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UID:0-383@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20180502T163000

DTEND;TZID=Asia/Jerusalem:20180502T173000

DTSTAMP:20230527T140734Z

URL:https://aerospace.technion.ac.il/events/continuous-closed-loop-transon
 ic-linear-cascade-for-aero-thermal-performance-studies-in-micro-turbomachi
 nery/

SUMMARY:Continuous Closed-Loop Transonic Linear Cascade for Aero-Thermal Pe
 rformance Studies in Micro-Turbomachinery
DESCRIPTION:Lecturer:Eli Yakirevich\n Faculty:Department of Aerospace Engin
 eering\n Institute:Technion – Israel Institute of Technology\n Location:
 Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstrac
 t: \n Details: \n The present work summarizes the design process of a new 
 continuous closed-loop hot transonic linear cascade. The facility features
  fully modular design which is intended to serve as a test bench for axial
  micro-turbomachinery components in independently varying Mach and Reynold
 s numbers ranges of 0 - 1.3 and 2⋅104 - 6⋅105 respectively. Moreover\,
  for preserving heat transfer characteristics of the hot gas section\, the
  gas to solid temperature ratio (up to 2) is retained. This operational en
 vironment has not been sufficiently addressed in prior art\, although it i
 s critical for the future development of ultra-efficient high power or thr
 ust devices.\nIn order to alleviate the dimension specific challenges asso
 ciated with micro-turbomachinery\, the facility is designed in a highly ve
 rsatile manner\, and can easily accommodate different geometric configurat
 ions (pitch\, ±20° stagger angle\, ±20° incidence angle)\, absent of a
 ny alterations to the test section. Owing to the quick swap design\, the v
 ane geometry can be easily replaced without manufacturing or re-assembly o
 f other components. Flow periodicity is achieved by the inlet boundary lay
 er suction and independently adjustable tailboard mechanisms. Enabling tes
 t-aided design capability for micro gas turbine manufacturers\, aero-therm
 al performance of various advanced geometries can be assessed in engine re
 levant environments.
CATEGORIES:Seminars
LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng.

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