Analysis of Low Frequency Combustion Instabilities in a Laboratory Ramjet Combustor

Vigor Yang; Fred E.C. Culick

doi:10.1080/00102208608923839

Analysis of Low Frequency Combustion Instabilities in a Laboratory Ramjet Combustor

Vigor Yang, Fred E.C. Culick

College of Engineering

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

77 Citations (Scopus)

Abstract

Low frequency pressure oscillations in a research ramjet combustor have been studied using an integral technique. The analysis deals with plane one-dimensional oscillations with a two-dimensional mean flowfield. The flowfield in the dump combustor consists of three parts: a flow of reactants, a region containing combustion products, and a recirculation zone, separated by a flame sheet and a dividing streamline. Each region is treated separately and matched with the other. Acoustic fields in the inlet section and in the combustion chamber are coupled at the interface to determine the complex wave number characterizing the linear stability. Good agreement with experimental results has been demonstrated.

Original language	English
Pages (from-to)	1-25
Number of pages	25
Journal	Combustion science and technology
Volume	45
Issue number	1-2
DOIs	https://doi.org/10.1080/00102208608923839
Publication status	Published - 1986 Feb 1

All Science Journal Classification (ASJC) codes

General Chemistry
General Chemical Engineering
Fuel Technology
Energy Engineering and Power Technology
General Physics and Astronomy

Access to Document

10.1080/00102208608923839

Cite this

@article{6bd5d39c7b8c43d5b13d1b5de98edf5f,

title = "Analysis of Low Frequency Combustion Instabilities in a Laboratory Ramjet Combustor",

abstract = "Low frequency pressure oscillations in a research ramjet combustor have been studied using an integral technique. The analysis deals with plane one-dimensional oscillations with a two-dimensional mean flowfield. The flowfield in the dump combustor consists of three parts: a flow of reactants, a region containing combustion products, and a recirculation zone, separated by a flame sheet and a dividing streamline. Each region is treated separately and matched with the other. Acoustic fields in the inlet section and in the combustion chamber are coupled at the interface to determine the complex wave number characterizing the linear stability. Good agreement with experimental results has been demonstrated.",

author = "Vigor Yang and Culick, {Fred E.C.}",

note = "Funding Information: The authors are indebted to Drs. F. E. Marhle. E. E. Zukoski and D. A. Snii~hfo r several useful discussions. This work was supported parlly by Ihc California Inslitulc of Technology, and partly by the Air Force Office of Scientific Research, Grant No. AFOSR-80-0265.",

year = "1986",

month = feb,

day = "1",

doi = "10.1080/00102208608923839",

language = "English",

volume = "45",

pages = "1--25",

journal = "Combustion science and technology",

issn = "0010-2202",

publisher = "Taylor and Francis Ltd.",

number = "1-2",

}

TY - JOUR

T1 - Analysis of Low Frequency Combustion Instabilities in a Laboratory Ramjet Combustor

AU - Yang, Vigor

AU - Culick, Fred E.C.

N1 - Funding Information: The authors are indebted to Drs. F. E. Marhle. E. E. Zukoski and D. A. Snii~hfo r several useful discussions. This work was supported parlly by Ihc California Inslitulc of Technology, and partly by the Air Force Office of Scientific Research, Grant No. AFOSR-80-0265.

PY - 1986/2/1

Y1 - 1986/2/1

N2 - Low frequency pressure oscillations in a research ramjet combustor have been studied using an integral technique. The analysis deals with plane one-dimensional oscillations with a two-dimensional mean flowfield. The flowfield in the dump combustor consists of three parts: a flow of reactants, a region containing combustion products, and a recirculation zone, separated by a flame sheet and a dividing streamline. Each region is treated separately and matched with the other. Acoustic fields in the inlet section and in the combustion chamber are coupled at the interface to determine the complex wave number characterizing the linear stability. Good agreement with experimental results has been demonstrated.

AB - Low frequency pressure oscillations in a research ramjet combustor have been studied using an integral technique. The analysis deals with plane one-dimensional oscillations with a two-dimensional mean flowfield. The flowfield in the dump combustor consists of three parts: a flow of reactants, a region containing combustion products, and a recirculation zone, separated by a flame sheet and a dividing streamline. Each region is treated separately and matched with the other. Acoustic fields in the inlet section and in the combustion chamber are coupled at the interface to determine the complex wave number characterizing the linear stability. Good agreement with experimental results has been demonstrated.

UR - http://www.scopus.com/inward/record.url?scp=84950201932&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84950201932&partnerID=8YFLogxK

U2 - 10.1080/00102208608923839

DO - 10.1080/00102208608923839

M3 - Article

AN - SCOPUS:84950201932

SN - 0010-2202

VL - 45

SP - 1

EP - 25

JO - Combustion science and technology

JF - Combustion science and technology

IS - 1-2

ER -

Analysis of Low Frequency Combustion Instabilities in a Laboratory Ramjet Combustor

Abstract

All Science Journal Classification (ASJC) codes

Access to Document

Other files and links

Fingerprint

Cite this