Abstract: An alignment tool including a base ring having a base ring inside diameter bounded by a base ring inner surface, the base ring comprising a top surface opposite a bottom surface; a stabilizer ring having a stabilizer ring inside diameter bounded by a stabilizer ring inner surface, the stabilizer ring comprising a stabilizer ring upper surface opposite a stabilizer ring lower surface; a biasing member in operative communication between the base ring top surface and the stabilizer ring lower surface; a gap formed between the base ring and the stabilizer ring; and at least one pull tab formed from the base ring.

Abstract: A power and thermal management system thermal bus vapor cycle architecture including a bypass duct formed between a gas turbine inner fan duct and a gas turbine outer fan duct; a condenser coil located within the bypass duct, the condenser coil being configured as an annulus disk shape heat exchanger; at least one evaporator coil fluidly coupled to the condenser coil and located within the bypass duct upstream of the condenser coil relative to a bypass air flow direction; a gearbox in operative communication with the gas turbine engine; and a variable speed compressor in operative communication with the gearbox, the variable speed compressor being fluidly coupled with the at least one evaporator coil and the condenser coil.

Abstract: A metallic sheath for a composite fan blade includes a body comprising a leading edge portion configured to cover a leading edge of the blade; a top surface adjacent the leading edge; an extension portion proximate the top surface configured to cover a portion of a tip of the blade along an intermediate chord length; an encapsulation portion opposite the top surface configured to couple directly with the tip of the blade; a sheath suction side flank configured to overlap a suction side of the blade; a sheath pressure side flank opposite the suction side flank configured to overlap a pressure side of the blade; and an insulator coupled between the encapsulation portion and the tip of the blade.

Abstract: A vane assembly has a vane and an arm having first and second holes in its shank proximate first and second ends. First and second tabs project laterally opposite each other from the shank proximate the second end and have: a bend; and a distal portion distally of the bend overlapping and spaced apart from and having a face facing the shank second face. The second tab distal portion partially overlaps the first tab distal portion. A third hole in the second tab distal portion overlaps a distal end edge of the first tab and has proximal and distal edges. A vane shaft has a first facet abutting the proximal edge of the third hole, a second facet abutting the first tab, and a third facet circumferentially between the first facet and the second facet and abutting at least one of the first tab and the second tab.

Abstract: A plug assembly for plugging one or more ports of a gas turbine engine, the plug assembly including: a sheath including: an inner end; an outer end located opposite the inner end; and a sheath through-passage extending from the outer end to the inner end; a connector body passing through the sheath through-passage, the connector body comprising a rotatable joint; a cover operably connected to the connector body via the rotatable joint; a biasing mechanism configured to apply a force to the connector body; and a top housing comprising a bottom end and a connector passageway extending from the bottom end a top end of the top housing, wherein the biasing mechanism abuts the bottom end or is located in the cavity at the bottom end, and wherein the connector body passes through the connector passageway.

Abstract: A wall assembly for use in a combustor of a gas turbine engine, the wall assembly including: a support shell; a liner panel; and an annular grommet extending from the liner panel, the annular grommet defining a dilution passage and the annular grommet extends through an opening in the support shell when the support shell and the liner panel are secured to each other, the annular grommet having a top portion that defines a portion of a periphery of the dilution opening; and a backstop extending from the top portion of the annular grommet, the backstop defining another portion of the periphery of the dilution passage and the backstop extending through and above the opening in the support shell when the liner panel is secured to the support shell.

Abstract: A vane arm has first and second holes in its shank proximate first and second ends. First and second tabs each project laterally opposite each other from the shank proximate the second end and have: a bend; and a distal portion distally of the bend. The second tab distal portion partially overlaps the first tab distal portion. A third hole is in the second tab distal portion overlapping a distal end edge of the first tab and having a proximal edge and a distal edge. At least along a region across an axis of the second hole, the third hole distal edge and proximal edge diverge from each other in a direction toward the first end and/or the first tab distal end edge and the third hole proximal edge diverge from each other in a direction toward the first end.

Abstract: A ceramic matrix composite laminate comprises a ceramic matrix that encapsulates a plurality of layers. Each layer comprises fibers. Each layer comprises a plurality of fill fibers and a plurality of warp fibers or a plurality of bias fibers. The outermost layer contains a different concentration of fibers per unit volume than a layer located near an interior of the ceramic matrix composite laminate. A gradient in the number of fibers exists between the outermost layer and the layer located at the interior of the ceramic matrix composite laminate, or a combination thereof. A combined ceramic matrix composite comprises a plurality of composite laminates; wherein each laminate has a different fiber concentration gradient from another laminate that it is in contact with.

Abstract: A propulsion system includes a gas turbine engine, a nacelle, a bifurcation, an electrical assembly, and a thermal management assembly. The gas turbine engine includes a rotational assembly and an engine static structure. The engine static structure houses the rotational assembly. The nacelle forms an annular bypass duct radially between the engine static structure and the nacelle. The bifurcation extends between the engine static structure and the nacelle. The electrical assembly includes an electric machine and a control unit. The electric machine is coupled with the rotational assembly. The control unit is electrically connected to the electric machine. The control unit is disposed within the bifurcation. The thermal management assembly includes a control unit cooling circuit. The control unit cooling circuit is connected in fluid communication with and formed by the control unit. The control unit cooling circuit is disposed within the bifurcation.

Abstract: An applicator assembly for applying a liquid to at least one fastener includes a housing, a vat body, at least one applicator roller pair, and at least one removal roller pair. The housing includes a sidewall assembly. The sidewall assembly extends between and to a bottom end and a top end. The vat body is disposed within the sidewall assembly. The vat body extends between and to a bottom side and a top side. The vat body forms a liquid cavity at the top side. The at least one applicator roller pair is disposed within the liquid cavity. The at least one applicator roller pair includes a first applicator roller and a second applicator roller. The at least one removal roller pair is disposed between the liquid cavity and the top end. The at least one removal roller pair includes a first removal roller and a second removal roller.

Abstract: A method of inspecting an indirectly accessible cavity of a gas turbine engine is provided. The method includes memorizing a guide tube formed of smart metal alloy (SMA) into a bent shape and straightening the guide tube. The method also includes installing a scope, which includes a connecting line to which an inspection element is attached, into the guide tube. The method then includes inserting the guide tube into the gas turbine engine toward a location of the indirectly accessible cavity, heating the guide tube to cause the guide tube to return to the bent shape in order to bring the inspection element into the indirectly accessible cavity and using the inspection element to perform an inspection of the indirectly accessible cavity.

Abstract: A method of manufacturing a fiber reinforced coating. The method includes providing a substrate and plasma spraying a ceramic matrix having fibers encapsulated in a precursor material onto the substrate.

Abstract: A gas turbine engine may include a propulsor section including a propulsor having propulsor blades extending from a propulsor hub. A speed reduction device interconnects a turbine and a propulsor shaft that drives the propulsor. Bearings are positioned on opposite sides of the speed reduction device. A propulsor drive gear module is also disclosed.

Abstract: A method for coating a component of a gas turbine engine includes providing the component having a bond coat and contaminants on a surface of the bond coat; laser treating the surface to remove the contaminants and to produce a cleaned surface on the bond coat; peening the cleaned surface to produce a peened surface on the bond coat, and applying a ceramic coat to the peened surface.

Abstract: A method includes receiving weld data about a weld, and analyzing, using a physics-based model, the weld data to predict a formation of a defect in the weld. The method further includes providing feedback to enable process optimization during a design stage or active control during welding to control a welding machine to correct for and eliminate the formation of the defect in the weld.

Abstract: A propulsion system for an aircraft includes a propulsor rotor, a powerplant, a nacelle and a lockout system. The powerplant is coupled to and configured to drive rotation of the propulsor rotor. An electrical system for the powerplant is configured to receive electrical power from an electrical power source. The nacelle includes an access structure configured to move between a first position and a second position. The access structure at least partially covers the electrical system when in the first position. The access structure is arranged in the first position for propulsion system operation. The access structure is operable to be arranged in the second position for propulsion system maintenance and/or propulsion system inspection. The lockout system is configured to automatically trigger an operation to cut off the electrical power to the electrical system from the electrical power source when the access structure moves away from the first position.

Abstract: A gas turbine engine stator stage has: an inner diameter platform; an outer diameter shroud; and a plurality of airfoils extending between the platform and shroud. The platform has an axially forward end and an axially aft end and an inner diameter (ID) surface. At least one of the platform forward end, aft end, and inner diameter (ID) surface bears a swirl generator for inducing swirl in a leakage flow passing radially inward behind the aft end and forward and then radially outward past the forward end.

Abstract: A gas turbine engine comprises a ring comprising an inner ring and an outer ring that define a gas path therebetween; a vane disposed in the gas path and supported by the inner ring and the outer ring, the vane includes an inner platform, an outer platform, and an airfoil section disposed therebetween, wherein the inner ring and the outer ring include one or more of: a flange designed to abut an opposing flange defined by the inner platform, the outer platform or both, and permit axially aftward movement until abutment occurs to achieve a nominal tolerance mode; a contact surface designed to abut an opposing contact surface defined by the inner platform, the outer platform or both, and permit axially aftward movement until abutment occurs to achieve a nominal tolerance mode; and, an angled contact surface designed to abut an opposing angled contact surface defined by the inner platform, the outer platform or both, and permit axially aftward movement until abutment occurs to achieve a nominal tolerance mode.

Abstract: A start mechanism for a propulsion system including a receptacle in operative communication with a case; at least one portable source of energy disposed within the receptacle; a flow channel fluidly coupled to the receptacle; and a turbine flow path within the case, the turbine flow path fluidly coupled to the flow channel; wherein the at least one portable source of energy is configured to produce at least one of electrical energy and a source of chemical energy.

Abstract: An acoustic treatment proximate a fan stage including the acoustic treatment disposed in at least one location along surfaces exposed to a fan discharge airflow downstream from a fan within the fan stage.