Numerical study on solid-fuel scramjet combustor with fuel-rich hot gas

Xiang Zhao; Zhi xun Xia; Bing Liu; Zhong Lv; Li kun Ma

doi:10.1016/j.ast.2017.12.024

Numerical study on solid-fuel scramjet combustor with fuel-rich hot gas

Xiang Zhao, Zhi xun Xia, Bing Liu, Zhong Lv, Li kun Ma

National University of Defense Technology

Research output: Contribution to journal › Article › peer-review

33 Scopus citations

Abstract

Solid-fuel scramjet combustor with cavity faces challenges of ignition and flame holding. In the current study, a novel concept, solid-fuel scramjet combustor with fuel-rich hot gas, is proposed. The Reynolds-average Navier–Stokes (RANS) equations coupled with the SST k−ω turbulence model and the second-order spatially accurate upwind scheme are employed to calculate its flow field. The feasibility of the solid-fuel scramjet combustor with fuel-rich hot gas is studied based on the validation of numerical method. The comparison of the performance is made between the combustor with fuel-rich gas and the combustor with cavity. Various parameters, namely excess air coefficient of gas generator and mass flow rate of fuel-rich gas, are studied, and their effects on the combustion efficiency, total pressure recovery and fuel regression rate are analyzed. This is the basic study for experiments of a solid-fuel scramjet combustor with fuel-rich hot gas.

Original language	English
Pages (from-to)	25-33
Number of pages	9
Journal	Aerospace Science and Technology
Volume	77
DOIs	https://doi.org/10.1016/j.ast.2017.12.024
State	Published - Jun 2018
Externally published	Yes

Keywords

Combustor performance
Fuel-rich hot gas
Solid-fuel scramjet

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10.1016/j.ast.2017.12.024

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title = "Numerical study on solid-fuel scramjet combustor with fuel-rich hot gas",

abstract = "Solid-fuel scramjet combustor with cavity faces challenges of ignition and flame holding. In the current study, a novel concept, solid-fuel scramjet combustor with fuel-rich hot gas, is proposed. The Reynolds-average Navier–Stokes (RANS) equations coupled with the SST k−ω turbulence model and the second-order spatially accurate upwind scheme are employed to calculate its flow field. The feasibility of the solid-fuel scramjet combustor with fuel-rich hot gas is studied based on the validation of numerical method. The comparison of the performance is made between the combustor with fuel-rich gas and the combustor with cavity. Various parameters, namely excess air coefficient of gas generator and mass flow rate of fuel-rich gas, are studied, and their effects on the combustion efficiency, total pressure recovery and fuel regression rate are analyzed. This is the basic study for experiments of a solid-fuel scramjet combustor with fuel-rich hot gas.",

keywords = "Combustor performance, Fuel-rich hot gas, Solid-fuel scramjet",

author = "Xiang Zhao and Xia, {Zhi xun} and Bing Liu and Zhong Lv and Ma, {Li kun}",

note = "Publisher Copyright: {\textcopyright} 2018 Elsevier Masson SAS",

year = "2018",

month = jun,

doi = "10.1016/j.ast.2017.12.024",

language = "英语",

volume = "77",

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T1 - Numerical study on solid-fuel scramjet combustor with fuel-rich hot gas

AU - Zhao, Xiang

AU - Xia, Zhi xun

AU - Liu, Bing

AU - Lv, Zhong

AU - Ma, Li kun

PY - 2018/6

Y1 - 2018/6

N2 - Solid-fuel scramjet combustor with cavity faces challenges of ignition and flame holding. In the current study, a novel concept, solid-fuel scramjet combustor with fuel-rich hot gas, is proposed. The Reynolds-average Navier–Stokes (RANS) equations coupled with the SST k−ω turbulence model and the second-order spatially accurate upwind scheme are employed to calculate its flow field. The feasibility of the solid-fuel scramjet combustor with fuel-rich hot gas is studied based on the validation of numerical method. The comparison of the performance is made between the combustor with fuel-rich gas and the combustor with cavity. Various parameters, namely excess air coefficient of gas generator and mass flow rate of fuel-rich gas, are studied, and their effects on the combustion efficiency, total pressure recovery and fuel regression rate are analyzed. This is the basic study for experiments of a solid-fuel scramjet combustor with fuel-rich hot gas.

AB - Solid-fuel scramjet combustor with cavity faces challenges of ignition and flame holding. In the current study, a novel concept, solid-fuel scramjet combustor with fuel-rich hot gas, is proposed. The Reynolds-average Navier–Stokes (RANS) equations coupled with the SST k−ω turbulence model and the second-order spatially accurate upwind scheme are employed to calculate its flow field. The feasibility of the solid-fuel scramjet combustor with fuel-rich hot gas is studied based on the validation of numerical method. The comparison of the performance is made between the combustor with fuel-rich gas and the combustor with cavity. Various parameters, namely excess air coefficient of gas generator and mass flow rate of fuel-rich gas, are studied, and their effects on the combustion efficiency, total pressure recovery and fuel regression rate are analyzed. This is the basic study for experiments of a solid-fuel scramjet combustor with fuel-rich hot gas.

KW - Combustor performance

KW - Fuel-rich hot gas

KW - Solid-fuel scramjet

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U2 - 10.1016/j.ast.2017.12.024

DO - 10.1016/j.ast.2017.12.024

M3 - 文章

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SN - 1270-9638

VL - 77

SP - 25

EP - 33

JO - Aerospace Science and Technology

JF - Aerospace Science and Technology

ER -

Numerical study on solid-fuel scramjet combustor with fuel-rich hot gas

Abstract

Keywords

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