简介：Anumericalinvestigationonover-shroud&inter-shroudleakageflowhasbeencarriedouttoexploretheunderneathflowphysicsatthestageofshroudedLowPressure(LP)turbine.ComparedwiththeNointer-Shroudgap'sLeakageflowModel(NSLM)andWithinter-Shroudgap'sLeakageflowModel(WSLM),theaerodynamiccharacteristicsandtheheattransferperformancehavebeenstudied.Throughtheaerodynamicpointofview,itisconcludedthatduetothepressuredifferencebetweentherotor'spassageandtheover-shroudcavity,inthestream-wisedirection,flowstructurehasbeenmodified,andtheinter-shroudleakageflowmayevencauseflowseparationinthevicinityofthebladepassage'sthroat.Inthecircumferentialdirection,separationflowsappearovertherotor'sshroudsurface(upperplatformoftheshroud).Meanwhile,fromthepointofviewofheattransfer,furtherprovisiononcontourmapsofthenon-dimensionalNusseltnumberrevealsthatthereattachmentofleakageflowwouldenhancetheheattransferratesandendangertherotor'slabyrinthfinsovertheshroud.However,duetothelimitedamountofinter-shroudleakageflow(currentcomputationalmodel),temperaturedistributionvariationalongthebladesurface(neartherotor'stipsection)seemstohaveonlyminorinsignificantdifferences.Attheendofthepaper,theauthorputsforwardsomerecommendationsforthepurposeoffuturesuccessfulturbinedesign.