A research program to investigate helicopter downwash and frigate airwake interaction has been initiated using a statistically robust experimental program featuring design of experiments. Engineering analysis of the helicopter/frigate interface is complicated by the fact that two flow fields become inherently coupled as a separation distance decreases. The work presented was performed in the Old Dominion University 7 × 8 ft Low-Speed Wind Tunnel using a simplified 1/50-scale frigate waterline model and traverse-mounted powered rotor with thrust measurement capability. Particle image velocimetry velocity surveys were acquired with rotor thrust coefficient measurements at coincident locations to help understand the underlying flow physics.
NomenclatureC T thrust coefficient, T /(ρ(πR 2 )(V Tip ) 2 ) D rotor diameter (2R), m f frequency of vortex shedding, Hz S t Strouhal number, S t = f V ∞ /D T thrust, kgf V ∞ freestream velocity, m/s V Tip speed of the rotor tip, m/s x longitudinal distance from the base of a hangar, m y lateral distance from the base of a hangar, m z vertical distance above a landing deck/ground plane, m ρ air density, kg/m 3 rotational speed of the rotor, ad/s
Günümüzde yeni teknolojilerle birlikte ortaya çıkan Endüstri 4.0 devrimi dijitalleşmeyi hızlandırmaktadır. Bununla birlikte doğuştan itibaren internet ile büyüyen ve "Z kuşağı" olarak tanımlanan dijital nesilin eğitim talepleri de ortaya çıkan yeni fırsatlarla birlikte hızlı bir şekilde dönüşüme uğramaktadır. Z kuşağı, dijital öğeleri metinsel öğelere tercih etmekte, zamandan ve mekândan bağımsız olarak kişisel öğrenme istemektedir. Dijitalleşme ve Z kuşağının öğrenme tercihleri, her alanda olduğu gibi eğitimde de dönüşümü zorunlu hale getirmektedir. Özellikle son dönemlerde ortaya çıkan sanal gerçeklik (SG), artırılmış gerçeklik (AG) ve karma gerçeklik (KG) uygulamaları ile eğitimler daha etkin ve uygun maliyetle verilmektedir. Bu çalışmada, Endüstri 4.0 ile ortaya çıkan teknolojilerden özellikle AG uygulamalarının eğitimde ve özellikle de uçak bakım sahasındaki uygulamaları incelenmiştir. Son bölümde ise Sivil Havacılık Genel Müdürlüğü (SHGM) tanınmış okul isterleri çerçevesinde uçak bakım eğitiminde AG uygulamalarının kullanılabilirliği değerlendirilmiş ve uçak bakım alanındaki AG uygulama eğitimlerinin standartlarının belirlenerek sertifikasyon çalışmalarının başlatılması konusunda çalıştay yapılması önerilmiştir.
The main purpose of this study is to experimentally analyze the exergetic performance of a small-scale turbojet engine that can be used in unmanned aerial vehicles (UAVs) when different blend ratios of kerosene with diesel are necessary, like in extraordinary situations. Comparative analysis was performed to understand the effects of the use of various diesel rates on the jet engine’s performance. To maintain air operations when refueling is required, easy-reachable fuels can help for short but important periods. In cases when there is a need for the use of a quick-reachable fuel in war conditions, diesel may be a suitable fuel. The UAV turbojet engine consists of a radial compressor, an annular combustion chamber, an axial turbine, and a propelling nozzle. The compressor, combustion chamber, turbine, and nozzle were evaluated by using the exergy analysis method. The performance parameters to evaluate the turbojet engine components were specific fuel consumption, thrust, overall exergy efficiency, and air-to-fuel ratio. The turbojet engine was operated at different throttle settings to monitor the changes in the performance parameters. As a result of using different kerosene and diesel fuel blends at different throttle settings, it was observed that the findings were consistent. Generally, the maximum exergy efficiencies took place in the turbine except for the full throttle settings. The minimum exergy efficiencies belonged to the nozzle. It was observed that irrespective of which fuel blend was used, thrust specific fuel consumption values decreased as the throttle setting increased. On the other hand, thrust values, overall exergy efficiencies, and air-to-fuel ratios had an increasing trend as the throttle setting was increased.
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