Optimizing combustion performance in a solid rocket scramjet engine

Jie Liu; Ning fei Wang; Jian Wang; Zi yan Li

doi:10.1016/j.ast.2019.105560

Optimizing combustion performance in a solid rocket scramjet engine

Jie Liu^*, Ning fei Wang, Jian Wang, Zi yan Li

^*Corresponding author for this work

School of Aerospace Engineering

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

43 Citations (Scopus)

Abstract

To enhance combustion efficiency of a boron-based propellant solid rocket scramjet (SRS) engine, this study attempted a new organization scheme combining cavity and pneumatic slope. To optimize the proposed system, a series of numerical simulations were performed, and through orthogonal design and single factor analysis, the key factors were determined. The developed two-phase flow simulation has been verified by the full-scale ground test, given an error within 10%. The results show that for both combustion efficiency and total pressure recovery, the influence of gas injection mode is much greater than the ratio of the length to depth of the concave cavity as well as the cavity depth. And the combustion performance has proved to be optimized via the enlarged low speed area near the cavity and the strengthened particles reflux.

Original language	English
Article number	105560
Journal	Aerospace Science and Technology
Volume	99
DOIs	https://doi.org/10.1016/j.ast.2019.105560
Publication status	Published - Apr 2020

Keywords

Combustion efficiency
Orthogonal design
Solid propellant
Solid rocket scramjet
Two-phase flow

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10.1016/j.ast.2019.105560

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Liu, J., Wang, N. F., Wang, J., & Li, Z. Y. (2020). Optimizing combustion performance in a solid rocket scramjet engine. Aerospace Science and Technology, 99, Article 105560. https://doi.org/10.1016/j.ast.2019.105560

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title = "Optimizing combustion performance in a solid rocket scramjet engine",

abstract = "To enhance combustion efficiency of a boron-based propellant solid rocket scramjet (SRS) engine, this study attempted a new organization scheme combining cavity and pneumatic slope. To optimize the proposed system, a series of numerical simulations were performed, and through orthogonal design and single factor analysis, the key factors were determined. The developed two-phase flow simulation has been verified by the full-scale ground test, given an error within 10%. The results show that for both combustion efficiency and total pressure recovery, the influence of gas injection mode is much greater than the ratio of the length to depth of the concave cavity as well as the cavity depth. And the combustion performance has proved to be optimized via the enlarged low speed area near the cavity and the strengthened particles reflux.",

keywords = "Combustion efficiency, Orthogonal design, Solid propellant, Solid rocket scramjet, Two-phase flow",

author = "Jie Liu and Wang, {Ning fei} and Jian Wang and Li, {Zi yan}",

note = "Publisher Copyright: {\textcopyright} 2019 Elsevier Masson SAS",

year = "2020",

month = apr,

doi = "10.1016/j.ast.2019.105560",

language = "English",

volume = "99",

journal = "Aerospace Science and Technology",

issn = "1270-9638",

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T1 - Optimizing combustion performance in a solid rocket scramjet engine

AU - Liu, Jie

AU - Wang, Ning fei

AU - Wang, Jian

AU - Li, Zi yan

PY - 2020/4

Y1 - 2020/4

N2 - To enhance combustion efficiency of a boron-based propellant solid rocket scramjet (SRS) engine, this study attempted a new organization scheme combining cavity and pneumatic slope. To optimize the proposed system, a series of numerical simulations were performed, and through orthogonal design and single factor analysis, the key factors were determined. The developed two-phase flow simulation has been verified by the full-scale ground test, given an error within 10%. The results show that for both combustion efficiency and total pressure recovery, the influence of gas injection mode is much greater than the ratio of the length to depth of the concave cavity as well as the cavity depth. And the combustion performance has proved to be optimized via the enlarged low speed area near the cavity and the strengthened particles reflux.

AB - To enhance combustion efficiency of a boron-based propellant solid rocket scramjet (SRS) engine, this study attempted a new organization scheme combining cavity and pneumatic slope. To optimize the proposed system, a series of numerical simulations were performed, and through orthogonal design and single factor analysis, the key factors were determined. The developed two-phase flow simulation has been verified by the full-scale ground test, given an error within 10%. The results show that for both combustion efficiency and total pressure recovery, the influence of gas injection mode is much greater than the ratio of the length to depth of the concave cavity as well as the cavity depth. And the combustion performance has proved to be optimized via the enlarged low speed area near the cavity and the strengthened particles reflux.

KW - Combustion efficiency

KW - Orthogonal design

KW - Solid propellant

KW - Solid rocket scramjet

KW - Two-phase flow

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JO - Aerospace Science and Technology

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Optimizing combustion performance in a solid rocket scramjet engine

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Keywords

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