Computational investigation of multi-cavity fuel injection on hydrogen mixing at supersonic combustion chamber

Li, Zhixiong; Manh, Tran Dinh; Gerdroodbary, M. Barzegar; Nam, Nguyễn Đăng; Moradi, Rasoul; Babazadeh, Houman

doi:10.1016/j.ijhydene.2020.01.096

Cited by 86 publications

(11 citation statements)

References 59 publications

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“…Thus total pressure loss in a single-strut combustor is 14% lower than that of a combustor with a multi strut. [50][51][52][53][54][55][56][57][58][59][60]…”

Section: Discussionmentioning

confidence: 99%

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Numerical investigations on the performance of a multistrut hydrogen injector in a scramjet combustor

2021

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This study aims at investigating the effect of a multistrut-based hydrogen injector in a scramjet combustor underreacting case. The numerical analysis is carried out using two-dimensional Reynolds-averaged Navier-Stokes equations with the Shear Stress Transport k − ω turbulence model in contention to comprehend the flow physics during scramjet combustion. The three major parameters, such as the shock wave pattern, wall pressures, and static temperature across the combustor, are validated with the reported experimental results. The results comply with the range, indicating that the adopted simulation method for single strut injection can be extended for other investigations. It is noticed that with multistrut injectors, as hydrogen jet pressure increases in the supersonic flow field, the jet penetration rate in the lateral direction of the flow and the total pressure loss as compared with the baseline injection pressure conditions has increased. The supersonic flow characteristics are determined based on the flow properties, combustion efficiency, mixing efficiency, and total pressure loss. Compared with the single-strut output of a scramjet combustor, multistruts inclusion increased the combustion efficiency by almost 18%, the mixing efficiency attained the maximum with 16% fewer lengths. The total pressure loss in single-strut is 14% lower than that of multistrut.

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“…Thus total pressure loss in a single-strut combustor is 14% lower than that of a combustor with a multi strut. [50][51][52][53][54][55][56][57][58][59][60]…”

Section: Discussionmentioning

confidence: 99%

“…From the above discussion, it is evident that this paper's numerical approach is confident to investigate the reacting flow studies of the strut-based scramjet combustor. 35,[56][57][58]…”

Section: Validation Of the Numerical Modelmentioning

confidence: 99%

Numerical investigations on the performance of a multistrut hydrogen injector in a scramjet combustor

2021

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“…To improve the thermal performance of the spike, several modifications had been performed and examined on the spike. injection of opposing and lateral jets is also done to decrease the heat rate nearby the nose of the main body 25 , 26 . This model is efficient due to the formation of multiple circulations which deflect the incoming flow from the main body and reduce the strength of shark interaction on the shoulder of the main body to develop this mother injection of a coolant cast could help and improve the cooling performance of this technique 27 – 30 .…”

Section: Introductionmentioning

confidence: 99%

Influence of coolant multi-jets on heat reduction of nose cone with blunt spike at hypersonic flow

Ghanbari

Maddah

Alinejad

2022

Sci Rep

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The importance of the cooling system for the design of the forebody of high-speed vehicles is significant due to severe aerodynamic heating at hypersonic flight. In the present study, injection of multi and single-coolant jets on the thermal performance of forebody design of nose cone with the cut spike is thoroughly investigated at hypersonic flow. A three-dimensional model of the blunt cone is presented for computational investigations of proposed jet and spike configurations. Injection of two coolant gasses (Helium and carbon dioxide) into the cooling system of the nose cone with a blunt spike is investigated. Three locations for both opposing and lateral jets are compared to find the efficient jet location. Our results indicate that a single lateral jet injected from the tip of the spike is more efficient for heat reduction. A comparison of the multiple injection system also shows that the heat reduction of the helium gas is about 15% more than CO2 jets.

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“…[13][14][15][16] Meanwhile, several books and papers have been published in this field of study. [17][18][19][20][21][22] The film injection, cavity technique, and porthole injections are the most conventional approaches for the fuel injection system. Some of the scholars concentrated on the application of the strut as a shock producer or free stream deflector for mixing augmentation of the fuel jets.…”

Section: Introductionmentioning

confidence: 99%

“…To investigate the scramjet engine, numerous techniques and models have been proposed and studied by scientists 13‐16 . Meanwhile, several books and papers have been published in this field of study 17‐22 . The film injection, cavity technique, and porthole injections are the most conventional approaches for the fuel injection system.…”

Section: Introductionmentioning

confidence: 99%

Computational investigation of multi hydrogen jets at inclined supersonic flow

2020

Self Cite

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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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Computational investigation of multi-cavity fuel injection on hydrogen mixing at supersonic combustion chamber

Cited by 86 publications

References 59 publications

Numerical investigations on the performance of a multistrut hydrogen injector in a scramjet combustor

Numerical investigations on the performance of a multistrut hydrogen injector in a scramjet combustor

Influence of coolant multi-jets on heat reduction of nose cone with blunt spike at hypersonic flow

Computational investigation of multi hydrogen jets at inclined supersonic flow

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