Design and Analytical Evaluation of a Swirler-Injector System

Mousemi, Arash; Mosadegh, Sepehr; Khademi, Alireza; Sorrentino, Giancarlo

doi:10.11159/jffhmt.2021.019

Cited by 1 publication

(2 citation statements)

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“…Mathematical simulations by Mazaheri and Shakeri [33] show that changes in combustor geometry can lead to a reduction in nitric oxide emissions. Furthermore, according to Mousemi et al [19] and Saboohi et al [20,21], it is possible to design an optimized combustor in terms of NOx and CO reduction by tuning the coupling between the design factors of combustor components. The basic sizing of the combustor and the calculation of NOx and CO emissions are shown in the flowchart of Figure 5a in the form of a subroutine.…”

Section: Stages Of Takeoff and Landing Cycle Subsonic Aircraft Engine Thrust Onmentioning

confidence: 99%

“…Several researchers have suggested the design theory of the SAC. Mousemi et al [19] presented an integrated approach for designing a combustor liner by applying a coupling between a swirl injector and a swirler. Saboohi et al [20] organized an automated 2D conceptual design algorithm of combustor considering the shape and size of the snout part located in front of the dome of the primary zone and recirculation zone.…”

Section: Introductionmentioning

confidence: 99%

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One-Dimensional Analysis of Double Annular Combustor for Reducing Harmful Emissions

Jeong¹,

Ahn²

2021

Energies

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The number of aircraft flights worldwide has increased steadily since the introduction of air transportation to the public. Accordingly, environmental issues caused by the exhaust gases of aircraft engines have emerged. In particular, international organizations have crafted emission regulations since gases exhausted during takeoff and landing have been identified as the direct cause of air pollution near airports. Nitrogen oxides (NOx) produced at high combustion temperatures and carbon monoxide (CO) due to incomplete combustion affect the performance of the combustion chamber. Therefore, annular combustors comprising two annular zones have been developed to reduce the emissions of these two substances, which occur under different conditions. Parameters that should be considered when modifying a conventional single annular (SAC) to a double annular combustor (DAC) are discussed herein. In this paper, an optimization algorithm for obtaining the main design parameters of the DAC is presented to minimize NOx and CO emissions and an operation solution for reducing carbon monoxide emission is identified. A thermodynamic model of a high-bypass turbofan engine (PS-90A) is used to establish the inlet and outlet conditions of the combustor. Analysis results show that NOx emissions can be effectively reduced by adjusting the design parameters and CO emissions can be significantly decreased by partially turning off the fuel supply based on the engine cycle.

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Section: Stages Of Takeoff and Landing Cycle Subsonic Aircraft Engine Thrust Onmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%