The invention discloses a blade tip coupled cooling experiment 
system for 
turbine blades of a gas 
turbine. The blade tip coupled cooling experiment 
system comprises a high temperature main flow channel, a U-shaped 
cooling channel, an experimental test section and a 
data acquisition and analysis 
system, wherein the high temperature main flow channel comprises a 
temperature control box, and a main flow gas pump, a main flow gas flow stabilization tank, a main flow 
gas heater and a main flow three-way 
electromagnetic valve which are sequentially connected; the U-shaped 
cooling channel comprises acold flow outlet 
vacuum pump, and a cold flow inlet gas pump, a cooling gas flow stabilization tank, a cooling 
gas heater and a cold flow inlet three-way 
electromagnetic valve which are sequentiallyconnected; the experimental test section comprises a U-shaped 
cooling channel, a high-temperature main flow channel and a blade tip plate with a through hole in the center, and an embedded plate is embedded in the through hole; the 
data acquisition and analysis system comprises a cooling channel 
infrared thermal imager, a main flow channel 
infrared thermal imager, a 
CCD camera, and a 
data acquisition and analysis computer connected with the cooling channel 
infrared thermal imager, the main flow channel infrared thermal imager and the 
CCD camera; and an outlet of the main flow three-way 
electromagnetic valve is communicated to an inlet of the high temperature main flow channel, and an outlet of the cold flow inlet three-way electromagnetic valve is communicated to an inlet of the U-shaped cooling channel.