航空发动机燃烧室热声不稳定的预设性能控制

doi:10.7527/S1000-6893.2022.28182

Abstract

Abstract:

To reduce NO _x emissions in aero-engine combustion chambers， lean premixed pre-vaporized combustion technology is widely used， leading to more frequent combustion instability. The energy of aero-engine combustion instability comes from the combustion of the propellant， with thermoacoustic instability being the main form of combustion instability. To suppress the thermoacoustic instability， the influence of flame combustion response on the system is firstly considered based on the Culick model， and the mathematical model of thermoacoustic instability with state delay is derived. Based on the derived model， the influence of the convection time from fuel injection to heat release from combustion on the stability of the thermoacoustic system is then explored， a back-stepping active control method with prescribed performance designed， and the upper bound of the convection time obtained under the premise of ensuring the prescribed performance of the system. Both theoretical analysis and simulation results verify that the active control method can make the pressure oscillation of the thermoacoustic instability system converge asymptotically and satisfy the prescribed performance with time-delay robustness.

Key words: thermoacoustic instability, state delay, prescribed performance control, backstepping, robust control

CLC Number:

V239

Xiao MENG, Dan MA, Hongjun LIN, Chao CHEN. Prescribed performance control of thermoacoustic instability in aero-engine combustion chambers[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(17): 128182-128182.

Figures/Tables 6

Table 1

System parameters［15］

参数	数值
$D 11$	-0.01
$E 11$	-0.005
比热比 $γ ¯$	1.23
燃烧室长度 $L$ /m	0.762
燃烧室横截面积 $S$ /m²	0.013
燃烧室平均压力 $p ¯$ /atm	5.5

Table 1

Fig.1

Fig.2

Fig.3

Fig.4

Fig.5

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Prescribed performance control of thermoacoustic instability in aero-engine combustion chambers

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