To　study　how　the　pulsating　coolant　extracted　from　the　compressor　affect　the　flow　and　cooling　characteristics　of　the　squealer　tip　of　a　gas　turbine　blade,　the　aerodynamic　and　cooling　performance　of　the　turbine　blade　squealer　tip　with　film　cooling　pulsation　characteristics　is　studied　by　numerically　solving　three-dimensional　unsteady　Reynolds-averaged　Navier-Stokes　(URANS)　equations　and　using　the　standard　k-ω　turbulence　model.　Nine　film　holes　are　arranged　along　the　middle　camber　line　of　the　squealer　tip　at　equal　intervals,　and　sinusoidal　function　is　used　to　describe　the　discipline　of　the　coolant　pulsation.　The　tip　film　cooling　effectiveness　and　total　pressure　loss　coefficient　are　compared　and　studied　at　three　pulsating　amplitudes　and　five　pulsating　frequencies.　The　results　show　that　there　are　obvious　differences　in　the　coolant　penetration　and　adhesion　at　different　instants　in　a　pulsating　cycle.　When　the　coolant　blowing　ratio　fluctuates　slightly,　the　increase　of　the　pulsating　frequency　changes　the　phase　of　the　tip　film　cooling　effectiveness　curve,　but　has　no　effect　on　the　overall　cooling　performance.　However,　when　the　coolant　blowing　ratio　fluctuates　greatly,　the　increase　of　the　pulsating　frequency　will　slightly　improve　the　tip　cooling　efficiency,　and　affected　by　the　delayed　feedback　effect,　as　the　pulsating　frequency　increases　to　the　maximum　value　of　2　000　Hz,　the　lowest　value　of　film　cooling　effectiveness　is　increased　by　about　50%　compared　to　250　Hz　during　the　pulsation　period.　The　high-temperature　mainstream　periodically　invades　the　coolant　pipeline　with　the　large　amplitude　pulsation,　causing　damage　to　the　original　structure　of　the　film　holes　at　the　tip　middle　chord　and　trailing　edge.　The　averaged　total　pressure　loss　coefficient　follows　the　law　of　sinusoidal　function　when　the　coolant　blowing　ratio　pulsates　with　a　low　frequency,　the　total　pressure　loss　difference　increases　at　varied　instants　with　the　pulsating　amplitude　enlargement.　Meantime,　the　difference　gradually　decreases　when　the　pulsating　frequency　increases.　This　study　can　provide　the　reference　for　the　aerothermal　performance　analysis　of　the　turbine　blade　squealer　tip　with　consideration　of　the　film　cooling　pulsation　characteristics.　©　2022,　Editorial　Office　of　Journal　of　Xi＇an　Jiaotong　University.　All　right　reserved.