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UID:0-193@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20230308T133000

DTEND;TZID=Asia/Jerusalem:20230308T143000

DTSTAMP:20230308T113823Z

URL:https://aerospace.technion.ac.il/events/development-of-an-additive-man
 ufactured-micro-gas-turbine/

SUMMARY:Development of an Additive Manufactured Micro Gas Turbine
DESCRIPTION:Lecturer:Lukas Badum\n Faculty:Department of Aerospace Engineer
 ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla
 ssroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: https://techn
 ion.zoom.us/j/98367931661\n Abstract: \n Details: \n Ultra micro gas turbi
 nes for electric power generation below 1 kW are a viable replacement tech
 nology for lithium batteries in drones due to their high energy density. T
 o achieve high aerodynamic efficiency\, turbomachinery at centimeter scale
  and speeds up to 500\,000 rpm are required. Previous research showed that
  small-scale effects disqualify design practices applied to larger gas tur
 bines where subcomponents can be optimized isolated from system design. To
  appropriately capture component interdependencies of ultra micro gas turb
 ines\, an integrated design approach based on reduced order models is expe
 dient. Therefore\, a comprehensive engine design model including thermodyn
 amic cycle analysis\, compressor and turbine aerodynamic design\, combusto
 r design and high-speed generator design is presented. The design system i
 s adapted to capture additive manufacturing constraints of small-scale com
 ponents. In addition\, reduced order models for rotordynamics\, stress ana
 lysis and heat transfer are used to define the permissible design space.\n
 To validate the established set of reduced order models\, extensive experi
 mental investigations have been performed. The applicability of additive m
 anufacturing to micro gas turbines was investigated by performance compari
 son of two rotors manufactured with lithographic ceramic manufacturing (LC
 M) and selective laser sintering (SLS). To this end\, compressor performan
 ce maps were recorded at speeds up to 450\,000 rpm\, showing significant p
 erformance benefit for the LCM processed rotor and good agreement with the
  reduced order model. Additionally\, porous media combustion performance w
 as measured\, showing low achievable equivalence ratios but considerable r
 adiation heat losses. Furthermore\, a high-speed generator was developed a
 nd tested validating the reduced order modelling approach. Finally\, syste
 m performance testing is currently on-going on a preliminary micro turbine
  prototype integrating generator\, turbomachinery and combustor.
CATEGORIES:Seminars
LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng.

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