A rotor loading system for an aircraft turbine engine has a first tool having first proximal and first distal ends. The first proximal end defines a traction interface about a first axis and a first surface radially outward of the traction interface. The first distal end defines first projections spaced circumferentially and extending to outward of the first surface. The system has a second tool with second proximal and second distal ends. The second proximal end defines a torque interface about a second axis and a second surface radially outward of the torque interface. The second distal end defines second projections spaced circumferentially and extending to outward of the second surface. One of the first and the second tool is received by the other one of the tools such that: the first and the second axis are colinear and each of the first projections is received between two second projections.

A rotor loading system for an aircraft turbine engine has a first tool having first proximal and first distal ends. The first proximal end defines a traction interface about a first axis and a first surface radially outward of the traction interface. The first distal end defines first projections spaced circumferentially and extending to outward of the first surface. The system has a second tool with second proximal and second distal ends. The second proximal end defines a torque interface about a second axis and a second surface radially outward of the torque interface. The second distal end defines second projections spaced circumferentially and extending to outward of the second surface. One of the first and the second tool is received by the other one of the tools such that: the first and the second axis are colinear and each of the first projections is received between two second projections.

The present invention is directed to a turbomachinery blade and a method of fabricating the turbomachinery blade. The turbomachinery blade comprises a plurality of blade segments, and the plurality of the blade segments are separate from one another at least partially in an axial direction forming radial seams between adjacent blade segments. The method comprises forming a plurality of blade segments which are separate from one another at least partially in an axial direction; and forming radial seams between adjacent blade segments.

An article comprises a first portion comprising a first alloy and a second portion comprising a second alloy that is metallurgically bonded to the first portion to form a monolithic article. The metallurgical bonding involves the application of an electrical current across the bond line and results in a retention of a metallurgical structure of the first portion and of a metallurgical structure of the second portion immediately adjacent to a bond line. The first portion has a first dominant property and the second portion has a second dominant property. The first dominant property is different from the second dominant property. The first dominant property is selected to handle operating conditions at a first position of the article where the first portion is located and the second dominant property is selected to handle operating conditions at a second position of the article where the second portion is located.

An article comprises a first portion comprising a first alloy and a second portion comprising a second alloy that is metallurgically bonded to the first portion to form a monolithic article. The metallurgical bonding involves the application of an electrical current across the bond line and results in a retention of a metallurgical structure of the first portion and of a metallurgical structure of the second portion immediately adjacent to a bond line. The first portion has a first dominant property and the second portion has a second dominant property. The first dominant property is different from the second dominant property. The first dominant property is selected to handle operating conditions at a first position of the article where the first portion is located and the second dominant property is selected to handle operating conditions at a second position of the article where the second portion is located.

A method for constructing a nozzle ring for a turbocharger turbine nozzle includes the steps of: providing a nozzle ring in the form of an annular flat disk, the nozzle ring having a first face and an opposite second face; forming a plurality of circumferentially spaced circular bores extending through the nozzle ring from the first face to the second face; providing a plurality of vanes, each vane having a circular vane shaft extending from one end of the vane; inserting the vane shafts respectively into the bores in the nozzle ring from said first face thereof and orienting each vane to achieve a desired setting angle for the vane; and rigidly affixing the vane shafts to the nozzle ring to fix the vanes at the desired setting angles.

A method for constructing a nozzle ring for a turbocharger turbine nozzle includes the steps of: providing a nozzle ring in the form of an annular flat disk, the nozzle ring having a first face and an opposite second face; forming a plurality of circumferentially spaced circular bores extending through the nozzle ring from the first face to the second face; providing a plurality of vanes, each vane having a circular vane shaft extending from one end of the vane; inserting the vane shafts respectively into the bores in the nozzle ring from said first face thereof and orienting each vane to achieve a desired setting angle for the vane; and rigidly affixing the vane shafts to the nozzle ring to fix the vanes at the desired setting angles.

A method of fabricating an airfoil preform for a turbine engine by selective melting on a bed of powder, the preform including an airfoil and a removable support secured to the airfoil, the airfoil being fabricated layer by layer from a first edge to a second edge of the airfoil, the method including fabricating the removable support and the airfoil, the removable support being for securing to a fabrication platform and to a portion of a face of the airfoil situated near the first edge and facing the fabrication platform. The face of the airfoil facing the fabrication platform includes a flat extending away from the face, the flat being present over a portion of the face that is situated outside the first edge, the support being secured to the flat or both to the flat and to the portion of the face that is situated outside the first edge.

An airfoil vane includes an airfoil section which includes an outer wall that defines an internal cavity. A baffle is situated in the internal cavity. The baffle includes a leading edge portion and a trailing edge portion which is bonded to the leading edge portion at a joint. The leading edge portion and the trailing edge portion define an internal cavity therewithin. Both the leading edge portion and the trailing edge portion include a plurality of cooling holes which are configured to provide cooling air to the airfoil outer wall. The trailing edge portion is formed of sheet metal and the leading edge portion is formed of non-sheet-metal. A method of making a baffle for a vane arc segment and a method of assembling a ceramic matrix composite airfoil vane are also disclosed.

An airfoil vane includes an airfoil section which includes an outer wall that defines an internal cavity. A baffle is situated in the internal cavity. The baffle includes a leading edge portion and a trailing edge portion which is bonded to the leading edge portion at a joint. The leading edge portion and the trailing edge portion define an internal cavity therewithin. Both the leading edge portion and the trailing edge portion include a plurality of cooling holes which are configured to provide cooling air to the airfoil outer wall. The trailing edge portion is formed of sheet metal and the leading edge portion is formed of non-sheet-metal. A method of making a baffle for a vane arc segment and a method of assembling a ceramic matrix composite airfoil vane are also disclosed.