An　improved　efficient　uncertainty　quantification　(UQ)　analysis　framework　is　proposed　by　the　combination　of　sparse　polynomial　chaos　expansion　(PCE)　and　universal　Kriging　(UK)　metamodel　to　obtain　the　surrogate　model　(UK-PCE).　Moreover,　a　challenging　analytical　test　function　and　an　engineering　test　are　considered　to　investigate　the　response　performance　of　UK-PCE　method.　The　results　show　that　the　UK-PCE　method　reduces　the　computational　cost　by　more　than　70%　in　comparison　to　the　typical　PCE　method.　Then　this　method　was　applied　to　the　UQ　of　the　aerodynamic　and　heat　transfer　performance　of　GE-E3　rotor　blade　squealer　tip.　Additionally,　a　series　of　uncertainty　quantities　visualization　methods　based　on　the　data　mining　method,　parallel　computing　method,　and　Delaunay　triangulation　method　is　proposed　to　reveal　more　enlightening　uncertainty　phenomena　in　the　actual　operation.　The　results　of　UQ　show　that　under　the　influence　of　uncertain　inputs,　the　leakage　flow　rate　and　downstream　entropy　increase　will　be　significantly　increased.　The　statistical　average　of　tip　heat　flux　has　increased　by　8.56%　relative　to　the　design　value,　and　the　probability　of　it　deviating　from　the　design　value　by　10%　is　as　high　as　43.27%.　In　addition,　the　three-dimensional　tip　heat　flux　deviation　distributions　calculated　by　the　proposed　uncertainty　quantities　visualization　method　reveal　a　coupling　of　the　hot　corrosion　and　thermal　fatigue　of　the　squealer　tip.　It　is　also　indicated　that　under　the　influence　of　the　uncertain　inputs,　there　is　a　marked　increase　in　blade　tip　flux,　and　the　blade　tip　flux　deviation　has　been　maintained　at　a　high　value,　about　13.0%.　The　results　of　sensitivity　analysis　show　that　the　largest　contributor　to　the　uncertainty　of　the　blade　tip　aerodynamic　performance　is　the　tip　clearance　deviation　and　its　variance　index　to　the　uncertainty　of　leakage　flow　rate　and　downstream　entropy　increase　is　as　high　as　88.21%　and　62.63%.　Therefore,　the　geometric　accuracy　of　the　tip　clearance　should　be　strictly　ensured　in　the　turbine　blade　assembly　and　marching　process.　The　influence　of　the　inlet　total　temperature　deviation　on　the　uncertainty　of　the　heat　transfer　performance　of　the　squealer　tip　must　also　be　taken　into　account.　So　a　satisfactory　control　system　should　be　designed　in　the　actual　operation　of　the　gas　turbine　to　make　sure　that　the　fluctuation　of　inlet　total　temperature　can　be　attenuated　rapidly.　©　VC　2022　by　ASME.