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SUMMARY:Onset of unsteadiness in aero-engine intakes at incidence - Andrea
  Coschignano\, CUED
DTSTART:20161104T130000Z
DTEND:20161104T140000Z
UID:TALK68681@talks.cam.ac.uk
CONTACT:Akshath Sharma
DESCRIPTION:When travelling under high-thrust conditions\, such as during 
 take-off and climb\, the substantial mass flow demand by a turbofan engine
  is sufficient to accelerate the flow over the intake lip to supersonic co
 nditions. This faster-than sound flow pocket is terminated by a near-norma
 l shock wave. The adverse pressure gradient imposed by this disturbance on
  the boundary layer can cause the latter to separate\, introducing large s
 cale unsteadiness and an increase in viscous losses. These losses have a d
 irect negative repercussion on the overall engine efficiency as the total 
 pressure reaching the fan face is reduced. Moreover\, if the separated bou
 ndary layer does not reattach before the engine face\, the unsteadiness\, 
 characteristic of separated flows\, may increase the stress on the fan\, w
 hich can ultimately reduce component lives.\n\nTurbofan engines are design
 ed to operate over a wide range\, defined by inflow speed\, incidence and 
 engine demand. The consequences of increasing the last two parameters are 
 considered in the experimental investigation currently being undertaken at
  the Cambridge University Engineering Department. In particular\, the main
  interest is to assess the the onset and severity of any unsteady regimes.
 \n\nIn conclusion\, come along to see pretty pictures of shock waves!
LOCATION:LR11\, Cambridge University Engineering Department
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