Turbomachine component for a gas turbine, turbomachine assembly and gas turbine having the same

A turbomachine component for a gas turbine, the turbomachine component comprising:

• an airfoil comprising an airfoil wall defining an internal space of the airfoil, and a first and a second cooling channel in the internal space of the airfoil;
• a first impingement insert inserted in the first cooling channel and defining a first main flow channel for conducting flow of cooling air along a longitudinal direction of the airfoil and at least one first peripheral flow channel for receiving impingement jets ejected from the first main flow channel via impingement holes of the first impingement insert;
• a second impingement insert inserted in the second cooling channel and defining a second main flow channel for conducting flow of cooling air along the longitudinal direction of the airfoil and at least one second peripheral flow channel for receiving impingement jets ejected from the second main flow channel via impingement holes of the second impingement insert;
• and
• a channel connecting conduit configured to conduct a flow of the cooling air from the first cooling channel to the second cooling channel and comprising:
• an inlet of the channel connecting conduit connected to an outlet of the first cooling channel, and
• an outlet of the channel connecting conduit connected to an inlet of the second cooling channel.