Experimental Investigation of Inlet Distortion Effect on Performance of a Micro Gas Turbine

Naseri, Alireza; Sammak, Shervin; Boroomand, Masoud; Alihosseini, A. R.; Tousi, Abolghasem M.

doi:10.1115/1.4039057

Cited by 11 publications

(3 citation statements)

References 20 publications

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“…Generally, rig experiment with intake distortion device is a feasible method to study the intake characteristics of the engine (Naseri et al, 2018), but the cost is considerable. As for the numerical simulation methods, multiple segment parallel compressor model (Mazzawy, 1977) was extended to assess the effects of circumferential intake distortion on the the full engine (Yan.et al, 2015).…”

Section: Introductionmentioning

confidence: 99%

Research On Aero Engine Intake Distortion Based On 3D CFD Full Engine Simulation

Xu¹,

Wu²,

Liu³

et al. 2022

Proceedings of Global Power &Amp; Propulsion Society

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Intake distortions have large impacts on the performance of aero engines, and the investigations on intake distortions are in great need. Note that the component-decoupled simulations tend to break the constraint of power matching between compressor/turbine, which is key to understanding the underlying complicated process of intake distortions. In the present work, a steady-state three-dimensional component-coupled full engine simulation for a micro-turbojet engine, in which the aerodynamic/power matching is guaranteed, was employed to study the impacts of intake distortion on the engine operating state. The coupled/decoupled simulations are first applied to the states without intake distortion to reveal the advantage of coupled scheme. For intake distortion conditions, two typical adjustment strategies are adopted respectively to make the engine stable at rebalanced operating points, and the performance of the compressor in conjunction with the thrust of the full engine is analysed in detailed. The analytical results show that the matching problems induced by intake distortions are systematically demonstrated by the component-coupled scheme.

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Section: Introductionmentioning

confidence: 99%

Research On Aero Engine Intake Distortion Based On 3D CFD Full Engine Simulation

Xu¹,

Wu²,

Liu³

et al. 2022

Proceedings of Global Power &Amp; Propulsion Society

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“…They simulated the effects of inlet distortion on fan performance with DES (detached eddy simulation), and captured the flow structures of blades when encountering the distorted airflow. Naseri et al 17 used an air jet distortion generator to produce nonuniform inflow patterns. Tests were carried out with different circumferential distortion patterns and distortion intensities.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigations of mass-flux redistribution and performance prediction model on coupling effects of total pressure distortion-low Reynolds number in axial compressor

Zhu

Pan

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part A:

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Stability assessment is one of the important subjects in airworthiness certification. Many destabilizing factors can deteriorate the performance and stability margin of the compressor, and there are coupling effects between the external factors. This paper applies a computational method to investigate the coupling effects of total pressure distortion and low Reynolds number on an axial transonic compressor. The study was carried out on NASA stage 67, in which extensive open experimental data is available. Full annulus, steady, three-dimensional CFD has been used to study the coupling effects of 180-deg inlet distortion at low Reynolds number. The assessment of the stability margin loss under coupling effects by traditional methods results in a relative error of 27%. The local operating point of the rotor at different passages has been tracked, and the results reveal the reasons for the failure of model predictions. Combined with the analysis of the flow field under coupling effects, development solutions for the traditional model are proposed. The modifications to the model agree well with the calculation results. Finally, the improved model was validated. And according to the analysis of the rotor passage working points, the rationality of the model modification was verified.

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“…Sushanlal and Anish 8 conducted experimental and numerical studies on low aspect ratio turbine blades, and found that the interaction between the jet purge flow and the mainstream in the presence of upstream disturbance plays an important role in the evolution of secondary flows in the blade flow passage and outlet area. Salunkhe and Pradeep 9 studied axial flow fans without and with distorted inflow, and found that stall is caused by short-scale disturbance in the absence of distortion and reverse rotation inflow distortion, [10][11][12] while stall is caused by long-scale disturbance in the case of co-rotation inflow distortion. Sano et al 13 studied the flow instability in a vaned diffuser with an even number of blades.…”

Section: Introductionmentioning

confidence: 99%

Effect of motor intrusion on the aerodynamic performances and unsteady characteristics of internal flow of a volute-free centrifugal fan

Qin

Wang

He³

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part A:

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The volute-free centrifugal fans are widely used in air conditioning and ventilation applications due to their simple configuration and easy maintenance. The motor normally intrudes towards the fan interior from the rear disc to reduce the size and achieve better compatibility. The size and geometry of the motor affects the local flow field, which may have a serious impact on the aerodynamic performances of the fan. In this paper, we numerically investigated the effect of motor intrusion on the performances and internal flow characteristics of the volute-free centrifugal fan at different flow rates. The numerical results reveal that the internal flow field varies with the increasing of motor height at all flow rates. Under large flow rate, the height of motor has more obvious influence on the static pressure and static pressure efficiency of the fan; as the height of motor increases from 0 to 4 H/8, the two values decrease by 82.8% and 49.7%, respectively. The flow is more unstable which are manifested by the intensified velocity and pressure fluctuations. Therefore, the blocking effect of motor cannot be ignored and must be taken into account for the design the volute-free centrifugal fans.

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Experimental Investigation of Inlet Distortion Effect on Performance of a Micro Gas Turbine

Cited by 11 publications

References 20 publications

Research On Aero Engine Intake Distortion Based On 3D CFD Full Engine Simulation

Research On Aero Engine Intake Distortion Based On 3D CFD Full Engine Simulation

Numerical investigations of mass-flux redistribution and performance prediction model on coupling effects of total pressure distortion-low Reynolds number in axial compressor

Effect of motor intrusion on the aerodynamic performances and unsteady characteristics of internal flow of a volute-free centrifugal fan

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