A stator wheel for a turbomachine turbine. This wheel includes an inner shroud formed by an upstream portion and a downstream portion configured to be assembled with the blades by axial translation in a respective direction.

A stator wheel for a turbomachine turbine. This wheel includes an inner shroud formed by an upstream portion and a downstream portion configured to be assembled with the blades by axial translation in a respective direction.

A service tube assembly comprises a service tube having a threaded end portion and a ratchet hub spaced from the threaded end portion. The threaded end portion of the service tube is threadably engaged with a mating part. The assembly further comprises a locking member having a cantilever extending from a fixed end held relative to the mating part to a free end. A ratchet pawl is provided at the free end for engagement with the ratchet hub on the service tube.

A method of repairing a rod guide assembly of a fuel control unit of an aircraft engine is provided. The method comprises disconnecting a used spring seat from the rod of the rod guide assembly and welding a replacement spring seat to the rod using an electron beam controlled using a circular beam deflection pattern.

A method of repairing a rod guide assembly of a fuel control unit of an aircraft engine is provided. The method comprises disconnecting a used spring seat from the rod of the rod guide assembly and welding a replacement spring seat to the rod using an electron beam controlled using a circular beam deflection pattern.

There is described a fixture for supporting a plurality of gas turbine engine blades that are to be imaged. The mobile fixture comprises a plurality of interconnected mounts arranged to lie within a common plane, wherein each mount comprises at least one support surface for holding a respective blade. Support surfaces of respective mounts are oriented such that their respective normal vectors have the same angle with respect to the common plane.

An assembly is provided for a turbine engine. This turbine engine assembly includes a static structure, a conduit and a bracket. The static structure includes a port. The conduit extends longitudinally through the port. The bracket couples the conduit to the static structure. The bracket includes a first base mount, a second bade mount, a conduit mount, a first damper and a second damper. The first base mount is attached to the static structure. The second base mount is attached to the static structure. The conduit mount is mechanically coupled with the conduit. The first damper is between the first base mount and the conduit mount. The second damper is between the second base mount and the conduit mount.

An assembly is provided for a turbine engine. This turbine engine assembly includes a static structure, a conduit and a bracket. The static structure includes a port. The conduit extends longitudinally through the port. The bracket couples the conduit to the static structure. The bracket includes a first base mount, a second bade mount, a conduit mount, a first damper and a second damper. The first base mount is attached to the static structure. The second base mount is attached to the static structure. The conduit mount is mechanically coupled with the conduit. The first damper is between the first base mount and the conduit mount. The second damper is between the second base mount and the conduit mount.

The invention relates to a connecting device for an adjustable blade or vane of a gas turbine, comprising a journal element connected to a respective blade or vane and a lever element connected to the journal element, wherein the lever element and the journal element are jointly movable about a journal axis of rotation. A clamping element is provided, being situated between the lever element and the journal element, such that a force-locking connection is or can be produced between the journal element, the clamping element, and the lever element. The lever element, the clamping element, and the journal element are aligned relative to each other by means of a positioning element, the positioning element being received in a first seat of the journal element and a corresponding second seat of the lever element.

The invention relates to a connecting device for an adjustable blade or vane of a gas turbine, comprising a journal element connected to a respective blade or vane and a lever element connected to the journal element, wherein the lever element and the journal element are jointly movable about a journal axis of rotation. A clamping element is provided, being situated between the lever element and the journal element, such that a force-locking connection is or can be produced between the journal element, the clamping element, and the lever element. The lever element, the clamping element, and the journal element are aligned relative to each other by means of a positioning element, the positioning element being received in a first seat of the journal element and a corresponding second seat of the lever element.