Abstract: Systems (100) and methods (1000) for additively manufacturing or repairing a component from a base material (10). The system may include a laser metal deposition (LMD) system (200) operably connected to a means for cooling (300) the base material during laser processing of additive materials deposited in a melt pool on the base material. The LMD system includes a laser energy source (202) configured to direct laser energy towards the base material to form the melt pool thereon and to processes the deposited additive materials to form layers on the base material upon solidification. The means for cooling may be configured to cool the base material to within a cooling temperature range during the LMD process, which results in, e.g., a cooling/freezing effect. This cooling effect shortens the solidification period during laser processing and allows for weld heat to be released from the base material.

Abstract: A gas turbine engine component (50, 100, 150, 160, 174, 206, 236), including: a surface (54) subject to loss caused by a wear instrument during operation of the component in a gas turbine engine and a performance feature (80, 82, 102, 152, 162, 172, 200, 230) associated with the surface. The surface and the performance feature interact in a manner that changes with the loss such that a change in performance of the gas turbine engine resulting from the loss is mitigated.

Abstract: A gas turbine engine component (50, 100, 150, 160, 174, 206, 236), including: a surface (54) subject to loss caused by a wear instrument during operation of the component in a gas turbine engine and a performance feature (80, 82, 102, 152, 162, 172, 200, 230) associated with the surface. The surface and the performance feature interact in a manner that changes with the loss such that a change in performance of the gas turbine engine resulting from the loss is mitigated.

Abstract: A method of repairing or manufacturing a superalloy component (50) by depositing a plurality of layers (22, 24, 26, 28) of additive superalloy material having a property that is different than an underlying original superalloy material (30). The property that is changed between the original material and the additive material may be material composition, grain structure, principal grain axis, grain boundary strengthener, and/or porosity, for example. A region (60) of the component formed of the additive material will exhibit an improved performance when compared to the original material, such as a greater resistance to cracking (58).

Abstract: A gas turbine engine component (50, 100, 150, 160, 174, 206, 236), including: a surface (54) subject to loss caused by a wear instrument during operation of the component in a gas turbine engine and a performance feature (80, 82, 102, 152, 162, 172, 200, 230) associated with the surface. The surface and the performance feature interact in a manner that changes with the loss such that a change in performance of the gas turbine engine resulting from the loss is mitigated.

Abstract: A process and apparatus for solid freeform fabrication and repair of components on existing bodies (such as turbine blades), the innovative process and apparatus as well as the resultant product having the following advantages: a) Can build on existing 3-D surfaces. Not limited to horizontal flat surfaces, b) Usable for metals that are difficult to weld. c) Robust process that is adaptable to new damage modes. d) No shielding of the melt pool by inert gas is needed. e) Wide range of powder sizes.

Abstract: A superalloy component such as a gas turbine engine blade (40) having a ceramic thermal barrier coating (41) is repaired using a textured repair foil (30). A degraded region of the thermal barrier coating is removed (14) and the underlying superalloy material surface is prepared (16) for re-coating. The repair foil is includes a layer of boron-free braze material (34) and a layer of superalloy material (32) having a textured surface (36). The foil is brazed (18) to the prepared surface during a solution heat treatment effective to homogenize the braze (20). A new area of thermal barrier coating (46) is applied over the foil with a bond that is enhanced by the texturing of the foil surface.

Abstract: A gas turbine engine component (50, 100, 150, 160, 174, 206, 236), including: a surface (54) subject to loss caused by a wear instrument during operation of the component in a gas turbine engine and a performance feature (80, 82, 102, 152, 162, 172, 200, 230) associated with the surface. The surface and the performance feature interact in a manner that changes with the loss such that a change in performance of the gas turbine engine resulting from the loss is mitigated.

Abstract: A method, including: detecting in a nondestructive manner a marker (10, 12, 50, 70, 76, 78) that is fully submerged in a substrate (14) to obtain spatial information about the marker; detecting in a nondestructive manner the marker after a period of time to obtain a change in the spatial information; and using the change in the spatial information to determine a change in a dimension (30) of the substrate. The method may be used to measure creep in a gas turbine engine component.

Abstract: Refurbishment of hot gas path components of gas turbine engines can now be performed locally in lieu of the traditional use of a specialized fixed regional repair facility. A mobile manufacturing platform (10) is provided with the capability to inspect and to repair ceramic coated superalloy alloy components, including the ability to perform flux assisted laser processing (68) of powdered materials. The mobile platform may include a powder mixing capability (32) for custom on-site mixing of proprietary powder compositions from a standardized powder inventory (34). A communications element (36) conveys the proprietary powder compositions from a remote home office location (38). Superalloy components can now be repaired (62) or fabricated (80) on-site by qualified technicians rather than certified welders. The mobile platform may be self-powered by a vehicle hybrid power unit or a renewable energy source.

Abstract: A superalloy component such as a gas turbine engine blade (40) having a ceramic thermal barrier coating (41) is repaired using a textured repair foil (30). A degraded region of the thermal barrier coating is removed (14) and the underlying superalloy material surface is prepared (16) for re-coating. The repair foil is includes a layer of boron-free braze material (34) and a layer of superalloy material (32) having a textured surface (36). The foil is brazed (18) to the prepared surface during a solution heat treatment effective to homogenize the braze (20). A new area of thermal barrier coating (46) is applied over the foil with a bond that is enhanced by the texturing of the foil surface.

Abstract: A superalloy component such as a gas turbine engine blade (40) having a ceramic thermal barrier coating (41) is repaired using a textured repair foil (30). A degraded region of the thermal barrier coating is removed (14) and the underlying superalloy material surface is prepared (16) for re-coating. The repair foil is includes a layer of boron-free braze material (34) and a layer of superalloy material (32) having a textured surface (36). The foil is brazed (18) to the prepared surface during a solution heat treatment effective to homogenize the braze (20). A new area of thermal barrier coating (46) is applied over the foil with a bond that is enhanced by the texturing of the foil surface.

Abstract: A process and apparatus for solid freeform fabrication and repair of components on existing bodies (such as turbine blades), the innovative process and apparatus as well as the resultant product having the following advantages: a) Can build on existing 3-D surfaces. Not limited to horizontal flat surfaces, b) Usable for metals that are difficult to weld. c) Robust process that is adaptable to new damage modes. d) No shielding of the melt pool by inert gas is needed. e) Wide range of powder sizes.

Abstract: A preform (22, 22A-U) containing metal (32, 34) and flux (33) for forming a metal layer to be added to a component being repaired or additively manufactured. The metal may be constrained in the preform in a distribution that forms a shape of a sectional layer or a surface repair of a component in response to an energy beam (58) that melts the preform. The preform is placed on a working surface (42), which may be a previously formed layer (42A-C) in additive manufacturing, or may be an existing component surface (122) for repair The preform is then melted by the energy beam (58) to form a new integrated layer (40A-F) on the component with an over-layer of slag (56) that shields and insulates the melt pool (54) and the solidifying layer The slag is removed, and a subsequent layer may be added.

Abstract: A method for forming a textured bond coat surface (48) for a thermal barrier coating system (44) of a gas turbine component (34). The method includes selectively melting portions of a layer of alloy particles (16) with a patterned energy beam (20) to form successive layers of alloy material (16?, 16?) until a desired surface geometric feature (26) is achieved. The energy beam pattern may be indexed between layers to form a protruding undercut (28) in the geometric feature. The patterned energy beam may be formed by directing laser energy from a diode laser (30) through a cartridge filter (32). Particles of a flux material (18) may be melted along with the alloy particles to form a protective layer of slag (22) over the melted and cooling alloy material.

Abstract: A method of repairing or manufacturing a superalloy component (50) by depositing a plurality of layers (22, 24, 26, 28) of additive superalloy material having a property that is different than an underlying original superalloy material (30). The property that is changed between the original material and the additive material may be material composition, grain structure, principal grain axis, grain boundary strengthener, and/or porosity, for example. A region (60) of the component formed of the additive material will exhibit an improved performance when compared to the original material, such as a greater resistance to cracking (58).

Abstract: A method of repairing a superalloy component (22) wherein a section (24) of the component containing a plurality of service-induced cracks (18, 20) is removed, then a replacement section (26) of superalloy material is installed with a structural braze joint (28) containing no boron or silicon. The replacement section may have a textured surface ((38) to enhance bonding with an overlying thermal barrier coating (42). The replacement section may be pre-formed to standardized dimensions in expectation of a typical service-induced crack pattern, and the removed section excavated accordingly. The interface between the replacement section and the component may be shaped to provide a mechanical interlock there between.

Abstract: A hollow turbine engine component with complex internal features can include a first region and a second, high resolution region. The first region can be defined by a first ceramic core piece formed by any conventional process, such as by injection molding or transfer molding. The second region can be defined by a second ceramic core piece formed separately by a method effective to produce high resolution features, such as tomolithographic molding. The first core piece and the second core piece can be joined by interlocking engagement that once subjected to an intermediate thermal heat treatment process thermally deform to form a three dimensional interlocking joint between the first and second core pieces by allowing thermal creep to irreversibly interlock the first and second core pieces together such that the joint becomes physically locked together providing joint stability through thermal processing.

Abstract: A turbine engine component, such as a turbine blade or vane, with complex internal features can be cast using a core having a first region with normal resolution features and a second region with high resolution features. The core can be formed from a single structure. Alternatively, the first region can be defined by a first ceramic core piece, which can be formed by any conventional process, such as by injection molding or transfer molding. The second region can be defined by a second ceramic core piece formed separately by a method effective to produce high resolution features, such as tomo lithographic molding. The first core piece and the second core piece can be joined by interlocking engagement, such as by male and female dovetails. The high resolution features can be effective to produce high efficiency internal cooling features in the cast component.