Abstract: A blade with an airfoil profile for a gas turbine includes at least two opposite walls enclosing the inner part of the blade which form cooling channels and method of cooling the blade with a reduced cooling fluid flow rate at a side towards the bottom part of the blade in comparison to the side at the top part, wherein the airfoil profile extends from a bottom to a top part of the blade and at least one direct cooling fluid inlet is arranged at the bottom part of the blade, where at least one set of ribs is respectively arranged on the two walls, extending from the respective wall into the inner part of the blade, forming cooling channels in-between ribs with a channel cross-section smaller at the side towards the bottom part of the blade compared to the side at the top part.

Abstract: A blade with an airfoil profile for a gas turbine includes at least two opposite walls enclosing the inner part of the blade which form cooling channels and method of cooling the blade with a reduced cooling fluid flow rate at a side towards the bottom part of the blade in comparison to the side at the top part, wherein the airfoil profile extends from a bottom to a top part of the blade and at least one direct cooling fluid inlet is arranged at the bottom part of the blade, where at least one set of ribs is respectively arranged on the two walls, extending from the respective wall into the inner part of the blade, forming cooling channels in-between ribs with a channel cross-section smaller at the side towards the bottom part of the blade compared to the side at the top part.

Abstract: An airfoil having cooling passages inside is provided, wherein each radial cross section of the airfoil has a shape of specific profile, wherein hot gas flows along the airfoil's surface from a leading edge to trailing edge, the airfoil's surface comprises a pressure-side and suction-side defined by the trailing edge and leading edge, wherein the trailing edge has cooling fluid discharge exits, the pressure-side and suction-side are respectively defined by a wall comprising an inner surface and an outer surface, which inner surface has ribs extending in a rib-direction inclined to the radial direction, wherein along a portion of at least 10% of the profile's lengths the inclined ribs contact each other at respective cross-contact-points, forming a 2-dimensional matrix. At least one additional blocking-rib extends from the pressure-side to the suction-side and extends from one cross-contact-point to another to cause additional turbulence of said cooling fluid flow to be discharged.

Abstract: A gas turbine blade including a root and an air foil with a leading edge and a trailing edge, a cooling air channel system extending from a cooling air opening in the root via a winding serpentine channel to a trailing edge channel at the trailing edge including an air outlet at the trailing edge is provided. For efficiently cooling the trailing edge of the blade it is proposed that the cooling air channel system includes an air bypass channel connecting the cooling air opening in the root with the trailing edge channel bypassing the serpentine channel.

Abstract: A gas turbine blade including a root, an airfoil with a leading edge and a trailing edge, a radial outer tip, and a pressure side and a suction side between the leading edge and the trailing edge, and a cooling air channel system extending from an air inlet opening in the root throughout the airfoil to a plurality of air outlets at the pressure side and the leading edge of the top of the tip of the airfoil.

Abstract: A gas turbine blade including a root, an airfoil with a leading edge and a trailing edge, a radial outer tip, and a pressure side and a suction side between the leading edge and the trailing edge, and a cooling air channel system extending from an air inlet opening in the root throughout the airfoil to a plurality of air outlets at the pressure side and the leading edge of the top of the tip of the airfoil.

Abstract: A gas turbine blade including a root and an air foil with a leading edge and a trailing edge, a cooling air channel system extending from a cooling air opening in the root via a winding serpentine channel to a trailing edge channel at the trailing edge including an air outlet at the trailing edge is provided. For efficiently cooling the trailing edge of the blade it is proposed that the cooling air channel system includes an air bypass channel connecting the cooling air opening in the root with the trailing edge channel bypassing the serpentine channel.

Abstract: The invention refers to a component defining a blade or a vane for a rotary machine having a rotor rotatable about an axis. The component includes an inner space forming a passage for a cooling fluid between first and second walls. First ribs project from the fist wall and extend essentially in parallel to each other to form fist channels for the fluid from a leading part of the inner space to a trailing part of the space. The first ribs extend in a first direction forming a first angle of inclination to the axis in the leading part and in a second direction forming a second angle of inclination to the axis in the trailing part. The first angle is greater than the second angle.