Ali Arshad

Dr. Ali Arshad

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Research Focus & Metrics

Academic Career Length

13Years (2014-Present)

(Calculated once Scilit publication data is synced: current year − year of first publication + 1)

Representative Publications

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30 September 2016 in Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
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AAAli Arshad
Ali Arshad
QLQiushi Li
Qiushi Li
SLSimin Li
Simin Li
TPTianyu Pan
Tianyu Pan
Experimental investigations of the effect of inlet blade loading on the rotating stall inception process are carried out on a single-stage low-speed axial compressor. Temporal pressure signals from the six high response pressure transducers are used for the analysis. Pressure variations at the hub are especially recorded during the stall inception process. Inlet blade loading is altered by installing metallic meshed distortion screens at the rotor upstream. Three sets of experiments are performed for the comparison of results, i.e. uniform inlet flow, tip, and hub distortions, respectively. Regardless of the type of distortion introduced to the inflow, the compressor undergoes a performance drop, which is more severe in the hub distortion case. Under the uniform inlet flow condition, stall inception is caused by the modal type disturbance while the stall precursor switched to spike type due to the highly loaded blade tip. In the presence of high blade loading at the hub, spike disappeared and the compressor once again witnessed a modal type disturbance. Hub pressure fluctuations are observed throughout the process when the stall is caused by a modal wave while no disturbance is noticed at the hub in spike type stall inception. It is believed that the hub flow separation contributes to the modal type of stall inception phenomenon. Results are also supported by the recently developed signal processing techniques for the stall inception study.

23 February 2021 in International Journal of Aeronautical and Space Sciences
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AAAli Arshad
Ali Arshad
LRLucas Brandão Rodrigues
Lucas Brandão Rodrigues
ILIñigo Martínez López
Iñigo Martínez López

29 June 2021 in Journal of Mechanical Science and Technology
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AAAli Arshad
Ali Arshad
MAMohamed Akeel Fouzul Ameer
Mohamed Akeel Fouzul Ameer
OKOlegs Kovzels
Olegs Kovzels

5 June 2020 in Journal of Mechanical Science and Technology
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AAAli Arshad
Ali Arshad
SSSupun Samarasinghe
Supun Samarasinghe
FAF. A. M. Akeel
F. A. M. Akeel
AUAleksandrs Urbahs
Aleksandrs Urbahs

20 July 2022
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Conference Paper
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AAAli Arshad
Ali Arshad
CNChameera Nawanjana
Chameera Nawanjana
VKVadims Kovalcuks
Vadims Kovalcuks
This paper is the further implementation of the airfoil optimization methodology presented by authors in [1] and verified in [2]. The main focus of the study is to choose and optimize the airfoil for the wing section of the future 4R-UAV. 4R-UAV is a project funded by the Latvian Council of Science with the goal to create an innovative, aerodynamically improved, and eco-friendly UAV. Instead of conventional UAV wings comprising one airfoil, 4R-UAV wings will uniquely include two different airfoils, in order to achieve additional performance from the wingtip section. PSU94 airfoil was selected as the parent airfoil due to its application in wingtips. The optimization and CFD analysis demonstrated improved aerodynamic characteristics in the optimized airfoil (PSU94mod) compared to the original airfoil (PSU94). Optimized airfoil with improved aerodynamic characteristics will be used for the future 4R-UAV wing.

20 October 2021 in Archive of Mechanical Engineering
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AAAli Arshad
Ali Arshad
PCPengbo Cong
Pengbo Cong
AEAdham Awad Elsayed Elmenshawy
Adham Awad Elsayed Elmenshawy
Ilmars BlumbergsIlmars Blumbergs
Ilmars Blumbergs
This study aims to optimize the 2-cylinder in-line reciprocating compressor crankshaft. As the crankshaft is considered the "bulkiest" component of the reciprocating compressor, its weight reduction is the focus of current research for improved performance and lower cost. Therefore, achieving a lightweight crankshaft without compromising the mechanical properties is the core objective of this study. Computational analysis for the crankshaft design optimization was performed in the following steps: kinematic analysis, static analysis, fatigue analysis, topology analysis, and dynamic modal analysis. Material retention by employing topology optimization resulted in a significant amount of weight reduction. A weight reduction of approximately 13% of the original crankshaft was achieved. At the same time, design optimization results demonstrate improvement in the mechanical properties due to better stress concentration and distribution on the crankshaft. In addition, material retention would also contribute to the material cost reduction of the crankshaft. The exact 3D model of the optimized crankshaft with complete design features is the main outcome of this research. The optimization and stress analysis methodology developed in this study can be used in broader fields such as reciprocating compressors/engines, structures, piping, and aerospace industries.