Experimental and Numerical Study of Flow Structure and Liner Wall Temperature in Reverse Flow Combustor

Gao, Xuan; Duan, Fei; Lim, Seng Chuan; Yip, Mee Sin

doi:10.1615/ihtc15.gtb.009249

Cited by 6 publications

(14 citation statements)

References 19 publications

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“…The effective jet mixing also reduced the enormous emission of NO 2 at the combustor exit. Similar experimental analysis of the flow structure and the liner wall temperature was done by Gao et al 3,12 The results showed that the combustion process does not influence the flow pattern but increases the mean velocity magnitude significantly. The release of the enormous amount of energy due to the flaming of highly compressed air and the fuel mixture during the combustion phenomenon increased the flow Figure 1.…”

Section: Introductionsupporting

confidence: 65%

“…The illustrative diagram of a mini gas turbine engine (GTE). 3 kinetic energy which eventually increased the mean velocity.…”

Section: Introductionmentioning

confidence: 98%

“…By modifying the geometry of the liner wall, lower average temperature and more uniform temperature profiles were achieved at the combustor exit. Using the same turbulent model and combustion model, Gao et al 3 developed a CFD model of a 60periodic sector of these -30 mini GTE reverse flow combustor (Model A). By comparing the numerical results with the experimental results, 12 good agreement could be achieved in terms of the thrust and the temperature at the exit region.…”

Section: Introductionmentioning

confidence: 99%

“…By comparing the numerical results with the experimental results, 12 good agreement could be achieved in terms of the thrust and the temperature at the exit region. 3,12 The present study is focused on the laboratory based SR-30 mini GTE. The SR-30 mini GTE (as shown in Figure 1) is a small-scale air-breathing engine composed of an inlet nozzle, a single stage radial compressor, a reverse flow combustor, a single stage axial turbine and an exhaust nozzle.…”

Section: Introductionmentioning

confidence: 99%

“…While it is claimed that this engine is capable of producing thrust up to 200 N, it appears to be not always the case. 3,12 The experimental results showed that the achievable thrust was much lower than the claimed thrust and that the risk of compressor choking at higher r/min and mass flow rate could damage the engine. 12,16,17 Therefore, in order to improve the thrust performance of the mini GTE, the performance optimization of the SR-30 mini GTE was investigated by Wang and his colleagues 18 by means of combustor geometry modification.…”

Section: Introductionmentioning

confidence: 99%

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Effect of geometric modification on flow behaviour and performance of reverse flow combustor

Joy

Wang

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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Numerical investigation had been performed on the reverse flow combustor of a mini gas turbine engine so as to investigate the performance characteristics of the combustor by means of geometry modifications. In order to enhance the thrust performance of the reverse flow combustor, the baseline combustor (Model A) was previously modified by increasing its chamber volume by 15%, the fuel-air ratio (FAR) by 40% and by raising the injection point density to two (Model B). However, the thrust optimization of the baseline combustor resulted in high combustor exit temperature that could potentially damage the combustor liners. To rectify the adversity of high exit temperature, the combustor cooling effects were achieved by subsequently adding additional passage holes at the dilution zone of the Model B combustor so as to direct the incoming cold flow from the compressor exit towards the outgoing hot flow in the reverse flow combustor (Model C). The commercial software ANSYS Fluent 17.0 was adopted in this study and to solve the turbulence model, Reynolds Averaged Navier–Stokes methodology was adopted by employing standard k-ɛ turbulence model with standard wall function. A probability density function model was generated to introduce the combustion species and a discrete phase Model was employed to specify the kerosene fuel-based injector properties. The numerical results of Model A combustor were validated against the previous experimental results using grid convergence test. The numerical results were observed to be in good agreement with the experimental results. However, ineffective mixing was found to be a setback for the baseline combustor (Model A) indicating the need for combustor performance improvement. The comparative results of the revised combustor model (Model C) showed that better cooling effects at the combustor exit could be achieved by adding supplementary passage holes at the downstream of the combustor outer liner, respectively. The addition of dilution holes also resolved the issue of high pressure loss that was observed in Model A combustor with no significant change in the specific fuel consumption. The present paper confirms that the performance of the reverse flow combustor model could be affected by slight geometric modification. The performance characteristics of the combustor models are presented in terms of thrust, thrust-to-weight ratio, specific fuel consumption, pressure loss and pattern factor.

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Section: Introductionsupporting

confidence: 65%

“…The illustrative diagram of a mini gas turbine engine (GTE). 3 kinetic energy which eventually increased the mean velocity.…”

Section: Introductionmentioning

confidence: 98%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%