Analysis of the flow structure in a supersonic channel with cavity

Мұқаба

Дәйексөз келтіру

Толық мәтін

Ашық рұқсат Ашық рұқсат
Рұқсат жабық Рұқсат берілді
Рұқсат жабық Тек жазылушылар үшін

Аннотация

The results of numerical study of supersonic flow in a channel with cavity are given. The calculated oscillation spectra are analyzed using the fast Fourier transform. Two types of oscillatory modes can be distinguished in the resulting periodic self-oscillatory regime. The first type of the modes corresponds to acoustic vibrations caused by the passage of sound waves along the cavity and calculated using the modified Rossiter formula. The second type of the modes corresponds to the frequencies of flow-rate oscillations caused by mass transfer between the cavity and the external flow. It is shown that the flow structure is modified when fuel is supplied in front of the cavity. Active combustion occurs in the layer of mixing fuel and oxygen from air. The flow pattern demonstrates the onset of Kelvin–Helmholtz instability on the interface between the main flow and the reacted gas. It is shown that an increase in the supplied fuel pressure leads to a decrease in the oscillation frequency and an increase in the characteristic size of oscillations.

Толық мәтін

Рұқсат жабық

Авторлар туралы

R. Seleznev

Dukhov Automatics Research Institute; Ishlinsky Institute for Problems in Mechanics of the Russian Academy of Sciences

Хат алмасуға жауапты Автор.
Email: rkseleznev@gmail.com
Ресей, Moscow; Moscow

Әдебиет тізімі

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Қосымша файлдар

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Әрекет
1. JATS XML
Жүктеу
2. Fig. 1. Combustion chamber diagram. Arrows indicate the directions of the main air flow, fuel feed locations and two pressure measurement zones.

Жүктеу (104KB)
Метадеректер
3. Fig. 2. Distribution of the Mach number in the computational domain at the moment of external supersonic flow into the cavity region. The animation file of the Mach number field at successive moments of time is presented in the appendix Fig_02_Mach_no_H2.avi.

Жүктеу (111KB)
Метадеректер
4. Fig. 3. Distribution of pressure in the computational domain at successive moments. The animation file of the pressure field at successive moments is presented in the appendix Fig_03_Pres_no_H2.avi.

Жүктеу (559KB)
Метадеректер
5. Fig. 4. Spectrum of pressure oscillations (a) inside the cavern (b) on the chamber stack at a distance of 59 cm from the beginning of the chamber. Green dotted lines indicate the frequencies of flow oscillations (842, 1685, 2527, 3370, 4212, 5055 Hz). Blue dotted line with a dot indicates the frequencies of Rossiter acoustic oscillations (1569, 3661, 5754 Hz).

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Метадеректер
6. Fig. 5. Temperature distribution in the calculation domain for different fuel supply pressures: (a) Pinj = 0.5 MPa, (b) Pinj = 1 MPa, (c) Pinj = 1.5 MPa. The animation file of the calculated temperature field for the fuel supply pressure Pinj = 1 MPa is presented in the appendix Fig_05_Temp _H2.avi.

Жүктеу (292KB)
Метадеректер
7. Fig. 6. Distribution of the Mach number in the computational domain for different fuel supply pressures: (a) Pinj = 0.5 MPa, (b) Pinj = 1 MPa, (c) Pinj = 1.5 MPa. The animation file of the calculated Mach number for the fuel supply pressure Pinj = 1 MPa is presented in the appendix Fig_05_Mach _H2.avi.

Жүктеу (176KB)
Метадеректер
8. Fig. 7. Time dependence of dimensionless pressure sensor readings (x = 59 cm) for different fuel supply pressures: (a) Pinj = 0.5 MPa, (b) Pinj = 1 MPa, (c) Pinj = 1.5 MPa.

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