Tip shroud for cooled blade of gas turbine

A gas turbine moving blade assembly comprising:

• a moving blade having a blade root and an outer end portion;
• and
• a tip shroud mounted on the outer end portion of said moving blade, said tip shroud having opposite side faces, an outer face, a plurality of cooling air holes formed in the side faces, and a plurality of cooling air holes formed in the outer face of said tip shroud,
• wherein said cooling air holes, formed in the outer face of said tip shroud, communicate with the interior of said moving blade and are positioned on a higher pressure side of a combustion gas passage, and
• wherein said cooling air holes, formed in the outer face of said tip shroud, are positioned only on an upstream side of said tip shroud relative to the flow of combustion gas in the combustion gas passage.

A gas turbine moving blade assembly comprising:

• a moving blade having a blade root and an outer end portion;
• and
• a tip shroud mounted on the outer end portion of said moving blade, said tip shroud having opposite side faces, an outer face, a plurality of cooling air holes formed in the side faces, and a plurality of cooling air holes formed in the outer face of said tip shroud
• wherein said cooling air holes, formed in the outer face of said tip shroud, communicate with the interior of said moving blade And are Positioned on a higher pressure side of a combustion gas passage,
• wherein each of said cooling holes, formed in the side faces of said tip shroud, communicate with the interior of said moving blade and have an elongated elliptical shape so as to release cooling air over a wide area of said tip shroud.