Analysis on Combustion Instability Characteristics of Model Swirl Combustor With Gas Fuel

doi:10.12096/j.2096-4528.pgt.21093

Abstract

Abstract:

Combustion instability is easy to occur under lean combustion of gas turbine. Analyzing and predicting the characteristics of unstable combustion is of great significance to ensure the normal operation of combustion chamber. The flame describing function (FDF) of combustion chamber was obtained by numerical simulation, and the thermoacoustic instability characteristics of combustion chamber were predicted by combining the low-order thermoacoustic network model. Firstly, the operating conditions and main frequency of oscillating combustion were obtained through the self-excited oscillation experiment of model swirler combustor.Secondly, by using large eddy simulation (LES), the response characteristics of heat release rate of flame combustion under different inlet disturbances were obtained, and the FDF was fitted. Finally, the low-order thermoacoustic network model of the combustion chamber was established, and the instability characteristics of the combustion chamber were analyzed. The results show that the oscillation characteristics predicted by the model are consistent with the experimental data, indicating that the model can predict the combustion instability characteristics from the mechanism.

Key words: gas turbine combustor, combustion instability, thermoacoustic network model, large eddy simulation (LES), flame describing function (FDF)

CLC Number:

TK 16

Jiangang HAO, Wenming GONG, Yang DING, Danwei ZHENG, Yong LIU. Analysis on Combustion Instability Characteristics of Model Swirl Combustor With Gas Fuel[J]. Power Generation Technology, 2022, 43(6): 927-934.

Figures/Tables 10

Fig. 1 Layout diagram of combustion chamber system measurement

Fig. 2 Structures of combustor swirler and venturi

Tab. 1 Experimental conditions

工况	当量比
S1	0.79
S2	0.71
S3	0.59
S4	0.55
S5	0.47
S6	0.39
S7	0.35

Fig. 3 Fourier spectrum under operating conditions of S1 and S7

Fig. 4 Schematic diagram of variable section longitudinal acoustic elements

Fig. 5 Variation of heat release rate disturbance with velocity disturbance calculated by LES under different frequencies

Fig. 6 Predicted FDF results and fitting lines obtained by the 16th order fitting

Fig. 7 Schematic diagram of system model

Fig. 8 Contour map of eigenvalue location (growth rate and frequency) under different amplitude velocity disturbances

Fig. 9 Variation of system growth rate with velocity disturbance near 359 Hz

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