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.