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Experimental Test Rig Design and Testing of a Box-Bladed Propeller
2013 (English)Independent thesis Advanced level (professional degree), 20 credits / 30 HE creditsStudent thesis
Abstract [en]

This masters thesis is a dedicated nal work of an aerospace engineering eduction providedby Lule_a University of Technology. The work has been part of a design andexperimental project carried out during the fall of 2012 at GKN Engine System departmentin collaboration with the department of Fluid Dynamics at Chalmers Universityof Technology.The main objective has been to investigate the Box propeller concept feasibilityat an initial experimental stage. To reach the goal a custom propeller test rig havebeen essential to manufacture, which has been the head extensive work of the thesis.The iterative design process has concluded in two rig designs for scale-model testing; aSingle rotor Static test Rig (SSR) and a Dual rotor Dynamic test Rig (DDR). The SSRis of a less complicated design because of its single rotor arrangement and essentiallycommercial of the self instrumentation, which have made it possible to realize the designwithin the given time frame.The SSR process describes the path from rst drawings to CAD models, onwards tomanufacturing and assembling. The rst Box prop tests have now been performed in theSSR and reach over 100% of the specied speed range measuring net thrust, rotationalspeed together with additional motor parameters to derive propeller torque.The Box propellers were manufactured by two dierent rapid prototype methodsand plastic materials, where the initiating Box-blade design was developed by our thesisintern co worker. The Polyjet method and Verogrey 850 appeared to be the mostsuccessfully propeller sample. Resulting performance data captured gave a coecient ofthrust stagnating towards CT=0.31 with best accuracy of 2.7%.The work of the initiating SSR have given benets in practical knowledge usefulfor the DDR design since rig similarities such as drive systems is of identical type.The DDR involved more challenging considerations from requirement of contra rotatingarrangement and aerodynamic structure for low speed wind tunnel testing. After a thirddesign layout it have approached a adequate nal design. At the thesis closure phase theDDR have been delivered further to another thesis intern team who working on designimprovement and further rig realization

Place, publisher, year, edition, pages
2013. , 132 p.
Keyword [en]
Technology, Aerospace, propulsion, testing
Keyword [sv]
URN: urn:nbn:se:ltu:diva-57785Local ID: e69bc921-7a02-4077-a057-3b33ffb90618OAI: diva2:1031173
Subject / course
Student thesis, at least 30 credits
Educational program
Space Engineering, master's level
Validerat; 20131009 (global_studentproject_submitter)Available from: 2016-10-04 Created: 2016-10-04Bibliographically approved

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