Redundant entry cooling air feed hole blockage preventer for a gas turbine engine

A vane ring for a gas turbine engine component, comprising:

• an inner vane platform around an axis;
• an outer vane platform around the axis;
• a multiple of vanes that extend between the inner vane platform and the outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooling airflow through a respective one of a multiple of feed passages;
• a hooked rail that extends from the outer vane platform;
• and
• a multiple of metering passages in the hooked rail, each of the multiple of metering passages intersects with one of the multiple of feed passages;
• and
• a multiple of secondary passages recessed in the hooked rail, each of the multiple of secondary passages in communication with one of the multiple of metering passages at an angle, each of the multiple of metering passages and the multiple of secondary passages being circular in cross-section, a diameter of each of the multiple of secondary passages equivalent to a diameter of each of the multiple of metering passages.