Abstract: A turbine blade is provided. The turbine blade may include a blade body including a leading edge, a trailing edge, a suction side, a pressure side, and a tip region, a squealer tip extending upward from the tip region of the blade body, a winglet extending outward from the squealer tip on the suction side of the blade body, and a cooling hole obliquely formed through the winglet to communicate with an inner cavity of the blade body.

Abstract: Disclosed are a blade ring segment for a turbine section, a turbine section having the blade ring segment, and a gas turbine having the turbine section. Multiple blade ring segments is installed in a turbine casing accommodating turbine blades rotated by combustion gas from a combustor. The blade ring segment includes an inner panel provided in the turbine casing and having multiple air holes through which cooling air fed from the outside of the turbine casing flows, an outer panel disposed on one side of the inner panel, and a cooling structure protruding from one side of the outer panel so as to form a flowing channel in a zigzag pattern so that cooling air fed through the air holes flows therethrough.

Abstract: A turbine blade is provided. The turbine blade may include a blade body including a leading edge, a trailing edge, a suction side, a pressure side, and a tip region, a squealer tip extending upward from the tip region of the blade body, a winglet extending outward from the squealer tip on the suction side of the blade body, and a cooling hole obliquely formed through the winglet to communicate with an inner cavity of the blade body.

Abstract: A gas turbine includes a turbine vane for suppressing a secondary vortex. The turbine vane includes a vane platform and a vane tip and is segmented into a plurality of span regions arranged across a span between the vane platform and the vane tip, each span region of the turbine vane including a specific airfoil that occupies a corresponding span region of the plurality of span regions and extends from a leading edge to a trailing edge of the turbine vane. The specific airfoil has a different thickness for each span region among a first span region having a first length that extends from the vane platform toward the vane tip; a second span region having a second length that extends from the first span region toward the vane tip; and a third span region having a third length that extends from the second span region to the vane tip.

Abstract: Disclosed are a blade ring segment for a turbine section, a turbine section having the blade ring segment, and a gas turbine having the turbine section. Multiple blade ring segments is installed in a turbine casing accommodating turbine blades rotated by combustion gas from a combustor. The blade ring segment includes an inner panel provided in the turbine casing and having multiple air holes through which cooling air fed from the outside of the turbine casing flows, an outer panel disposed on one side of the inner panel, and a cooling structure protruding from one side of the outer panel so as to form a flowing channel in a zigzag pattern so that cooling air fed through the air holes flows therethrough.