Tip　leakage　flow　in　high　speed　turbine　induce　significant　thermal　loads　and　give　rise　to　intense　thermal　stresses　on　blade　tip,　while　increasing　inlet　pressure　tends　to　accelerate　leakage　velocity　beyond　transonic　regime.　The　present　research　quantifies　heat　transfer　and　film　cooling　effect　on　a　squealer　tip　with　three　film　cooling　layouts,　three　coolant　mass　flow　rates　and　a　relative　casing　movement.　The　results　indicate　that　area-averaged　HTC　of　PS　layout　is　higher　than　that　of　CAM　layout　by　6.9%　and　that　of　SS　layout　by　5.7%　when　coolant　flow　rate　equals　to　0.6%　mainstream　flow　rate.　By　comparison,　it　is　clearly　observed　that　area　of　the　high　heat　transfer　coefficient　regions　are　significantly　enlarged　when　the　flow　rate　of　coolant　is　increased.　With　relative　casing　movement,　a　significant　high　HTC　stripe　parallel　to　pressure　side　rim　is　formed.　In　case　of　the　PS　layout,　heat　transfer　coefficient　is　reduced　by　7.3%　with　casing　movement.　While　in　case　of　CAM　layout　and　SS　layout,　heat　transfer　coefficient　increased　by　4.8%　and　2.3%　with　casing　movement,　respectively.　Detailed　flow　patterns　with　three　film　cooling　layouts　are　also　illustrated.　Copyright　©　2020　ASME