the pylon and jet flow. The ignition and combustion of the burned-gas were suppressed at a close distance between the pylon and jet flow. For a large distance between the pylon and jet flow, the ignition and combustion of the burned-gas was enhanced. When hydrogen was injected as the main fuel from the upstream of the cavity, ignition of the main fuel was successful only for a large distance between the pylon and jet flow.

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Section: Supersonic Combustion Test Facilitymentioning

confidence: 99%

“…The mass flow rate of the mainstream was 255 g/s. The thickness of boundary layer was 5 mm, 7) which corresponds to 50% of the cavity depth and 29.4% of the pylon height. In this study, three experiments were carried out: cold flow, combustion, and main fuel injection.…”

Section: Experimental Conditionsmentioning

confidence: 99%

Flow Field and Combustion Field Control Using Pylons Installed Upstream of a Cavity in Supersonic Flow

Hizawa

Yamaguchi

Murata

et al. 2020

Trans. Japan Soc. Aero. S Sci.

Self Cite

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“…Yan and Liu (2006) studied the effect of static pressure ratio on the flow field and performance of the scramjet nozzle, and found out the change rule of nozzle performance under different external airflow conditions and different nozzle pressure ratios. Yamaguchi et al (2018) studied the influence of airstream total temperature on the Mach number distribution and stream angle distribution in the mainstream region of the scramjet nozzle by numerical methods. Wang et al (2012Wang et al ( , 2013 optimized the structure design of the scramjet nozzle under different Mach numbers and angles of attack for scramjet engine with high performance within the range of wide Mach number and angle of attack.…”

Section: Introductionmentioning

confidence: 99%

Combined effects of inlet airflow temperature and upper expansion angle on the performance of scramjet nozzle

Sun

Duan

et al. 2022

AEAT

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Purpose The purpose of this paper is to study the combined effects of inlet airflow temperature and the expansion angle of the upper expansion surface (upper expansion angle) on the performance of the scramjet nozzle. Design/methodology/approach The Spalart-Allmaras turbulence two-dimensional model of the nozzle is established for the study. The influence of inlet airflow temperature on the performance of the nozzle is analyzed by detecting the change of the wall pressure of the nozzle. The three angles are chosen for the upper expansion angle (βb) in the model: 8°, 12° and 16°. The temperature of inlet airflow is 600–1,800 K. Findings The study results show that when the βb is 8° and 16°, the wall pressure of the nozzle has a complicated and large fluctuation with the inlet airflow temperature, while the wall pressure has little change as βb is 12°; the thrust coefficient, pitching moment coefficient and lift coefficient of the nozzle fluctuate greatly with the increase of the inlet airflow temperature when βb is 8° and 16°, while the thrust coefficient, pitching moment coefficient and lift coefficient have little fluctuation as βb is 12°. Originality/value The study of the combined effects of the inlet airflow temperature and upper expansion angle on the performance of the scramjet nozzle can provide guidance for the design of scramjet nozzles.

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超音速流における気流境界層吸込みが流れ場および保炎性能へ与える影響

Norimatsu¹,

Wakita²,

Kudo³

et al. 2023

JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCE

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Development and verification of a supersonic nozzle with a rectangular cross section at a Mach number of 2.8 for a scramjet model combustor

Abstract: Development and verification of a supersonic nozzle with a rectangular cross section at a Mach number of 2.8 for a scramjet model combustor

Cited by 5 publications

References 10 publications

Flow Field and Combustion Field Control Using Pylons Installed Upstream of a Cavity in Supersonic Flow

Flow Field and Combustion Field Control Using Pylons Installed Upstream of a Cavity in Supersonic Flow

Combined effects of inlet airflow temperature and upper expansion angle on the performance of scramjet nozzle

超音速流における気流境界層吸込みが流れ場および保炎性能へ与える影響

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