ANSYS-CFX Research Papers - Academia.edu (original) (raw)

Gasturbinesusedinaircraftareoperatedinavarietyofenvironmentsrangingfromarctictodesertconditions.Desertareaspresentaparticularchallengetogasturbineoperationbecauseofparticulatematterthatcanbeingestedintotheengine,whentheengineoperatesneargroundlevel.Predictionsofparticulateladenflowswiththeaccountofturbulentviscousfluidsarecomplexphysicsandcanbeapproachedintwoways–Onewayortwowaycoupling.

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- Turbomachinery Aerodynamics, Axial flow compressors, ANSYS-CFX, Blades

The objective of this paper is to model and simulate a wing powered with a distributed propulsion system at both take-off and cruise conditions. The thesis demonstrates the advantages of Distributed Electric Propulsion (DEP) by studying the flow around a wing. MATLAB was used to generate the wing external dimensions using the wing design parameters (aspect ratio, taper ratio, twist angle). The modelling of the wing was performed using ANSYS Workbench and the one of the high-lift propellers (HPs) and Tip Propeller (TP) in SolidWorks before importing the propellers from SolidWorks to ANSYS and attaching them at the front of the leading edge of the wing at equal distances. The propellers in this thesis are designed using the blade radius with constant twist angle from root to tip using the information collected through a literature review, as the optimization of the propellers alone is not the main focus of this project. The project scope is only limited to the way through which they are utilized in a configuration that improves the wing aerodynamic performance. After creating the meshes and applying the required setups, four simulations where conducted in this project through a step by step analysis that first started with a simulation of the wing alone. After adding the propellers, the wing with all HPs and TP was simulated in deployed stationary configuration at take-off conditions. The lift value increased and the drag decreased as a result of this improvement. Once more, the wing with the same configuration was simulated by assigning rotational velocities to the propellers. The results showed a great improvement in the lift and drag values. A last simulation was performed at cruise conditions where all the HPs were folded in the nacelles and the wing was simulated with the TP being in stationary configuration. Additional simulations were later performed to improve the reliability from the results obtained after each of the simulations. Moreover, the plots of the pressure, velocity and streamlines provided relevant information about the aerodynamic interference between the wing and the propellers. The slipstreams created by the propellers and their effects on the wing were also discussed. The results concluded that significant aerodynamic improvements can be achieved in DEP Technology by installing a propeller at the wingtip and HPs at the leading edge of the wing at appropriate locations.

- by Nassam Assouma
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- Aerodynamics, Optimization techniques, Matlab, Nasa

Radial inflow turbines have established their place in small power units and turbochargers which usually operate under highly unsteady gas flows. The present numerical study is an aerodynamic characterization of the steady and unsteady gas flows through the components of a twin-entry radial turbine with an asymmetrical volute, with an insight on the volute/rotor interactions and the effects of pulsatile flow. The details of the flow structures were possible to obtain by considering the full rotor blades simulations. Examination of the both sides of volute has revealed much more energy conversion with respect to the shroud side and the tongue influence is clearly depicted by a low momentum due to mixing till a tangential position. The rotor flow is characterized by intense secondary flows provoking migration of low energy fluid from hub to shroud and interacting with tip leakage flow. Spectral analys is of the pressure fluctuations recorded at different interfaces has revealed high unsteadiness which may be characterized by a space-time periodic behaviour and described by a double Fourier decomposition. This has led to the determination of different pressure fluctuation frequencies arising during the turbine working time and prevailing modes and their originating sources.

This study presents the aerodynamic behaviours of a twin-entry radial inflow turbine under steady and transient con-ditions. The influence of the volute tongue is depicted by a low momentum wake propagating toward the rotor entry, but
its effect does not extend beyond a circumferential position of 60

, and more total pressure loss is revealed with respect to
the hub side. The transient simulations carried out at different operating conditions and Fast Fourier Transform analysis of
static pressure fluctuations induced by the components’ interactions have revealed a space-time periodic behaviour which
has been described by a double Fourier decomposition. The flow simulations considering the two sides subject to both
non-pulsatile and pulsatile flows conditions have revealed the existing rotor and tongue potential effects and interaction
effects the rotor and volute, in addition to the circumferential and spanwise flow non-uniformities at the volute exit, which
are more accentuated with a pulsatile flow at inlet. The results of Fast Fourier Transform analysis of temporal pressure
fluctuations at the inter-space depict an unsteady behaviour related to the pulsatile frequencies which are characterised by
high amplitudes. On the other hand, the spatial pressure fluctuations for the non-pulsatile and pulsatile flows conditions
seem to have the same dominant modes since Fast Fourier Transform analysis was carried out at a fixed instant.

- by CERDOUN Mahfoudh and +1
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- CFD Analysis, Turbomachinery, ANSYS-CFX, Radial Inflow Turbine

According to the high costs of structured packings, efficient and high-capacity packings can be provided with a precise and optimal design at the minimum expenses. In structured packings, the pressure drop is one of the critical factors in calculating the optimal diameter of the tower. In the present research, two phase pressure drop in SulzerBX structured packing was optaincd by computational fluid dynamics and compared with experimental data. The relative error was 9.1%. Furthermore, the amount of maximum pressure drop was 833.7 Pascal per meter at gas and liquid velocities of 0.899 and 0.0298 m/s, respectively. In addition, the minimum pressure drop was 25.1 Pascal per meter at gas and liquid velocities of 0.341 and 0.0298, respectively. Compared with conventional packings the pressure drop in perforated plates illustrated a 7% reduction. To the best of the authors' knowledge, there is no reported study on this packing using perforated plates by computational fluid dynamics. This study aims to investigate the influence of packing plates holes on two phase pressure drop.
Keywords: Structured Packing , Computational Fluid Dynamics , Pressure Drop , Sulzer_BX

- by ali shahmohammadi
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- Distillation columns, ASPEN PLUS, ANSYS-CFX, Adsorbent

An increase in passenger numbers had resulted in larger planes that were hard to fit in most airports in the world, which, according to Boeing, fit in the E category of the International Civil Aviation Organization (ICAO) specifications. To be able to fly to these airports wingspan of the planes must be under 65 m. This paper looked into optimizing the A380 to be able to fly with a 65 m wingspan by utilizing the bi-wing and flying wing design. Due to the limitations of the Ansys student version of the Ansys software and the accuracy of the modeling of the A380's wings, the lift and drag forces for the wings were affected. However, it was found out that while both the bi-wing and flying wing designs offered higher lift than the wing utilized in the A380, the flying wing design had better performance.

- by Thu Y Win
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- Aerospace Engineering, Aerodynamics, ANSYS CFX, Ansys