The present disclosure relates to an impeller and a method of manufacturing the same. The impeller includes: a hub in which a plurality of spiral first slots are formed; a shroud which is positioned opposite the hub, and has a plurality of spiral second slots formed therein; and a plurality of blades which is coupled to the hub and the shroud, and have an upper protrusion formed on one side and a lower protrusion formed on the other side; and wherein the upper protrusion is inserted into and coupled to a second hole formed in the second slot, and the lower protrusion is inserted into and coupled to a first hole formed in the first slot.

A method and casting core for forming a landing for welding a baffle inserted into an airfoil are disclosed, wherein the baffle landing of the blade or vane is formed in investment casting by the casting core rather than by wax, reducing tolerances and variability in the location of the baffle inserted into the cooling cavity of airfoil when the baffle is welded to the baffle landing.

A turbine blade disposed along a radial direction of a turbine includes: an airfoil portion positioned in a fluid flow passage of the turbine; and a shroud portion positioned on an inner side or an outer side of the airfoil portion in the radial direction, and having an opening with which an end portion of the airfoil portion is to be engaged. A clearance is formed between a wall surface forming the opening of the shroud portion and an outer peripheral surface of the end portion of the airfoil portion. The wall surface of the shroud portion and the outer peripheral surface of the airfoil portion are joined to each other. At least one of the shroud portion or the airfoil portion has a cooling hole formed thereon, the cooling hole having an opening into the clearance and being configured to supply the clearance with a cooling fluid.

A method includes joining a fuel plurality of injection components to a fuel manifold, wherein for each fuel injection component in the plurality of fuel injection components, a metallic joint is formed joining and sealing the fuel injection component to the manifold. A system includes a fuel manifold. A plurality of fuel injection components are connected in fluid communication with the fuel manifold with metallic joints sealing between each of the plurality of fuel injection components and the fuel manifold to prevent leakage from between the manifold and the plurality of fuel injection components.

A rod assembly includes a turnbuckle that extends along a central axis, a first rod that is to be screwed into a first adjustment hole of the turnbuckle, a second rod that is to be screwed into a second adjustment hole of the turnbuckle, a first nut that is fitted to a first adjustment end portion of the first rod, and a second nut that is fitted to a second adjustment end portion of the second rod. A first turnbuckle-welded portion is provided between the first nut and the turnbuckle, and a second turnbuckle-welded portion is provided between the second nut and the turnbuckle. A first rod-welded portion is provided between the first nut and the first rod, and a second rod-welded portion is provided between the second nut and the second rod.

This blade repair method has: a first welding step in which overlay welding in which a first welding material is used is performed to form a notched part and a bury a first region positioned on a blade-body side with a first welding material; and a second welding step in which, after the first welding step, overlay welding in which a second welding material is used is performed to form a notched part and bury a second region positioned on a front-surface side of a platform with the second welding material. The high-temperature strength of the second welding material is higher than the high-temperature strength of the first welding material, the weldability of the first welding material is higher than the weldability of the second welding material, and the second region is located in a range from 1.0 mm to 3.0 mm (inclusive) from the front surface of the platform toward the blade body.

A journal support pin to support intermediate gears for use in gas turbine engine comprises a titanium body, and an outer surface outside of the titanium body having a surface hardness that is harder than the body. A gas turbine engine and a method of forming a journal support pin to support intermediate gears for use in gas turbine engine are also disclosed.

A fan with airfoil blades is provided for a regenerative air vacuum street sweeper. The blades are formed using cut and pressed upper and lower panels which are welded at a forward edge to a rod to form the airfoil leading edge and welded at the rear edges to form the airfoil trailing edge. Pins extend laterally outwardly from the rod for mounting each blade in corresponding holes in the front and rear plates of the fan housing. The side edges of the blade are welded to the plates at a 9-11° angle of attack. The airfoil blades allow for reduced size, horse power, noise, and manufacturing and shipping costs.

A gas turbine engine includes a propulsor and a fan drive turbine. The fan drive turbine drives the propulsor through a geared architecture. The geared architecture includes a sun gear, a ring gear, and intermediate gears supported on journal support pins. The sun gear engages the intermediate gears and the intermediate gears engages the ring gear. The journal support pins include a titanium body and an outer surface outside of the titanium body that has a surface hardness that is harder than the titanium body. The outer surface is provided by a steel sleeve. Oil supply holes extend from a central bore in the titanium body through the steel sleeve. At least one pin extends through the steel sleeve to secure the steel sleeve to the titanium body.

A method for manufacturing a turbine engine part in which a first rough casting element includes a first face and a second face opposite to each other is assembled by the second face on an orifice which has a second element of the part. The method includes machining a through-cavity in the first element which opens at the first face and from the second face of the first element and machining the first face of the first element so as to form an area suitable for ensuring the attachment of a conduit on the first element. The machining of the cavity and of the first face is achieved by using a machining reference frame based on the second element.