Blade outer air seal cooling passage

A gas turbine engine component comprising:

• a structure including a first wall and a second wall that provide a cooling passage, the cooling passage extends a length from a first end to a second end, a cluster of impingement inlet holes is provided in the second wall at the first end, and an outlet is provided at the second end wherein a first region is provided within the cooling passage beneath the cluster of impingement inlet holes, and a second region includes turbulators, the first region extends in the range of 25-65% of the length and has lower fluid friction than the second region, and the first region is without the turbulators, wherein the structure includes multiple parallel discrete cooling passages each having the outlet and the cluster of impingement inlet holes arranged on opposite sides of the structure.