Airfoils bodies having a first core cavity and a second core cavity located within the airfoil body that is adjacent the first core cavity. The second core cavity is defined by a first cavity wall, a second cavity wall, a first exterior wall, and a second exterior wall, wherein the first cavity wall is located between the second core cavity and the first core cavity and the first and second exterior walls are exterior walls of the airfoil body. The first cavity wall includes a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall. At least one first cavity impingement hole is formed within the first surface and a central ridge extends into the second core cavity from at least one of the first cavity wall and the second wall and divides the second core cavity into a two-vortex chamber.

A method of joining first and second turbine vanes is provided. The method includes casting and machining each of the first and second turbine vanes, coating each of the first and second turbine vanes with thermal barrier coating (TBC) and executing field assisted sintering technology (FAST) processing to join the first and second turbine vanes.

A case for a gas turbine engine includes a cast case section cast case section configured to be welded between a forward case section and an aft case section.

A method of fabricating a ceramic turbine blade, the method includes selective melting on a powder bed in order to obtain a blade mold cavity in a mold, a ceramic-based suspension is provided, the suspension is introduced into the blade mold cavity, the suspension is subjected to a gelation step in the mold cavity in order to obtain a blade suitable for being extracted from the mold cavity, and the blade is extracted from the mold cavity.

A stiffness boss for a turbine case of a gas turbine engine is disclosed. The stiffness boss includes a head portion disposed on an outer case surface of the turbine case, the head portion configured to provide rigidity in response to a transverse load being applied to the turbine case in a transverse direction. The stiffness boss also includes a leg portion disposed on the outer case surface of the turbine case and connected to the head portion, the leg portion configured to provide rigidity in response to an axial load being applied to the turbine case in an axial direction, such that deformation of the turbine case is resisted.

Extracorporeal circuit devices can be used for on-pump open-heart surgery to support surgical procedures such as coronary artery bypass grafting. In some cases, a centrifugal pump is used as part of an extracorporeal circuit. Centrifugal pump heads are described herein that induce flow on two sides of an impeller plate, and that can be conveniently mechanically assembled.

A component for a gas turbine engine includes a platform having an outer surface and an inner surface. A cover plate can be positioned adjacent to the outer surface of the platform. The outer surface of the platform can include a pocket and the cover plate is positioned relative to the pocket to establish a platform cooling channel therebetween.

Methods for manufacturing a turbine nozzle are provided. A plurality of nozzle segments is formed. Each nozzle segment comprises an endwall ring portion with at least one vane. The plurality of nozzle segments are connected to an annular endwall forming a segmented annular endwall concentric to the annular endwall with the at least one vane of each nozzle segment extending between the segmented annular endwall and the annular endwall.

A stator vane for a gas turbine engine is provided. The stator vane has a platform surface from which an aerofoil extends, and a joggle surface that is circumferentially and radially displaced from the platform surface. Multiple stator vanes are arranged together to form a stator vane row, with each stator vane in the row remaining independent of the others. When the stator vanes are assembled together in a row, the joggle surface of one vane circumferentially overlaps a recess surface formed in a neighbouring vane. Because of the increased circumferential extent of the vanes, the vane is able to rotate in a retaining slot less than a conventional vane. This results in less wear and/or damage to the components.

A gas turbine nozzle guide vane structure includes a vane shaped as an airfoil and having a vane trailing edge, an endwall including an opening to receive an end of the vane, and an element securing the endwall and the vane to each other. Clearance remaining between the endwall and the vane defines a plenum to feed cooling air to the vane at a location adjacent the vane trailing edge. Certain arrangements may have a purge groove defined in at least one of the endwall and the vane and located between the endwall and the vane to receive cooling fluid supplied. In certain arrangements, the structure may include a cover sheet on the endwall defining a gap with the vane, the purge groove configured to receive cooling fluid that exits through the gap.