Abstract: The invention concerns a turbine for a gas turbine comprising a blade, a vane and an abradable lip attached to the blade or to the vane, wherein the blade and the vane are separated by a gap and the abradable lip extends part of the distance across the gap. Embodiments include the addition of an abrasive layer attached on the other side of the gap from the abradable lip. A method of manufacturing is also described.

Abstract: A gas turbine blade includes a blade root and a blade aerofoil, a cooling fluid plenum extending inside the gas turbine blade through the blade root, the blade aerofoil and the blade tip, a blade root impingement plate in the cooling fluid plenum inside the blade root and a blade tip impingement plate in the cooling fluid plenum inside the blade tip, the blade tip impingement plate having at least one cooling fluid hole configured and arranged to enable a cooling fluid to flow from the blade tip into the blade aerofoil via the cooling fluid hole or holes, and a pipe extending in the cooling fluid plenum from the blade root impingement plate to the blade tip impingement plate. The blade root impingement plate can direct the cooling fluid from the blade root to the pipe.

Abstract: The disclosure pertains to a vane comprising a platform and airfoil extending form said platform and connected to the platform by a fillet. An impingement tube is inserted into said airfoil delimiting a cooling channel between the impingement tube and the side walls. The vane further comprises a baffle structure positioned adjacent the fillet and which follows the inside contour of the fillet; delimiting a first cooling passage between the fillet and the baffle structure. A first obstruction is arranged on the inside of the airfoil at the connection of the fillet to the side walls for separating the first cooling passage from the cooling channel in the airfoil and to guide the cooling gas from the first cooling passage into the impingement tube. The disclosure further refers to a method for cooling such a vane.

Abstract: A gas turbine blade includes a blade root and a blade aerofoil, a cooling fluid plenum extending inside the gas turbine blade through the blade root, the blade aerofoil and the blade tip, a blade root impingement plate in the cooling fluid plenum inside the blade root and a blade tip impingement plate in the cooling fluid plenum inside the blade tip, the blade tip impingement plate having at least one cooling fluid hole configured and arranged to enable a cooling fluid to flow from the blade tip into the blade aerofoil via the cooling fluid hole or holes, and a pipe extending in the cooling fluid plenum from the blade root impingement plate to the blade tip impingement plate. The blade root impingement plate can direct the cooling fluid from the blade root to the pipe.

Abstract: The invention concerns a turbine for a gas turbine comprising a blade, a vane and an abradable lip attached to the blade or to the vane, wherein the blade and the vane are separated by a gap and the abradable lip extends part of the distance across the gap. Embodiments include the addition of an abrasive layer attached on the other side of the gap from the abradable lip. A method of manufacturing is also described.

Abstract: A new gas turbine-fuel cell Hybrid Cycle is proposed. The fuel cell advantageously operates close or under atmospheric pressure and is fully integrated with the gas turbine that is based on an Inverted Brayton-Joule Cycle. The idea of the invention is to capitalize on the intrinsic oxygen-nitrogen separation characteristic of the fuel cell electrolyte by sending to the Inverted Brayton-Joule Cycle only the anodic flow, which is the one free of nitrogen. In this way the flow that expands in the turbine consists only in steam and carbon dioxide. After the expansion the steam can be easily condensed, separated and pumped up. Therefore the compressor has mainly only to compress the separated carbon dioxide. This effect generates a substantial advantage in term of efficiency and enables separating the carbon dioxide.

Abstract: An airfoil portion including an outer wall that defines a cavity for receiving cooling air. The airfoil portion includes a leading edge that resides in an upstream direction, a trailing edge that resides in a downstream direction, a convex suction side, and a concave pressure side. At least one insert disposed within the cavity is configured to initially receive at least a portion of the cooling air entering the chamber of the insert and direct the cooling air through a plurality of insert apertures to cool the inner surface of the outer wall of the airfoil portion. The insert further includes a configuration that generally conforms to the contour of the outer wall of the chamber but in spaced relation thereto. A portion of the cooling air exits the airfoil portion through a plurality of film cooling apertures formed through the outer wall.

Abstract: The disclosure pertains to a vane comprising a platform and airfoil extending form said platform and connected to the platform by a fillet. An impingement tube is inserted into said airfoil delimiting a cooling channel between the impingement tube and the side walls. The vane further comprises a baffle structure positioned adjacent the fillet and which follows the inside contour of the fillet; delimiting a first cooling passage between the fillet and the baffle structure. A first obstruction is arranged on the inside of the airfoil at the connection of the fillet to the side walls for separating the first cooling passage from the cooling channel in the airfoil and to guide the cooling gas from the first cooling passage into the impingement tube. The disclosure further refers to a method for cooling such a vane.

Abstract: A new gas turbine-fuel cell Hybrid Cycle is proposed. The fuel cell advantageously operates close or under atmospheric pressure and is fully integrated with the gas turbine that is based on an Inverted Brayton-Joule Cycle. The idea of the invention is to capitalize on the intrinsic oxygen-nitrogen separation characteristic of the fuel cell electrolyte by sending to the Inverted Brayton-Joule Cycle only the anodic flow, which is the one free of nitrogen. In this way the flow that expands in the turbine consists only in steam and carbon dioxide. After the expansion the steam can be easily condensed, separated and pumped up. Therefore the compressor has mainly only to compress the separated carbon dioxide. This effect generates a substantial advantage in term of efficiency and enables separating the carbon dioxide.