CFD Validation and Flow Control of RAE-M2129 S-Duct Diffuser Using CREATETM-AV Kestrel Simulation Tools

Aref, Pooneh; Ghoreyshi, Mehdi; Jirasek, Adam; Mare, Luca di

doi:10.3390/aerospace5010031

Cited by 10 publications

(5 citation statements)

References 21 publications

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“…Aref et al [55] used the Q-criterion to explain the vortical structure formation in a RAE-M2129 air intake. A value of Q > 0= 0.1) is chosen in the present article to generate iso-surfaces for visualising the vortices generated by the synthetic jets during the blowing (Fig.…”

Section: Vorticity Dynamics and Q-criterionmentioning

confidence: 99%

Effects of Synthetic Jets on Swirl Inflow in a Variable- Geometry Twin Air-Intake

Yadav

Paul

Jain

et al. 2023

Preprint

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Air intakes are an integral part of contemporary passenger and military aircraft engines. Their impact on aerodynamic performance across the entire flight envelope is critical to aircraft flight safety, efficiency, and maneuverability, especially at high Mach numbers due to shock waves. The high demand for reduction in aircraft weight and size and enhancement of durability, comfort, and thermal and radar signatures compels researchers and engineers to explore new designs and develop efficient air intakes for high-performance aircraft engines. Although a number of studies on air intake have been conducted and reported in the open literature, there is little information available in the public domain on bifurcated twin air intakes using synthetic jet. As a result, the primary goal of this research is to use high-fidelity computational fluid dynamics modelling to investigate the effects of synthetic jets on swirl inflow variable geometry twin air intake aerodynamic performance over a range of Reynolds numbers. Some important parameters (distortion coefficient, non-uniformity index, swirl coefficient, and static and total pressure coefficients) were investigated. Both static and total pressure recovery have been increased at all swirl numbers. A significant decrease in distortion coefficient and swirl coefficient has also been achieved, reaching 67% in both cases. The reduction in the non-uniformity index is achieved by 62% for the controlled flow case. The findings show that the synthetic jets are effective in controlling the flow separation in the twin air-intakes and enhancing aerodynamic performance.

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Section: Vorticity Dynamics and Q-criterionmentioning

confidence: 99%

Effects of Synthetic Jets on Swirl Inflow in a Variable- Geometry Twin Air-Intake

Yadav

Paul

Jain

et al. 2023

Preprint

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show abstract

“…On the other hand, hybrid systems can have an additional benefit on performance parameters, compared to passive or active flow control alone [41]. As to mixing the mainstream and the secondary flow, some passive flow control technology, such as the vortex generator, shows great potential [42][43][44][45][46][47]. So, in this additional suction supplementary method research section, large mass flow suction control has been researched first, and then the combination of the micro-suction control and the vortex generator control.…”

Section: Additional Improvement For the Original Suction Controlmentioning

confidence: 99%

Suction Control of a Boundary Layer Ingestion Inlet

Liu,

Li,

Wang

et al. 2023

Aerospace

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This study presents a numerical investigation of suction control in an aggressive S-shaped air intake with large boundary ingestion. The results show that the variation of suction control parameters such as suction location, suction pipe diameter, and suction angle all have an impact on the effectiveness of the flow control. In general, further upstream suction, such as near the throat, is favorable for the decrease of the second flow intensity and the area of the low-energy fluid region at the exit of the S-shaped inlet. However, it is bad for the total pressure recovery and the circumferential total pressure uniform distribution. From the perspective of the uniformity of the total pressure distribution at the air intake exit, there is an optimal location for suction between the throat and the separation start point. A bigger suction pipe diameter brings better effects as the suction location and suction angle keep constant, due to more low-energy fluid being sucked out. But this doesn’t mean the largest mass flow suction results in the biggest improvement. Overall, sucking at the 1st bend, with suction angle and suction pipe diameter equaling 15 degrees and 12 mm, respectively, is the optimal suction scheme here. Since the change rule of the cross-section area along the centerline has not changed during suction control, the second flow and complex surface streamline at the air intake exit cannot be eliminated, though they can be decreased a lot with reasonable suction control. Similarly, owing to large boundary ingestion, the remarkable low-energy fluid region always exists despite the significant reduction of the separation and second flow, which is very different from the results of this kind of micro-suction executed in the non-BLI S-duct. To pursue a higher improvement, suction combined with vortex generator vanes has been further studied. Corresponding results analysis shows that the hybrid flow control method has great potential and should be investigated in detail in the future.

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“…both orientation of object with respect to the axis of the intake duct at the entry and angle of attack for aircraft was varied and simulated. Studies have been performed on estimating the trajectory of a store separation 1 and for understanding the flow inside an S-type diffuser duct [4][5][6][7] .…”

Section: Validationmentioning

confidence: 99%

“…As explained earlier, the design of the duct and the presence of the bird cause non-uniformity in the flow. This could affect the surge margin and lead to stall 7 .…”

Section: Variation In Engine Face Pressure Recovery Pattern For Variomentioning

confidence: 99%

Estimation of an Object Trajectory in an Intake Duct using Numerical Simulation

Aravinth¹,

Vidhyashankar²,

Abbas³

et al. 2020

Def. Sc. Jl.

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This research aims to study the trajectory of an object inside a serpentine duct of a gas turbine engine using computational fluid dynamics. The coupled implicit solver with 6-degree of freedom (6-DOF) and chimera mesh (Overset mesh) is used to track the object’s trajectory. Various object orientation and aircraft angle of attack (AoA) at a speed of Mach 0.3 is studied. This provides an understanding of the bird’s movement inside the duct that might cause damage to the engine components during takeoff and landing. It was observed that the combination of AoA and object orientation decide the length of the trajectory before impact. The object is found to travel the farther when the AoA is at -20o with object oriented at 0o and 45o.The object tends pitch and yield to the flow irrespective of its initial orientation and hence the aircraft angle of attack is a more predominant factor. The effect of pressure recovery due to AoA and object orientation is also presented. The recovery is found to be at its best for AoA of 0o irrespective of object orientation. This approach could be utilised for designing an intake duct that can limit the damage to engine components due to bird ingestion and simultaneously maintain good pressure recovery.

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CFD Validation and Flow Control of RAE-M2129 S-Duct Diffuser Using CREATETM-AV Kestrel Simulation Tools

Cited by 10 publications

References 21 publications

Effects of Synthetic Jets on Swirl Inflow in a Variable- Geometry Twin Air-Intake

Effects of Synthetic Jets on Swirl Inflow in a Variable- Geometry Twin Air-Intake

Suction Control of a Boundary Layer Ingestion Inlet

Estimation of an Object Trajectory in an Intake Duct using Numerical Simulation

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