The　first-stage　rotor　squealer　tip　is　a　key　area　in　the　gas　turbine　for　both　aerodynamic　performance　and　heat　transfer　characteristics,　which　should　be　carefully　designed.　However,　there　are　many　uncertainties　in　the　geometrical　parameters　and　operating　environment　of　the　blade　tip,　which　makes　the　actual　aerothermal　performance　of　the　turbine　blade　tip　significantly　deviate　from　the　design　value　in　actual　use　progress.　The　heat　transfer　characteristics　and　aerodynamic　performance　uncertainty　quantification　analysis　system　of　the　turbine　blade　squealer　tip　was　established.　The　non-embedded　polynomial　chaos　expansion　method,　integrated　with　Smolyak　Sparse　grid,　Sobol　Indic　technology　for　the　uncertainty　quantification　analysis　system　was　developed.　It　was　investigated　and　quantified　that　the　effects　of　the　tip　clearance,　mainstream　inlet　total　temperature　and　blowing　ratio　uncertainty　on　the　aerothermal　performance　of　blade　squealer　tip.　The　uncertainty　analysis　results　show　that　heat　flux　of　squealer　tip　QTip　basically　conforms　to　the　normal　distribution　when　considering　the　uncertainty　of　tip　clearance,　mainstream　inlet　total　temperature　and　blowing　ratio.　The　statistical　mean　value　of　the　QTip　increased　by　13.56%　relative　to　the　designed　value　and　the　probability　of　10%　deviation　from　the　designed　value　is　as　high　as　65.68%.　The　heat　flux　of　squealer　tip　leading　edge　is　more　sensitive　to　uncertainty　input　by　comparison　to　the　trailing　edge.　The　uncertainty　of　the　heat　flux　on　the　blade　surface　QBlade　near　the　leading　edge　region　is　obviously　larger　than　that　of　the　trailing　edge　area.　The　minor　deviations　of　the　total　pressure　loss　coefficients　at　the　squealer　tip　within　0~80%　axial　chord　regions　is　observed　considering　the　tip　clearance,　mainstream　inlet　total　temperature　and　blowing　ratio　uncertainty　inputs.　However,　the　uncertainty　error　of　the　total　pressure　loss　coefficient　at　the　squealer　tip　after　the　80%　axial　chord　regions　would　reach　about　50%.　The　sensitive　analysis　results　show　that　the　mainstream　inlet　total　temperature　is　the　dominant　variable　in　the　uncertainty　of　the　blade　heat　transfer　performance,　and　its　contribution　to　the　uncertainty　of　QTip　and　QBlade　is　93.87%　and　98.32%,　respectively.　The　uncertainty　of　the　aerodynamic　performance　of　the　squealer　tip　is　completely　dominated　by　the　tip　clearance,　and　the　uncertainty　variance　of　it　to　the　tip　total　pressure　loss　coefficient　obtained　as　86.44%.　Compared　with　the　main　effect,　the　influence　of　the　second-order　interaction　effect　among　the　variables　studied　on　the　squealer　tip　aerothermal　performance　is　almost　negligible.　©　2022,　Editorial　Department　of　Journal　of　Propulsion　Technology.　All　right　reserved.