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 rotor assembly includes a rotor having a dovetail slot. The dovetail slot includes a plurality of recesses and a first radially innermost surface. A rotor blade includes an airfoil that extends radially outward from a platform and a dovetail that extends radially inward from the platform. The dovetail includes a plurality of projections extending in opposite directions that are received by the plurality of recesses of the dovetail slot. The dovetail further includes a leading edge surface, a trailing edge surface, and a second radially innermost surface. The second radially innermost surface defines a groove from the leading edge surface to the trailing edge surface. The shim is positioned within the groove and between the first radially innermost surface of the dovetail slot and the second radially innermost surface of the dovetail. The shim extends at least partially radially along both of the leading edge surface and the trailing edge surface to secure the rotor blade within the dovetail slot during various operating conditions of the turbomachine.

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 manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate. A meter section of a cooling aperture is formed in the substrate. An internal coating is applied onto a surface of the meter section. An external coating is applied over the substrate. A diffuser section of the cooling aperture is formed in the external coating and the substrate to provide the cooling aperture.

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.

A component of an aircraft engine includes an annular flange disposed about a radially outer surface of the component. the annular flange includes an annular wall extending radially outwardly from the radially outer surface of the component. The annular wall includes radially-extending supports circumferentially spaced apart and extending radially between the radially outer surface of the component and a circumferentially uninterrupted radially outer rim of the annular wall. The annular wall includes one or more arcuate cutouts defined circumferentially between adjacent radially-extending supports and radially inwards of the radially outer rim of the annular wall. The radially-extending supports include fastener openings defined axially therethrough. A spigot extends axially from the radially outer rim of the annular wall and circumferentially about an entire circumference of the radially outer rim of the annular wall.

Systems and methods include providing a stator vane bushing for a variable stator vane assembly having a movable stator vane and a stator vane housing disposed annularly about the movable stator vane. The bushing includes a flange, a barrel extending from the flange, and a central aperture extending through the flange and the barrel and is disposed in the housing and annularly about the stator vane. The bushing is formed from a ceramic material having a coefficient of thermal expansion (CTE) lower than or equal to a CTE of one or more of a stator vane and a housing of the variable stator vane assembly.

A manufacturing method is provided during which a preform component for a turbine engine is provided. A cooling aperture is formed in the preform component. The cooling aperture includes a centerline, an inlet and an outlet. The cooling aperture extends longitudinally along the centerline through a wall of the preform component from the inlet to the outlet. The forming of the cooling aperture includes forming a first portion of the cooling aperture using a machining tool implement with a first toolpath that is angularly offset from the centerline by a first angle between thirty-five degrees and ninety degrees.

A method for removing a component fixed to an aeronautical part, the aeronautical part comprising a first material, and the component comprising a second material different from the first material, the method comprising steps of determining the thicknesses of the component as a function of the position on the component, and of removing the component by means of a pressurized water jet moving over the component as a function of the thicknesses determined in the determination step.