Abstract: Disclosed herein is a method comprising mixing a carrier liquid with particles and/or with a particle precursor to form a suspension or solution respectively; where the particles comprise a metal oxide; and where the particle precursor comprises a metal salt; injecting the suspension or solution through a plasma flame; and depositing the particles and/or the particle precursor onto a substrate to form an first abradable coating; where the first abradable coating comprises a plurality of cracks or voids that are substantially perpendicular to the substrate surface, where the substrate is a hub surface of a gas turbine engine or where the substrate is a cantilever stator.

Abstract: A deposition apparatus comprises: an infeed chamber; a preheat chamber; a deposition chamber; and optionally at least one of a cooldown chamber and an outlet chamber. At least a first of the preheat chamber and the cooldown chamber contains a buffer system for buffering workpieces respectively passing to or from the deposition chamber.

Abstract: Disclosed herein is a method comprising mixing a carrier liquid with particles and/or with a particle precursor to form a suspension or solution respectively; where the particles comprise a metal oxide; and where the particle precursor comprises a metal salt; injecting the suspension or solution through a plasma flame; and depositing the particles and/or the particle precursor onto a substrate to form an first abradable coating; where the first abradable coating comprises a plurality of cracks or voids that are substantially perpendicular to the substrate surface, where the substrate is a hub surface of a gas turbine engine or where the substrate is a cantilever stator.

Abstract: In accordance with the present disclosure, there is provided a process for limiting a critical stabilizer content in coatings comprising placing a source coating material in a crucible of a vapor deposition apparatus having a coating chamber, the source coating material having compositional range of LnO1.5 comprising a single cation mol % of 30-50% relative to zirconia (ZrO2), where Ln=La, Pr, Nd, Sm, Eu, Gd, and Tb and combinations thereof; energizing the source coating material with an electron beam that delivers a power density to the material in the crucible forming a vapor cloud from the source coating material; and depositing the source coating material as a coating system onto a surface of a work piece.

Abstract: An electron beam vapor deposition process for depositing coatings includes placing a source coating material in a crucible of a vapor deposition apparatus; energizing the source coating with an electron beam raster pattern that delivers a controlled power density to the material in the crucible forming a vapor cloud from the source coating material; and depositing the source coating material onto a surface of a work piece.

Abstract: A vapor deposition system fixture comprises an arm, a rake, a crown gear bearing assembly, a workpiece holder, a thermocouple, and a contact ring assembly. The crown gear bearing assembly is attached to and rotatably engaged with the rake and includes stationary portion and rotating portions. The workpiece holder is configured to rotate with the rotating portion. The thermocouple is configured to rotate with the workpiece holder. The contact ring assembly comprises a housing, a cover, first and second rotating contact rings, and first and second stationary contact rings. The housing is attached to at least one of the arm and the rake. The first and second rotating contact rings are electrically connected to the thermocouple. The first and second stationary contact rings surround the rotating ring. The first and second stationary contact rings are configured to receive an electrical signal from the first and second rotating contact rings.

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 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 clinch-in fastener with a cylindrical body having a top, a bottom, sides and an axial internal bore. The fastener has a single shank at the bottom end of the body having a top surface orthogonal to the bore and a chamfer tapering to the bottom of the body. The top surface of the shank is adapted for receiving the cold flow of material surrounding a receiving hole of a workpiece. The shank may have a plurality of notches in its outermost edge that extend through both the top surface of the shank and the chamfer. The bore of the fastener extends completely through the fastener body from top to bottom and may be threaded. A fastener installation system having a tool with means for affixation to a rotary and vertically reciprocal element of an industrial machine. The tip of the tool has a distal end face with at least one arcuate displacer adapted for deforming a workpiece as the tool rotates and is pressed against the workpiece. A bore within the tip holds a fastener installed by the tool.

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 fastener with a tapered head that frictionally mates with a tapered hole in a punched sheet. Frictional attachment is achieved with the fastener head remaining flush with the top of the panel. If a second panel of softer material is placed underneath against the backside of the first panel, in the same pressing step clinch features on the shank of the fastener attach to the second panel and attach the two sheets face-to-face. Attachment of the tapered head with the top panel exploits two different attachment phenomena: a locking taper and, depending on the choice of materials such as stainless steel, attachment by galling.

Abstract: A process for coating a gas turbine engine airfoil comprising coupling the airfoil having an internal surface with a chamber, the chamber configured to perform atomic layer deposition; injecting a first reactant into the chamber; forming a first monolayer gas thin film on the internal surface; removing the first reactant from the chamber; injecting a second reactant into the chamber; forming a reaction with the first monolayer gas film to form a solid thin film; removing the second reactant from the chamber; and forming a protective barrier coating on said internal surface.

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 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 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 two-part fastener with an insert and a compression sleeve. The insert is an internally-threaded fastener intended to be installed into a hole of a very hard panel. The insert itself is relatively hard with a knurled outer barrel portion and a flange at the bottom. A compression sleeve is made of relatively soft material and is preassembled around the barrel of the insert by friction fit. Upon installation into a panel with a blind hole having parallel sides, the compression sleeve is pressed into the panel and deforms outwardly between the insert and the side wall of the hole. Friction between the compression sleeve and the wall of the hole prevents torque out and pull out of the fastener from the panel.