Abstract: A low pressure turbine shaft installation tool including a disk having an inner diameter and an outer diameter; the disk has an upper surface with a lower surface opposite the upper surface; a set of disk through holes are arrayed about the disk; and at least one threaded fastener is associated with at least one of the disk through holes and the at least one threaded fastener in operative communication with the upper surface.

Abstract: An ultrasonic impact grinding assembly includes a vessel having an open top disposed opposite a base and configured to contain an abrasive slurry, at least one mixing mechanism disposed in the vessel, a fixture disposed on the base of the vessel and configured to retain a workpiece for ultrasonic impact grinding within the abrasive slurry, and an ultrasonic impact grinding machine having a tool tip disposed to contact the abrasive slurry in the vessel during an ultrasonic impact grinding operation.

Abstract: A coated fiber structure for use in a ceramic matrix composite comprises a fiber and a fiber coating arrangement applied to and at least partially circumscribing the fiber. The fiber coating arrangement comprises a first boron nitride layer comprising exfoliated hexagonal boron nitride, a silicon carbide layer extending at least partially coaxially with and in direct contact with the first boron nitride layer, and a second boron nitride layer radially opposite the silicon carbide layer, with respect to the first boron nitride layer.

Abstract: An electrodeposited nickel-chromium-aluminum (Ni—Cr—Al) composite including nickel-chromium alloy and aluminum, and alloys or compounds formed by Al, Cr and Ni applied on turbine components comprises from 2 to 50 wt % chromium, from 0.1 to 6 wt % aluminum, and a remaining balance of nickel, wherein the Ni—Cr—Al composite is heat-treated to form an aluminum compound and to restore materials lost during repair processes of the turbine components.

Abstract: A mandrel includes a mandrel body upon which to build ceramic matrix composite (“CMC”) yarns to provide a shear tube for building up an airfoil from CMC fabric layers. The mandrel body formed of at least two mandrel parts interfitting to define a desired shape for the shear tube, and such that after formation of the airfoil the at least two parts of the mandrel body can be separately removed from the shear tube in order to facilitate removal. A method is also disclosed.

Abstract: A vane arm has: a first end and a second end; a shank extending between the first end and the second end and having a first face and a second face; a first hole in the shank proximate the first end; a second hole in the shank proximate the second end; and a transverse groove in the first face intersecting the second hole. The groove has: a base; a first open end and a second open end; a first side face and a second side face. An asymmetry between the groove first side face and second side face provides for uniquely angularly registering the vane arm to a shaft.

Abstract: A turbine engine airfoil element has: an airfoil having: an exterior surface including a pressure side and a suction side; and a plurality of spanwise passageways including: a plurality of main body passageways along a camber line; and a plurality of skin passageways between the main body passageways and the exterior surface, wherein; the skin passageways have: a downstream direction from one or more inlets; a skin side; first and second lateral rounded transitions from the skin side; a parting line; and a longitudinally spaced plurality of protrusions from the skin side; and the protrusions have a height profile having: first and second tapering portions tapering from a maximum height, the first and second portions extending downstream; and first and second inwardly concave transitions to the skin passageway lateral rounded transitions.

Abstract: Examples described herein provide a method that includes comparing features in an image of a part with features of models in a database and creating a list of candidate models for the part. The method further includes rendering a three-dimensional (3D) model at a pose/scale of an imaging system to generate a synthetic image that contains features of the part. The method further includes creating a part representation based on the features of the part, wherein the part representation depicts a defect of the part. The method further includes classifying a region of the part based on a set of rules for the part to determine whether the defect is within an allowable tolerance for the part.

Abstract: A feather seal arrangement for a ceramic matrix composite (CMC) blade outer air seal (BOAS) of a turbine engine includes a CMC BOAS segment having a specific geometry and a first feather seal. The CMC BOAS segment includes a shoe having a flowpath side, an opposing non-flowpath side, and first and second matefaces extending axially between the flowpath side and the non-flowpath side from an upstream leading edge to a downstream trailing edge. One or more support flanges extend substantially transverse from the non-flowpath side. A geometry of the CMC BOAS segment allows a substantially flat first feather seal surface to be disposed on the non-flowpath side adjacent and substantially transverse to the first mateface. A first feather seal is disposed atop the non-flowpath side on the first feather seal surface and extends to an adjacent feather seal surface of an adjacent CMC BOAS segment.

Abstract: A ceramic matrix composite (CMC) airfoil component can be made by forming a stack of fabric plies with a plurality of plies adhered together with a tackifier. The stack of fabric plies is machined into an airfoil shape to form an airfoil core with an orientation of the fabric plies selected based upon strength and/or performance requirements of the airfoil component. The airfoil core is then overwrapped with an outer mold layer formed of one or more plies of fabric to form a preform. The preform is then densified, such as via melt infiltration (MI) and/or chemical vapor infiltration (CVI), to form the CMC airfoil component such as a turbine vane or a turbine blade.

Abstract: A process for fabricating a melt-infiltrated ceramic matrix composite comprising fabricating a ceramic fiber preform comprising a fiber, a fiber tow, or both; depositing a structural support material coating on the fiber, the fiber tow, or both to form a partially densified ceramic matrix composite comprising at least one pore, at least one porous network or both; depositing a fiber protection material coating on the fiber, the fiber tow, or both; infiltrating a slurry composition comprising a solvent into the pore, the porous network or both; drying the partially densified ceramic matrix composite to remove the solvent; depositing a sacrificial material coating on the fiber protection material coating; and, melt-infiltrating a molten infiltrant into the partially densified ceramic matrix composite to form a melt-infiltrated ceramic matrix composite.

Abstract: A process of fabricating at least one channel in a ceramic-containing material comprising providing at least one ceramic-containing material having a first major surface, a second major surface opposite the first major surface, at least one first side surface, and at least one second side surface adjacent the first side surface; removing at least a portion of material from the first major surface or the second major surface of the ceramic-containing material and form one or more structural features; providing at least one metal cover plate; disposing the metal cover plate adjacent the ceramic-containing material and covering the structural features; and, securing together the ceramic-containing material and the metal cover plate.

Abstract: A method for coating a substrate includes spraying a combination of powders. The combination of powders includes: Hf0.5Si0.5O2; Zr0.5Si0.5O2; and, optionally, at least one of HfO2 and ZrO2. A molar ratio of said Hf0.5Si0.5O2 and HfO2 combined to said Zr0.5Si0.5O2 and ZrO2 combined is from 2:1 to 4:1. A molar ratio of said Hf0.5Si0.5O2 to said HfO2 is at least 1:3.

Abstract: A preform comprising a first sub-laminate comprising a plurality of layers and a second sub-laminate comprising a plurality of layers. The first sub-laminate comprises a first unit cell comprising a first volume fraction of tows, where the first volume fraction of tows comprise first tows having a first tow spacing between successive first tows. The second sub-laminate comprises a second unit cell comprising a second volume fraction of tows, where the second volume fraction of tows comprise second tows having a second tow spacing between successive second tows. The first volume fraction of tows in the first unit cell is equal to the second volume fraction of tows in the second unit cell. The second tow spacing is less than the first tow spacing.

Abstract: A method of isolating hydrogen from water in a reactor includes charging a centrifuge with water via an inlet including an inlet valve. The centrifugal centrifuge is situated in a protective chamber. The method also includes heating the centrifuge such that at least some of the water splits into hydrogen and oxygen, rotating the centrifuge within the protective chamber such that the hydrogen and oxygen separate within the centrifuge according to their molecular mass, and drawing off at least some of the hydrogen from the centrifuge via an outlet including an outlet valve.

Abstract: A resonance inspection system a processing system configured to process resonance data including a vibratory response signature of a component over a portion of a frequency range of the vibratory response signature to generate a plurality of different resonance spectra waveforms of the vibratory response signature. The plurality of different resonance spectra waveforms includes a first resonance spectra waveform and a second resonance spectra waveform. The processing system is further configured to detrend the first resonance spectra waveform and the second resonance spectra waveform and identify a presence or an absence of a structural mode of the component using the first resonance spectra waveform and the second resonance spectra waveform.

Abstract: A ceramic matrix composite (CMC) blade outer air seal (BOAS) segment includes a preform having a base layup formed of one or more fabric plies folded to form a first rib portion, a shoe portion having an upstream fold edge and a downstream fold edge, and a second rib portion. One or more pre-densified CMC tubes are disposed circumferentially between the first rib portion and the upstream fold edge and between the second rib portion and the downstream fold edge, respectively. An outer wrap formed of one or more fabric plies is disposed to overwrap the first rib portion, the one or more pre-densified CMC tubes disposed circumferentially between the first rib portion and the upstream fold edge, the upstream fold edge, the downstream fold edge, the one or more pre-densified CMC tubes disposed circumferentially between the second rib portion and the downstream fold edge, and the second rib portion.

Abstract: A tooling assembly suitable for use in infiltrating a fibrous preform comprises a perforated fixture having a thickness. The fixture comprises a plurality of holes extending through the thickness, and a first counterbore aligned with at least one hole of the plurality of holes, the first counterbore having a first length extending partially through the thickness.

Abstract: An aircraft system includes an environmental control system and a propulsion system. The propulsion system includes a compressor section, a combustor section, a turbine section, a bypass flowpath, an air circuit, a working fluid system and a heat exchanger. The bypass flowpath bypasses the compressor section, the combustor section and the turbine section. The air circuit includes a circuit inlet fluidly coupled to the bypass flowpath. The air circuit is configured to direct air received from the bypass flowpath through the circuit inlet to the environmental control system. The working fluid system includes a fluid circuit. The working fluid system is configured to service one or more components of the propulsion system using a liquid working fluid directed through the fluid circuit. The heat exchanger is configured to transfer heat energy between the air in the air circuit and the liquid working fluid in the fluid circuit.

Abstract: Disclosed herein is an article comprising a substrate; an abrasive coating disposed on the substrate; where the abrasive coating comprises a matrix having abrasive grit particles dispersed therein; and a layer of material disposed on the abrasive coating; where the layer of material is a titanium nitride (TiN), boron nitride (BN), titanium-aluminum-nitrides [(TiAl)N], titanium-aluminum-silicon-nitrides [(TiAlSi)N], chromium nitrides (CrN), aluminum oxide (Al2O3), titanium oxide (TiO2), silicon carbo-nitride (SiCN), titanium carbo-nitride (TiCN), or a combination thereof.