Abstract: An apparatus for depositing a coating on a part comprises: a chamber; a source of the coating material, positioned to communicate the coating material to the part in the chamber; a plurality of thermal hoods; and means for moving a hood of the plurality of thermal hoods from an operative position and replacing the hood with another hood of the plurality of hoods.

Abstract: A system for measuring a temperature of a rotating workpiece comprises a deposition chamber, a crucible within the deposition chamber, an energy source, a drive system, a temperature sensor, first and second sensor wires, a dynamic electrical connection, and a control system. The crucible is configured to hold a deposition feedstock material. The energy source is configured to evaporate the deposition feedstock material. The drive system is configured to rotate the workpiece such that the evaporated deposition feedstock material can impinge the rotating workpiece. The temperature sensor is configured to sense the temperature of the rotating workpiece. The first and second sensor wires are electrically connected to the temperature sensor. The dynamic electrical connection is configured to electrically communicate the signal indicative of the sensed temperature from the rotatable workpiece holder to the stationary portion.

Abstract: A thermal barrier coating for a turbine engine component contains neodymia, optionally alumina, and zirconia. The thermal barrier coating has resistance to CMAS attack and a low thermal conductivity.

Abstract: A thermal barrier coating for a turbine engine component contains neodymia, optionally alumina, and zirconia. The thermal barrier coating has resistance to CMAS attack and a low thermal conductivity.

Abstract: A deposition apparatus (20) comprising: a chamber (22); a process gas source (62) coupled to the chamber; a vacuum pump (52) coupled to the chamber; at least two electron guns (26); one or more power supplies (30) coupled to the electron guns; a plurality of crucibles (32,33,34) positioned or positionable in an operative position within a field of view of at least one said electron gun; and a part holder (170) having at least one operative position for holding parts spaced above the crucibles by a standoff height H. The standoff height H is adjustable in a range including at least 22 inches.

Abstract: A coating system for coating a part (10), such as a turbine blade or vane, has a mask (14) positioned adjacent to a first portion (16) of the part (10) to be coated and a mechanism (30) for moving the mask (14) relative to the part (10). The mechanism (30) may be a gear mechanism or a magnetic mechanism.

Abstract: A deposition apparatus (20) comprising: a chamber (22); a process gas source (62) coupled to the chamber; a vacuum pump (52) coupled to the chamber; at least two electron guns (26); one or more power supplies (30) coupled to the electron guns; a plurality of crucibles (32,33,34) positioned or positionable in an operative position within a field of view of at least one said electron gun; and a part holder (170) having at least one operative position for holding parts spaced above the crucibles by a standoff height H. The standoff height H is adjustable in a range including at least 22 inches.

Abstract: An apparatus for use in a coating process includes a chamber, a crucible configured to hold a coating material in the chamber, an energy source operable to heat the interior of the chamber, a coating envelope situated with respect to the crucible, and at least one gas manifold located near the coating envelope. The at least one gas manifold is configured to provide a gas screen between the coating envelope and the crucible.

Abstract: A thermal barrier coating for a turbine engine component contains neodymia, optionally alumina, and zirconia. The thermal barrier coating has resistance to CMAS attack and a low thermal conductivity.

Abstract: A thermal barrier coating for a turbine engine component contains neodymia, optionally alumina, and zirconia. The thermal barrier coating has resistance to CMAS attack and a low thermal conductivity.

Abstract: The thermal barrier coating system comprises a matrix of a first chemistry with multiple embedded second phases of a second chemistry. The matrix comprises a stabilized zirconia. The second regions comprise at least 40 mole percent of oxides having the formula Ln2O3, where Ln is selected from the lanthanides La through Lu, Y, Sc, In, Ca, and Mg with the balance zirconia (ZrO2), hafnia (HfO2), titania (TiO2), or mixtures thereof. The second phases have a characteristic thickness (T6) of less than 2.0 micrometers (?m). The spacing between second phases has a characteristic thickness (T5) of less than 8.0 micrometers (?m).

Abstract: A method for use in a coating process includes pre-heating a substrate in the presence of a coating material and shielding the substrate during the pre-heating from premature deposition of the coating material by establishing a gas screen between the substrate and the coating material. An apparatus for use in a coating process includes a chamber, a crucible that is configured to hold a coating material in the chamber, an energy source operable to heat the interior of the chamber, a coating envelope situated with respect to the crucible, and at least one gas manifold located near the coating envelope. The at least one gas manifold is configured to provide a gas screen between the coating envelope and the crucible. A second manifold provides gas during a later coating deposition to compress a vapor plume of the coating material and focus the plume on the substrate to increase deposition rate.

Abstract: A thermal barrier coating for a turbine engine component contains neodymia, optionally alumina, and zirconia. The thermal barrier coating has resistance to CMAS attack and a low thermal conductivity.

Abstract: A coating-substrate combination includes: a Ni-based superalloy substrate comprising, by weight percent: 2.0-5.1 Cr; 0.9-3.3 Mo; 3.9-9.8 W; 2.2-6.8 Ta; 5.4-6.5 Al; 1.8-12.8 Co; 2.8-5.8 Re; 2.8-7.2 Ru; and a coating comprising, exclusive of Pt group elements, by weight percent: Ni as a largest content; 5.8-9.3 Al; 4.4-25 Cr; 3.0-13.5 Co; up to 6.0 Ta, if any; up to 6.2 W, if any; up to 2.4 Mo, if any; 0.3-0.6 Hf; 0.1-0.4 Si; up to 0.6 Y, if any; up to 0.4 Zr, if any; up to 1.0 Re, if any.

Abstract: An apparatus for use in a physical vapor deposition coating process includes a chamber, a crucible configured to hold a ceramic coating material in the chamber, an energy source operable to heat the interior of the chamber, a fixture for holding at least one substrate in the chamber, an actuator operable to rotate the fixture, and a controller configured to establish a plume of the ceramic coating material in the chamber to deposit the ceramic coating material from the plume onto the at least one substrate and form a ceramic coating thereon, and during the deposition, rotate the at least one substrate at a rotational speed selected with respect to deposition rate of the ceramic coating material onto the at least one substrate.

Abstract: A method for use in a physical vapor deposition coating process includes depositing a ceramic coating material from a plume onto at least one substrate to form a ceramic coating thereon, and during the deposition, rotating the at least one substrate at rotational speed selected with respect to deposition rate of the ceramic coating material onto the at least one substrate.

Abstract: An embodiment of a method includes retaining a first workpiece and a second workpiece selectively on a workpiece fixture disposed within a deposition chamber. The workpiece fixture includes tooling including a first workpiece holder, a second workpiece holder, and a first hollow wall. The first workpiece is separated from the second workpiece using the first hollow wall. Energy is selectively applied and directed within the deposition chamber, from an energy source toward a first crucible, the first crucible including a plurality of walls defining an upper recess contiguous with, and disposed directly above a first lower recess, at least the upper recess open to an interior of the deposition chamber. During the step of selectively applying and directing energy, a gas valve is controlled to maintain a partial vacuum in the deposition chamber of greater than 2 Pa to control a size and overlap of at least one coating zone formed around each of the at least one workpiece.

Abstract: A method includes forming a multi-layered ceramic barrier coating under a chamber pressure of greater than 1 Pascals. In the method, low- and high-dopant ceramic materials are evaporated using input evaporating energies that fall, respectively, above and below a threshold for depositing the materials in a columnar microstructure (low-dopant) and in a branched columnar microstructure (high-dopant).

Abstract: A thermal barrier coating is applied to a turbine engine component having a substrate. The thermal barrier coating has a first layer which has a strain tolerant columnar microstructure at an interface with the substrate for spallation resistance and a second layer which is porous conduction and radiation thermally resistant at an outer surface of the thermal barrier coating.

Abstract: An apparatus for depositing a coating on a part comprises: a chamber; a source of the coating material, positioned to communicate the coating material to the part in the chamber; a plurality of thermal hoods; and means for moving a hood of the plurality of thermal hoods from an operative position and replacing the hood with another hood of the plurality of hoods.