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UID:0-277@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20210203T163000

DTEND;TZID=Asia/Jerusalem:20210203T173000

DTSTAMP:20230525T070642Z

URL:https://aerospace.technion.ac.il/events/preliminary-design-tool-for-op
 timal-effusion-cooling-holes-diameter-and-spacing/

SUMMARY:A Preliminary Design Tool for Optimal Effusion Cooling Holes Diamet
 er and Spacing
DESCRIPTION:Lecturer:Yair Lange\n Faculty:Department of Aerospace Engineeri
 ng\n Institute:Technion – Israel Institute of Technology\n Location:http
 s://technion.zoom.us/j/91723342653\n Zoom: \n Abstract: \n Details: \n Mic
 ro gas turbines generally employ uncooled turbine blades and their thrust 
 is limited by the maximum allowable gas temperature. A miniature cooling s
 cheme embodying effusion cooling may significantly enable higher thrust-to
 -weight ratios. Modern manufacturing capabilities are improving and enabli
 ng affordable solutions for innovative cooling techniques. In scope of thi
 s work\, a quasi 1D effusion cooling model is developed. The model conside
 rs the internal duct and effusion holes flow\, conjugate heat transfer and
  the external film coverage. Solid temperature is allowed to vary both in 
 direction of metal shell thickness and the stream-wise direction of the ex
 ternal gas flow. The model is validated against three-dimensional computat
 ional fluid dynamics and it is shown that the model can predict main featu
 res of the combined internal and effusion cooling in gas turbine blades. A
 s a next step\, design optimization is conducted towards minimizing coolan
 t mass flow rate while retaining solid temperature at a prescribed value. 
 Finally\, this coolant modeling scheme is implemented for micro gas turbin
 e blades in order to find the preferable effusion holes pitch and diameter
  distributions. This approach offers a potential to decouple turbine aerod
 ynamics\, which dictate the core\, from the thermal management provided by
  the shell. Therefore\, as the shell and core manufacturing processes are 
 also separated\, the design timeline and development costs of the turbine 
 stage can be reduced.\n&nbsp\;\n\nZoom Meeting 
CATEGORIES:Seminars
LOCATION:https://technion.zoom.us/j/91723342653

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