Numerical study of effect of compressor swirling flow on combustor design in a MTE

Mu, Yao; Wang, Chengdong; Liu, Cunxi; Liu, Fuqiang; Hu, Chunyan; Xu, Gang; Zhu, Jihong

doi:10.1007/s11630-017-0948-1

Cited by 6 publications

(2 citation statements)

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“…Bolger et al 2 numerically investigated and experimentally verified the flow profiles including the swirl angles at each stage of a multi stage compressor of a gas turbine engine. The effect on combustor exit pattern factor with a centrifugal compressor exit swirl in a micro turbine combustor was investigated by Yong et al 3 They predicted an increase in pattern factor and pressure loss for 2 different combustor design configurations. They concluded that the flow condition from compressors have an obvious influence on the design of combustor and more attention should be focused on this by the designers.…”

Section: Introductionmentioning

confidence: 99%

“…From the above literature review, it is clear that the compressor exit will always have some swirl [1][2][3][4] which cannot be neglected in analysing an actual combustor performance. 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.…”

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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Section: Introductionmentioning

confidence: 99%