Abstract: A gas turbine engine component includes an exterior pressure side with a plurality of cooling holes located in the exterior pressure side. A relief cut surrounds at least one of the plurality of cooling holes.

Abstract: A shaft for a gas turbine engine includes an inner contour with a stiffening rib that defines a stiffened wall thickness related to a nominal wall thickness according to a ratio between about 1.125-2.1.

Abstract: A guide plate for a swirler assembly is disclosed. In various embodiments, the guide plate includes a guide plate flange configured for engagement with a swirler body having a plurality of primary swirler inlets; and a first plurality of purge holes extending through the guide plate flange and configured to introduce a first vectored purge flow into the swirler body.

Abstract: An ejector assembly for a cooling system of a gas turbine engine may comprise: a tail cone having a tail cone outlet in fluid communication with a cooling air flow of the cooling system; an ejector body defining a mixing section, a constant area section, and a diffuser section; and a nozzle section in fluid communication with an exhaust air flow of the gas turbine engine, the ejector assembly configured to entrain the cooling air flow via the exhaust air flow.

Abstract: Acoustic structures for a gas turbine engine are disclosed. In various embodiments, the acoustic structures comprise a panel in the form of a cellular structure having a plurality of cells; and a housing configured to house the cellular structure, the housing including a first rail configured for attachment to a static structure within the gas turbine engine and a second rail configured for attachment to the static structure. In various embodiments, the acoustic structures comprise a liner in the form of a non-segmented or two-piece structure configured to extend about the inner barrel of a nacelle structure. The disclosed panels and liners are configured to maximize the operational area of the acoustic structures by eliminating obstructions from adjacent flow paths.

Abstract: A bowed rotor start mitigation system for a gas turbine engine of an aircraft is provided. The bowed rotor start mitigation system includes a motoring system and a controller coupled to the motoring system and an aircraft communication bus. The controller is configured to determine at least one inferred engine operating thermal parameter based on at least one aircraft-based parameter received on the aircraft communication bus, where the at least one inferred engine operating thermal parameter is based on data describing a history of the aircraft before an engine shutdown. The motoring system is controlled to drive rotation of a starting spool of the gas turbine engine below an engine idle speed based on determining that the at least one inferred engine operating thermal parameter is within a preselected range.

Abstract: A gaspath component for a gas turbine engine includes a platform. A body extends outward from the platform and includes at least one internal cooling passage. The internal cooling passage includes at least one particulate redirection feature defined at an end of the body opposite the platform. The at least one particulate redirection feature includes a first face oblique to and facing an expected flow of fluid through the internal cooling passage and defines at least one corresponding opening.

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: Aspects of the disclosure are directed to a sealing system for an engine having an axial centerline, comprising: a stationary carbon segment, and a seal plate that rotates when the engine is operated, where the seal plate includes an end face that is opposed to an interface between the carbon segment and the seal plate, and where the end face includes at least one groove that conveys a liquid cooling fluid.

Abstract: A system of a machine includes a network of nodes distributed throughout the machine. Each of the nodes is operable to communicate through electromagnetic signals. The system also includes a radio frequency transceiver, a first antenna coupled to the radio frequency transceiver, a second antenna coupled to one or more sensor nodes, and a controller coupled to the radio frequency transceiver. The controller is configured to select at least one sensor node to interrogate, transmit one or more interrogation frequencies from the radio frequency transceiver through the first antenna to the second antenna, receive one or more sensor frequencies at the first antenna broadcast from the second antenna based on a frequency response of the at least one sensor node to the one or more interrogation frequencies, and determine one or more sensed values based on the sensor frequencies received at the radio frequency transceiver through the first antenna.

Abstract: A system of a machine includes a network of nodes distributed throughout the machine. A means is operable to communicate with the network of nodes through one or more electromagnetic signals. A plurality of waveguides is configured to guide transmission of the one or more electromagnetic signals. A radio frequency antenna is coupled to a first waveguide of the plurality of waveguides. A radio frequency transceiver is coupled between the means and the radio frequency antenna. A membrane is configured to support communication between the first waveguide and at least one node of the plurality of nodes.

Abstract: An article includes a substrate, a bond coat layer disposed on the substrate, and a layer of networked ceramic nanofibers disposed on the bond coat layer.

Abstract: A blade outer air seal for a gas turbine engine includes a platform having a leading edge and a trailing edge. A pair of circumferential edges connect the leading edge and the trailing edge. An end wall protrudes radially outward from the platform at the trailing edge. A first support rib connects one of the circumferential edges to the end wall and structurally supports the end wall. A first boss portion extends axially forward from the end wall and is disposed radially outward of the first support rib.

Abstract: An assembly is provided for a piece of rotational equipment. This assembly includes a first structure, a second structure and a fluid transfer assembly. The first structure is configured with an aperture. The second structure is configured as or otherwise includes a port. The fluid transfer assembly includes a fluid conduit and a slider element. The fluid conduit is configured as a monolithic tubular body that includes a first conduit end, a second conduit end, a first coupling and a second coupling. The fluid conduit extends axially along a centerline from the first conduit end, through the aperture and into the port to the second conduit end. The first coupling is mated with the first structure through the slider element. The second coupling is mated with the second structure through a cone seal interface.

Abstract: Oil slinger systems include a seal runner comprising an annular radial member having a radius (R) and an outer axially extending member having an axial length (L), wherein a proximal surface of the outer axially extending member comprising a plurality of helical grooves. Methods of radial convective cooling include pumping a cooling liquid through the oil slinger system and convectively cooling the oil slinger.

Abstract: A fan blade platform seal includes a platform portion including a first side and a second side opposite the first side. The platform portion further includes a flow path surface extending between the first side and the second side and a bonding surface opposite the flow path surface. The fan blade platform seal further includes a first seal portion including a first bonding segment including a first outer surface, mounted to the platform portion on the first side of the platform portion, and a first inner surface opposite the first outer surface. The fan blade platform seal further includes a stiffening portion mounted to the first inner surface. The stiffening portion includes a first bonding layer bonded to the first inner surface and a stiffening layer bonded to the first bonding layer on a first layer side of the stiffening layer.

Abstract: A system for component inspection comprising at least one sensor configured to capture sensor data of the component; and a processor coupled to the at least one sensor, the processor comprising at least one model configured to separate the sensor data into a normal category and an abnormal category.

Abstract: An airfoil assembly includes an airfoil that has an exterior wall that defines an interior cavity. The exterior wall extends between a leading end and a trailing end and an open inboard end and an open outboard end. The exterior wall is formed of a high temperature-resistant material selected from refractory metal-based alloys, ceramic-based material or combinations thereof. A support frame extends in the interior cavity and protrudes from the interior cavity through at least one of the open inboard end and the open outboard end.

Abstract: A blade outer air seal (BOAS) for a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion; and a multitude of cooling fins disposed around the radially outer face of the seal body, at least one of the multitude of cooling fins having at least one aperture.

Abstract: A combustor for use in a gas turbine engine comprising: an outward shell; an inward shell located radially inward of the outward shell, the inward shell and the outward shell defining a combustion chamber therebetween; an aft outward panel located proximate the outward shell, the aft outward panel extending from an aft end of the combustion chamber to an outward panel joint; an aft inward panel located proximate the inward shell, the aft inward panel extending from the aft end of the combustion chamber to an inward panel joint; and a forward panel located proximate a forward end of the combustion chamber, the forward panel comprising: an outward wall located proximate the outward shell; an inward wall located proximate the inward shell; and a forward wall located proximate the forward end of the combustion chamber, the forward wall extending from the inward wall to the outward wall.