Characteristics of transverse hydrogen jet in presence of multi air jets within scramjet combustor

Gerdroodbary, M. Barzegar; Fallah, Keivan; Pourmirzaagha, Hamoon

doi:10.1016/j.actaastro.2016.11.041

Cited by 150 publications

(20 citation statements)

References 40 publications

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“…Based on Gerdroodbary et al (2017b), the wake flow of the delta wing VG can be divided into two regions as shown in Fig. 6a (Wang et al, 2012).…”

Section: Experimental Results Of Vg Wake Flowmentioning

confidence: 99%

“…This shows that the flow features are extremely complex. However, the mixing rate is enhanced apparently because of the presence of the air jets in the supersonic combustor (Gerdroodbary et al, 2017b;Hassanvand et al, 2018). In addition, approaches such as importing slope, pylon, strut, and cavity have been put forward and compared in the Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering) ISSN 1673-565X (Print); ISSN 1862-1775 (Online) www.jzus.zju.edu.cn; www.springerlink.com E-mail: jzus@zju.edu.cn literature (Lee, 2012;Sujith et al, 2013;Moradi et al, 2018).…”

Section: Introductionmentioning

confidence: 99%

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Experimental investigation on flow characteristics of a transverse jet with an upstream vortex generator

Zhao

Liang

Zhang

et al. 2020

J. Zhejiang Univ. Sci. A

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This paper aims at probing the flow characteristics of a jet in supersonic crossflow (JISC) by installing a vortex generator (VG) upstream of the jet orifice. Nanoparticle planar laser scattering (NPLS) and stereo-particle image velocimetry (SPIV) technologies were employed to observe the flowfield, and three cases were designed for comparison. CASE0 stands for JISC without passive VG. In CASE1 and CASE2, VG is installed at 20 mm and 80 mm upstream away from the jet orifice, respectively. Transient flow structures show that two flow modes exist when the VG wake interacts with the JISC. In CASE1, vortices are induced from both sides of the jet plume because of the VG wake. This leads to a complex streamwise vortex system. Penetration and lateral diffusion are enhanced. In CASE2, intermittent large-scale eddies in the VG wake cause large streamwise vortices at the windward side of the jet. The penetration depth is also enhanced while the lateral diffusion is restrained. In addition, experimental results show that the penetration depth is approximately 8.5% higher in CASE1 than that in CASE0, and the lateral diffusion is larger by about 17.0%. In CASE2, the penetration is increased by about 26.2%, while the lateral diffusion is enhanced by just 0.5%.

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“…Based on Gerdroodbary et al (2017b), the wake flow of the delta wing VG can be divided into two regions as shown in Fig. 6a (Wang et al, 2012).…”

Section: Experimental Results Of Vg Wake Flowmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Experimental investigation on flow characteristics of a transverse jet with an upstream vortex generator

Zhao

Liang

Zhang

et al. 2020

J. Zhejiang Univ. Sci. A

View full text Add to dashboard Cite

show abstract

“…Due to the requirements of hypersonic aircrafts, ordinary fuel cannot meet the high specific impulse required by hypersonic aircrafts when the Mach number is relatively high and low-temperature fuel such as liquid hydrogen is needed as the propulsion fuel for ramjets [74]. Low-temperature fuel storage, fuel transfer, heat transfer, and the selection of fuel are all sub-areas designed in the low-temperature systems.…”

Section: Low-temperature Systemsmentioning

confidence: 99%

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

et al. 2019

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Combined-cycle engine is a potential propulsion system for hypersonic aircraft. To ensure long-term, normal operation of combined-cycle engine under the harsh environment of high thermal load, it is of great significance to study the thermal protection and management of the propulsion system. In this study, the objective and development status of thermal protection and thermal management systems for the combined-cycle propulsion system were described. The latest research progresses of thermal protection, thermal barrier coating, and thermal management system of the combined-cycle propulsion system were summarized. Moreover, the problems and shortcoming in current researches were summarized. In addition, a prospect for the future development of thermal protection and management of the combined-cycle propulsion system was presented, pointing out a direction of great value and vital research significance to thermal protection and management of the combined-cycle propulsion system.

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“…[35][36][37][38][39][40] The key advantage of the computational approach is low cost and informative results about details of flow feature. [41][42][43][44][45] Thus, several codes and software are developed for the simulation of compressible flow inside the scramjet engine. [45][46][47][48] The advance in the current commercial software easily enables the researchers to investigate different fuel mixing systems at supersonic free steam.…”

Section: Introductionmentioning

confidence: 99%

“…In this technique, fuel is injected through the nozzle as a cross-flow jet in the presence of the high Mach stream. 43,44 To increase the efficiency of this method, a single jet is substituted by multi microjets to amplify the fuel jet interface with supersonic air stream and, consequently, mixing efficiency of the fuel jet increase in the downstream of the jets. In the multi-jet systems, the row of jets is produced, and the gap of these jets augments the mixing efficiency.…”

Section: Introductionmentioning

confidence: 99%

Computational investigation of multi hydrogen jets at inclined supersonic flow

2020

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Summary Scramjet design is directly associated with the fuel mixing inside the combustor. In this study, the influences of the free stream angle on the fuel mixing zone of eight microjets are fully investigated. This study mainly tries to disclose the importance of the fuel jet interaction with a supersonic free stream on penetration and distribution of hydrogen jets. The effects of jet paces and different free stream angles are fully examined in this work. For the computational study, CFD numerical method is applied to obtain the fuel jet structure at supersonic cross‐flow. RANS equations with SST turbulence scheme is employed for the simulation of our model. Our simulations show that a positive angle of supersonic incoming flow is effective for the uniform expansion of the fuel mixing zone inside the combustor. According to our findings, increasing the angles of the free stream declines the mixing zone when the fuel jet interaction of the last jets with main stream decreases. Our results indicate that mixing efficiency of ‐20° is about 30% more than other angles.

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Characteristics of transverse hydrogen jet in presence of multi air jets within scramjet combustor

Cited by 150 publications

References 40 publications

Experimental investigation on flow characteristics of a transverse jet with an upstream vortex generator

Experimental investigation on flow characteristics of a transverse jet with an upstream vortex generator

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

Computational investigation of multi hydrogen jets at inclined supersonic flow

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