Method of manufacturing gas turbine engine element having at least one elongated opening

A method of manufacturing a shroud segment for a gas turbine engine, the method comprising:

• providing a mold defining a mold cavity having a shape corresponding to the shroud segment, the mold cavity including a platform cavity shaped to define a platform of the shroud segment, the platform cavity having a mold surface corresponding to an inner surface of the platform of the shroud segment;
• providing an insert extending partly through the platform cavity, the insert including a plurality of elongated pins extending in the platform cavity along and spaced apart from the mold surface;
• injecting a powder injection molding feedstock into the mold cavity to obtain a green part with a platform portion through which at least part of the elongated pins extend;
• disengaging the green part from the mold, including sliding the elongated pins out of the platform portion of the green part to define a plurality of elongated cooling passages in the platform of the shroud segment, the elongated cooling passages disposed radially between inner and outer surfaces of the platform portion;
• and
• debinding and sintering the green part to define the shroud segment.