Effect of swirl on the flow characteristics in the outer annulus of a prototype reverse-flow gas turbine combustor

Bharani, Sanjeev; Singh, Sadhna; Agrawal, D. P.

doi:10.1016/s0894-1777(01)00089-9

Cited by 15 publications

(6 citation statements)

References 6 publications

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“…Also, the pressure swirl-based fuel injection technique contributed significantly in the development of the toroidal vortex. Previous studies have reported that such flow behaviour often tends to bring uniformity in the flow pattern within the combustor especially at the combustor exit region 6,7 which was also observed in the present case. The velocity streamlines also show the presence of a large recirculating vortex in the secondary zone (at x/L = 0.4) of the Model A combustor.…”

Section: Results and Analysissupporting

confidence: 86%

“…Performance of the reverse flow combustor largely depends on the combustion chamber geometry and the control of the complex aerodynamics behaviour within the geometry. 1,2,4–6 In past, the initial designs of the combustor geometry predominantly relied on the experience, empirical analysis and test results. 1 However, with the advancement in technology, the study of the complex aerodynamics required effective means and measures for proper design and development of the combustors.…”

Section: Introductionmentioning

confidence: 99%

“…1 However, with the advancement in technology, the study of the complex aerodynamics required effective means and measures for proper design and development of the combustors. 4,5 Bharani et al 6 studied the effect of the swirl inflow on the flow characteristics of a reverse flow combustor. The results showed that the imposition of the swirl at the inlet affected the exit velocity profiles considerably when compared to the non-swirling inflow.…”

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: Results and Analysissupporting

confidence: 86%

Section: Introductionmentioning

confidence: 99%

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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“…The compact reaction zone causes the fuel evaporation distance to be shortened, which affects combustion efficiency and stability. The study of reverse-flow combustors has attracted the attention of many scholars [6][7][8][9][10][11][12][13][14]. For example, Bharani et al [9] showed that the flow characteristics and flow distribution of the jet holes of a reverse-flow combustor change when the flow characteristics of the outer annulus were altered.…”

Section: Introductionmentioning

confidence: 99%

“…The study of reverse-flow combustors has attracted the attention of many scholars [6][7][8][9][10][11][12][13][14]. For example, Bharani et al [9] showed that the flow characteristics and flow distribution of the jet holes of a reverse-flow combustor change when the flow characteristics of the outer annulus were altered. Additionally, the turbulence intensity level at the combustor outlet was not affected by the imposed inlet swirl.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation on Flow Characteristics of a Reverse-Flow Combustor

et al. 2022

International Journal of Aerospace Engineering

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Reverse-flow combustor is widely used for small engines to overcome high speed shaft whirling problem and to provide a low frontal area. An experimental investigation was carried out to research the flow field characteristics of a reverse-flow combustor in this paper. Different aerodynamic conditions were studied using PIV to reveal the characteristics of both the nonreacting and reacting flow fields. The structure of the nonreacting flow field in the central section shows similarity as the total pressure loss coefficient increases. The penetrating depth, jet angle, recirculation zone position, and the flow streamlines are similar, while the velocity value of the flow field increases. The structure of the reacting flow field on the central section is different from that of nonreacting flow field, but the variation trend of the reacting flow field under different pressure loss coefficient is similar to that of the nonreacting flow field. By examining the nonreacting and reacting flow fields under the same total pressure loss conditions, marked differences were observed in the primary zone close to the swirler outlet. The relative motion between fuel injection, airflow, and combustion affects the flow field in this zone. The velocity with combustion is faster than that of the nonreacting flow because of the increased temperature and heat release.

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Numerical Investigation of NOx Emission Reduction in Non-Premixed Lean Reverse-Flow Combustor in a Micro Gas Turbine Engine

Joy

Wang²,

Panisilvam³

et al. 2020

Emiss. Control Sci. Technol.

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Effect of swirl on the flow characteristics in the outer annulus of a prototype reverse-flow gas turbine combustor

Cited by 15 publications

References 6 publications

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

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

Experimental Investigation on Flow Characteristics of a Reverse-Flow Combustor

Numerical Investigation of NOx Emission Reduction in Non-Premixed Lean Reverse-Flow Combustor in a Micro Gas Turbine Engine

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