A vane assembly includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section that extends there between. A spar has a spar leg that extends through the hollow airfoil section. The spar leg has a through-passage and an end portion that protrudes from the second fairing platform. A support is secured with the end portion of the spar leg. The support has a platform that includes first and second sides, an opening that extends between the first and second sides, and a nozzle tube that extends from the second side. The first side is adjacent the second fairing platform. The end portion of the spar leg is disposed in the opening so as to fluidly connect the through-passage with the nozzle tube.

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 of repairing a piston seal assembly comprises removing worn material from a piston seal groove to generate a worked seal groove, applying a groove buildup member to the worked seal groove, and disposing a seal member proximate the groove buildup member.

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.

Repaired rotors are provided. The rotors are repaired by using an indenter apparatus for plastically straining original portions of the rotor and adjacent repair welds. The weld nugget, adjacent heat affected zones, and the adjacent parent-metal portions or new metal portions, are indented at a weld nugget and heat affected zone, to produce threshold levels of uniform plastic strain which meet or exceed plastic strain levels that provide, when the weld nugget and heat affected zone is heat treated, a recrystallized grain structure metallurgically comparable to the grain structure of the original parent-metal of the rotor. Repaired integrally bladed rotors for gas turbine engines, such as aircraft engines, are provided. Blades for gas turbine engines, including integrally bladed rotors, may be advantageously provided, having been manufactured or repaired as described.

The present application and the resultant patent provide an exhaust frame for a gas turbine engine. The exhaust frame may include an inner casing extending along a longitudinal axis of the exhaust frame, an outer casing positioned radially outward from the inner casing, a strut extending radially from the inner casing to the outer casing, and a relief groove defined in the inner casing or the outer casing and positioned about the strut. The present application and the resultant patent further provide a method for distributing stress concentrations in an exhaust frame of a gas turbine engine.

A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a first side plate, a second side plate and a backing plate that extend circumferentially about an assembly axis. A first brush seal and a second brush seal are positioned on opposite sides of the backing plate such that the first brush seal is between the first side plate and the backing plate and such that the second brush seal is between the second side plate and the backing plate. The first brush seal is dimensioned to establish a first sealing relationship with a first gas turbine engine component. The second brush seal is dimensioned to establish a second sealing relationship with a second gas turbine engine component. A method of assembly is also disclosed.

A thrust reverser door includes a backskin including an interior surface and an exterior loft surface. The thrust reverser door further includes a cover plate including a cover plate body having a first side and a second side opposite the first side. The thrust reverser door further includes a grid structure mounted to the second side of the cover plate body and the interior surface of the backskin.

An exhaust gas turbine is provided. The exhaust gas turbine includes a first turbine housing part having insulating material extending along an interior surface and a second turbine housing part having insulating material extending along an interior surface, the second turbine housing part coupled to the first turbine housing part to form a volute directing exhaust gas to a turbine wheel.

A turbine housing assembly includes a plurality of constituent members connected to one another and easily manufactured. The turbine housing assembly includes a scroll part, an annular lid part, an exhaust gas outlet and a connection part connectable to a bearing housing for a turbine shaft. The scroll part and the connection part are each formed of a single piece of sheet metal and each is welded to the annular lid part that is orthogonal to a turbine axial direction so that the scroll part and the connection part are connected to each other via the annular lid part. Such a turbine housing assembly is of reduced weight, is quite easy to manufacture, of reduced cost, and can be made, at least in part, of materials having lower heat capacity as compared to conventional turbine housings made of sheet metal.