Technical Brief

Influence of Turbulent Combustion Noise on the Decrement Estimates of Gas Oscillations

[+] Author and Article Information
V. Karmalita

Private Consultant,
255 Boylan Avenue,
Dorval, QC H9S5J7, Canada
e-mail: karmalita@videotron.ca

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF HEAT TRANSFER. Manuscript received August 29, 2017; final manuscript received May 3, 2018; published online June 7, 2018. Editor: Portonovo S. Ayyaswamy.

J. Heat Transfer 140(10), 104502 (Jun 07, 2018) (3 pages) Paper No: HT-17-1515; doi: 10.1115/1.4040255 History: Received August 29, 2017; Revised May 03, 2018

This paper deals with the autoregression method to determine the logarithmic decrement and natural frequency of gas oscillations in a combustion chamber. The proposed approach to quantify the impact of combustion noise on the estimates of oscillation decrement is based on a linear model of the vibrating combustion phenomena. An application of the proposed approach for afterburner tests is presented as well.

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Mile, J. H. , 2009, “ Time Delay Analysis of Turbofan Engine Direct and Indirect Combustion Noise Sources,” J. Propul. Power, 25(1), pp. 218–227. [CrossRef]
Ducruix, S. , Schuller, T. , Candel, S. , and Durox, D. , 2003, “ Combustion Dynamics and Instabilities: Elementary Coupling and Driving Mechanisms,” J. Propul. Power, 19(5), pp. 722–734. [CrossRef]
Karmalita, V. A. , and Furletov, V. I. , 1987, “ Autoregression Method for Determining the Decrement and Frequency of the Natural Oscillations of a Gas in a Combustion Chamber,” Combust. Explos. Shock Waves, 23(6), pp. 694–700. [CrossRef]
Box, G. E. P. , Jenkins, G. M. , and Reinsel, G. C. , 2008, Time Series Analysis: Forecasting and Control, 4th ed., Wiley, Hoboken, NJ. [PubMed] [PubMed]


Grahic Jump Location
Fig. 1

Spectra of processes X, E, Z

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Fig. 2

Amplitude-frequency characteristic of band-pass FIR-filter (q = 128)

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Fig. 3

Spectrum of gas pressure oscillations in the afterburner

Grahic Jump Location
Fig. 4

Spectrum of gas pressure oscillations after flight speed increase



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