A method of quasi-one dimensional numerical analysis for solid fuel scramjet combustor performance

Li He Wang; Zhi Wen Wu; Hong Wei Chi; Zhi Jun Wei; Ning Fei Wang

doi:10.7673/j.issn.1006-2793.2013.06.007

A method of quasi-one dimensional numerical analysis for solid fuel scramjet combustor performance

Li He Wang, Zhi Wen Wu^*, Hong Wei Chi, Zhi Jun Wei, Ning Fei Wang

^*Corresponding author for this work

School of Aerospace Engineering

Beijing Institute of Technology

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

5 Citations (Scopus)

Abstract

A solid fuel regression rate model was coupled to the quasi-one dimensional flow equations, and the flow parameters and the fuel regression rate were calculated together. The combustor diameter in next moment was obtained by plusing the local regression rate and the combustor diameter in previous moment. The unsteady flow problem of solid fuel scramjet combustion was decomposed into stationary problem every moment by solving the boundary conditions in each moment. This result provides a rapid methodology for performance prediction and design optimization of soild fuel scramjet combustor.

Original language	English
Pages (from-to)	742-747
Number of pages	6
Journal	Guti Huojian Jishu/Journal of Solid Rocket Technology
Volume	36
Issue number	6
DOIs	https://doi.org/10.7673/j.issn.1006-2793.2013.06.007
Publication status	Published - Dec 2013

Keywords

Combustor
Quasi-one dimensional flow
Regression rate
Scramjet
Solid fuel

Access to Document

10.7673/j.issn.1006-2793.2013.06.007

Cite this

@article{6870b44c25c44f6a822c5ad16d3eca2d,

title = "A method of quasi-one dimensional numerical analysis for solid fuel scramjet combustor performance",

abstract = "A solid fuel regression rate model was coupled to the quasi-one dimensional flow equations, and the flow parameters and the fuel regression rate were calculated together. The combustor diameter in next moment was obtained by plusing the local regression rate and the combustor diameter in previous moment. The unsteady flow problem of solid fuel scramjet combustion was decomposed into stationary problem every moment by solving the boundary conditions in each moment. This result provides a rapid methodology for performance prediction and design optimization of soild fuel scramjet combustor.",

keywords = "Combustor, Quasi-one dimensional flow, Regression rate, Scramjet, Solid fuel",

author = "Wang, {Li He} and Wu, {Zhi Wen} and Chi, {Hong Wei} and Wei, {Zhi Jun} and Wang, {Ning Fei}",

year = "2013",

month = dec,

doi = "10.7673/j.issn.1006-2793.2013.06.007",

language = "English",

volume = "36",

pages = "742--747",

journal = "Guti Huojian Jishu/Journal of Solid Rocket Technology",

issn = "1006-2793",

publisher = "Journal of Solid Rocket Technology",

number = "6",

}

TY - JOUR

T1 - A method of quasi-one dimensional numerical analysis for solid fuel scramjet combustor performance

AU - Wang, Li He

AU - Wu, Zhi Wen

AU - Chi, Hong Wei

AU - Wei, Zhi Jun

AU - Wang, Ning Fei

PY - 2013/12

Y1 - 2013/12

N2 - A solid fuel regression rate model was coupled to the quasi-one dimensional flow equations, and the flow parameters and the fuel regression rate were calculated together. The combustor diameter in next moment was obtained by plusing the local regression rate and the combustor diameter in previous moment. The unsteady flow problem of solid fuel scramjet combustion was decomposed into stationary problem every moment by solving the boundary conditions in each moment. This result provides a rapid methodology for performance prediction and design optimization of soild fuel scramjet combustor.

AB - A solid fuel regression rate model was coupled to the quasi-one dimensional flow equations, and the flow parameters and the fuel regression rate were calculated together. The combustor diameter in next moment was obtained by plusing the local regression rate and the combustor diameter in previous moment. The unsteady flow problem of solid fuel scramjet combustion was decomposed into stationary problem every moment by solving the boundary conditions in each moment. This result provides a rapid methodology for performance prediction and design optimization of soild fuel scramjet combustor.

KW - Combustor

KW - Quasi-one dimensional flow

KW - Regression rate

KW - Scramjet

KW - Solid fuel

UR - http://www.scopus.com/inward/record.url?scp=84893841211&partnerID=8YFLogxK

U2 - 10.7673/j.issn.1006-2793.2013.06.007

DO - 10.7673/j.issn.1006-2793.2013.06.007

M3 - Article

AN - SCOPUS:84893841211

SN - 1006-2793

VL - 36

SP - 742

EP - 747

JO - Guti Huojian Jishu/Journal of Solid Rocket Technology

JF - Guti Huojian Jishu/Journal of Solid Rocket Technology

IS - 6

ER -

A method of quasi-one dimensional numerical analysis for solid fuel scramjet combustor performance

Abstract

Keywords

Access to Document

Other files and links

Fingerprint

Cite this