The system for designing advanced Kaplan turbine-based on advanced blade design of a hydro powered turbine comprises an EES for calculating and determining a set of parameters involved in the designing of Kaplan turbine blade; a designing user interface for designing a 3d-model of the Kaplan turbine blade; an analyzing unit for CFD analysis of the turbine models on based on the K-omega turbulent model with a Y+ of 1, wherein the turbulent model is used to ensure the near wall function of water and the rotational pressure applied on the blades thereby generating results of the analysis using CFD post and plotted on a table for the comparative study of the blade models; and a manufacturing unit for manufacturing Kaplan turbine blade based on comparative study of the blade models using a machine learning approach.

An assembly for a dual-walled component of a gas turbine engine and methods of forming and repairing a dual-walled component. The assembly includes a cold section part having an outer surface that defines a plurality of impingement apertures, a hot section part including a pre-sintered preform, the hot section part positioned over the outer surface of the cold section part, and a plurality of support structures including the pre-sintered preform, the plurality of support structures positioned between the hot section part and the cold section part, the plurality of support structures separating the hot section part from the cold section part to define at least one cooling channel therebetween.

An assembly for a dual-walled component of a gas turbine engine and methods of forming and repairing a dual-walled component. The assembly includes a cold section part having an outer surface that defines a plurality of impingement apertures, a hot section part including a pre-sintered preform, the hot section part positioned over the outer surface of the cold section part, and a plurality of support structures including the pre-sintered preform, the plurality of support structures positioned between the hot section part and the cold section part, the plurality of support structures separating the hot section part from the cold section part to define at least one cooling channel therebetween.

A machine tool arranged to deliver an energy source through a processing head onto a work-piece, wherein; the machine-tool has a clamping mechanism arranged to temporarily receive the processing-head, or another machining or processing-head, to process a work-piece; the processing-head comprising one or more guiding mechanisms arranged to direct the energy source onto a work-piece and a processing-head docking-manifold arranged to have connected thereto one or more media to be, in use, supplied to the processing-head to facilitate processing of the work-piece; wherein the processing-head docking-manifold allows the one or more media to be supplied to the processing-head when the processing-head is connected to the clamping mechanism; and wherein the machine-tool also comprises at least one mechanism arranged to move a supply docking-manifold into and/or out of connection with the processing-head docking-manifold such that when the two manifolds are connected the or each media is supplied to the processing head.

A machine tool arranged to deliver an energy source through a processing head onto a work-piece, wherein; the machine-tool has a clamping mechanism arranged to temporarily receive the processing-head, or another machining or processing-head, to process a work-piece; the processing-head comprising one or more guiding mechanisms arranged to direct the energy source onto a work-piece and a processing-head docking-manifold arranged to have connected thereto one or more media to be, in use, supplied to the processing-head to facilitate processing of the work-piece; wherein the processing-head docking-manifold allows the one or more media to be supplied to the processing-head when the processing-head is connected to the clamping mechanism; and wherein the machine-tool also comprises at least one mechanism arranged to move a supply docking-manifold into and/or out of connection with the processing-head docking-manifold such that when the two manifolds are connected the or each media is supplied to the processing head.

A process of producing an article and an article made are provided. The process includes producing a near-net shape component. The process includes forming a consolidation shell by additive manufacturing. The consolidation shell defines an interior space having a geometry corresponding to a component. A metallic powder is provided to the interior space. Gas is removed from the interior space. The metallic powder is consolidated in the consolidation shell under sufficient heat and pressure to form the near-net shape component.

A process of producing an article and an article made are provided. The process includes producing a near-net shape component. The process includes forming a consolidation shell by additive manufacturing. The consolidation shell defines an interior space having a geometry corresponding to a component. A metallic powder is provided to the interior space. Gas is removed from the interior space. The metallic powder is consolidated in the consolidation shell under sufficient heat and pressure to form the near-net shape component.

Disclosed is a cooled airfoil having a hub end and tip, an airfoil height being defined between the hub end and the tip. The airfoil has a leading edge, trailing edge, suction side and pressure side. The airfoil has a first airfoil height section adjacent the hub end and extending towards the tip, wherein, in a meridional view, the leading edge and trailing edge are straight along the first airfoil height section. The airfoil has a second airfoil height section adjacent the tip and extending towards the hub end, wherein, in a meridional view, the airfoil is concavely shaped at the leading edge and is convexly shaped at the trailing edge along the second airfoil height section. At least one cooling channel has a length principally extending along the airfoil height, extends straight in a first cooling channel length section, and is bent in a second cooling channel length section.

Disclosed is a cooled airfoil having a hub end and tip, an airfoil height being defined between the hub end and the tip. The airfoil has a leading edge, trailing edge, suction side and pressure side. The airfoil has a first airfoil height section adjacent the hub end and extending towards the tip, wherein, in a meridional view, the leading edge and trailing edge are straight along the first airfoil height section. The airfoil has a second airfoil height section adjacent the tip and extending towards the hub end, wherein, in a meridional view, the airfoil is concavely shaped at the leading edge and is convexly shaped at the trailing edge along the second airfoil height section. At least one cooling channel has a length principally extending along the airfoil height, extends straight in a first cooling channel length section, and is bent in a second cooling channel length section.

A blade includes an airfoil section extending between leading and trailing edges, first and second opposed sides each joining the leading and trailing edges, and an inner end and a free end. The blade also includes an abrasive tip at the free end of the airfoil section. The abrasive tip includes particles diposed in a matrix material. The matrix material is a polymeric material that has a glass transition temperature greater than or equal to about 225 degrees C. (487 degrees F.). A gas turbine engine and a method of fabricating a blade are also disclosed.