Effects of Combustion Chamber Geometry Deviations Upon Exit Temperature Profiles for Populations With Varied Service Limitations

Kotzer, Clayton; LaViolette, M.; Allan, W.; Asghar, Asad

doi:10.1115/1.4002845

Cited by 5 publications

(6 citation statements)

References 11 publications

(21 reference statements)

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“…For strong flow penetration, the size of the passage holes was increased by 1.15 times the size of the largest passage hole in the secondary zone in order to achieve better flow penetration effect without damaging the combustor liner walls. 8 The number of the passage holes per row was kept similar to that in the secondary zone and was evenly distributed circumferentially across the combustor geometry. The schematic diagram of the passage holes situated at the combustor outer liner is shown in Figure 11.…”

Section: Results and Analysismentioning

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 Analysismentioning

confidence: 99%

“…Kotzer et al. 8 investigated the effects of the combustor chamber geometry on the exit temperature profiles. The results showed that small deviations in the combustor geometry could influence the temperature profile significantly, reflecting the strong sensitivity of internal flow pattern on the temperature distribution.…”

Section: Introductionmentioning

confidence: 99%

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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“…They observed that relatively small deviations in the spray pattern from a nominal distribution can translate into dramatic changes in the exit temperature distributions. Clayton et al 6 experimentally investigated the effect of combustion chamber geometry in the dilution zone on the exit temperature fields by using thermocouple rakes. They demonstrated that the pattern factor increases with the increase in the dilution zone geometry distortion.…”

Section: Introductionmentioning

confidence: 99%

“…The effect of various combustor design parameters such as fuel nozzle spray patterns, dilution hole geometry, fuel type, swirl number and different fuel injection methods on combustor exit pattern factor has been reported by authors. [5][6][7][8][9] The effect of combustor swirling flow (swirl number) on recirculation zone, flame speed, flame area, primary jet flow and flare geometry was reported by previous studies. [10][11][12][13] The effect of combustor inlet swirl angle (compressor discharge) on pattern factor and pressure loss still remains a gap which is addressed in this work.…”

Section: Introductionmentioning

confidence: 99%

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Influence of inlet swirl on pattern factor and pressure loss in an aero engine combustor

Rao

Prasad

Babu

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part C:

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The effect of compressor exit swirl angle (θsw) at the intake of an aero engine combustor on the exit temperature non-uniformity (pattern factor) and combustor total pressure loss is investigated. Experiments are conducted in the engine test rig, measuring the gas temperature and pressure at the inlet and exit planes of the combustor. These parameters are measured at distinct locations along the circumferential and radial directions in the engine test facility. Simulations are carried out using RANS based turbulence modeling and reacting flow approach with Ansys CFX commercial code. The predicted results are validated with experimental data at 5° swirl angle. The swirl angle at the combustor intake is further varied from 0° to 15° and 4 cases (0°, 5°, 10° and 15°) has been considered to predict the effect on the combustor pattern factor and pressure loss. The changes in the flow structure inside the combustion chamber for all these 4 cases are reported in detail. The pattern factor varies from 0.34 to 0.49 as swirl angle changes from 0° to 15°. The lowest pattern factor of 0.34 occurs at 10° swirl angle. However a linear increase in combustor total pressure loss from 5.85% to 6.53% is predicted with the change in swirl angle from 0° to 15°.

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Investigation on unsteady formation and evolution of high-temperature zone in a staged swirl combustor

Li,

Zhang,

et al. 2024

Applied Thermal Engineering

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Effects of Combustion Chamber Geometry Deviations Upon Exit Temperature Profiles for Populations With Varied Service Limitations

Cited by 5 publications

References 11 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

Influence of inlet swirl on pattern factor and pressure loss in an aero engine combustor

Investigation on unsteady formation and evolution of high-temperature zone in a staged swirl combustor

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