Patent attributes
A turbine blade for a gas turbine engine having a 5-pass serpentine flow cooling circuit with a first pressure side channel forming the first leg and being supplied with cooling air from an external source, a first down-pass channel on the suction side forming the second leg, a first collector cavity formed between the first and second leg to receive the cooling air from the second leg, a second collector cavity aft of the first collector cavity to receive cooling air from the first collector cavity through a core tie hole, a second pressure side cooling channel connected to the second collector cavity, a second suction side cooling channel to receive cooling air from the second pressure side channel, and a third up-pass channel along the trailing edge to receive cooling air from the second down-pass suction side channel.
