Abstract: A blade track for a gas turbine engine includes segments and joints that couple the segments together. Each segment extends part-way around a central axis of the engine and the joints couple together adjacent segments to form a full hoop.

Abstract: A turbine shroud for a gas turbine engine includes an annular metallic carrier and a blade track. One or more cavities are formed between the carrier and blade track to provide cooling air to the blade track.

Abstract: A turbine shroud for a gas turbine engine includes a carrier and a blade track. The blade track includes an annular runner and a plurality of inserts that extend radially outward away from the annular runner. The inserts extend through the carrier to couple the annular runner with the carrier.

Abstract: A turbine shroud assembly or blade track assembly adapted to extend around a turbine wheel assembly is disclosed. The turbine shroud assembly includes a carrier and a blade track coupled to the carrier. The blade track is movable between a radially-inward position having a first inner diameter and a radially-outward position having a second inner diameter larger than the first inner diameter.

Abstract: A turbine wheel for use in a gas turbine engine having a bladed ring attached to a rotor disk. The bladed ring includes features to fit within slots of the rotor disk to couple the bladed ring to the rotor disk.

Abstract: A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed as a composite structure including a number of plies of ceramic-containing material. The blades each include a root to fit within dovetail slots of the rotor disk to couple the blades to the rotor disk.

Abstract: A combustor for use in a gas turbine engine and methods for assembling the same are disclosed. The combustor includes an outer case and a combustion liner. The combustion liner is arranged radially inward of the outer case. The combustion liner is arranged to define an annular combustion chamber.

Abstract: An ultra high bypass ratio turbofan engine includes a variable pitch fan, a low pressure turbine, a reduction gearbox, and a plurality of outlet guide vanes. The ultra high bypass ratio turbofan engine has a bypass ratio between about 18 and about 40. The variable pitch fan and the low pressure turbine are coupled together by the reduction gearbox. The reduction gearbox reduces the speed of the variable pitch fan relative to the low pressure turbine. The plurality of outlet guide vanes are spaced aft of the variable pitch fan and are axially swept. The variable pitch fan and the low pressure turbine are configured to generate a fan pressure ratio between about 1.15 and about 1.24.

Abstract: One embodiment of the present disclosure is a unique gas turbine engine having a bearing system and method of operating the engine. Another embodiment is a unique rotor machine. Desired clearances are maintained in the engine and rotor and by the method. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for rotor machines, such as but not limited to, gas turbine engines.

Abstract: A gas turbine engine airflow member is disclosed having spherical interface shapes at a tip end and a hub end. In one embodiment, the airflow member is a fan blade. The spherical interface shapes can be convex or concave. In one form, the tip end spherical shape is axially shifted aft relative to a hub end. The tip end can include relatively little forward portion in an expanding flow path with predominant portion of the tip end in a contracting flow path. Such a configuration can occur with a midpoint and trailing edge located in the contracting flow path. A center of gravity of a swept airflow member having spherical end shape can be located on a pivot axis of the airflow member. Divot depressions can be provided to permit concave flow path shapes.

Abstract: A gas turbine engine includes an inner shaft extending axially along the gas turbine engine, a plurality of disks extending radially inwardly and toward the inner shaft, at least one hole in at least one of the plurality of disks, and an obstruction positioned between the inner shaft and an end of the disk having the at least one hole, such that a bore flow that flows along an axial length of the inner shaft is obstructed from flowing along the shaft by the obstruction, and forced to flow radially outward from the obstruction, through the at least one hole, and radially inward toward the inner shaft.

Abstract: An apparatus and method for transmitting a rotary input into counter-rotating outputs is disclosed herein. An exemplary apparatus for performing the method includes a planetary gear set having a sun gear rotatable by a rotary input, a plurality of planet gears in meshed engagement with the sun gear, a carrier coupling the plurality of planet gears together, and a ring gear encircling and in meshed engagement with the plurality of planet gears. The exemplary apparatus also includes a first shaft member coupled to the carrier for transmitting motion in a first rotational direction. The exemplary apparatus also includes a second shaft member coupled to the ring gear for transmitting motion in a second rotational direction opposite the first rotational direction. The first shaft member at least partially encircles the second shaft member.

Abstract: A coupling assembly for transmitting torque between a first body and a second body is disclosed herein. The coupling assembly includes a diaphragm plate extending radially between a radially inner periphery fixed for rotation with the first body. The diaphragm plate extends to a radially outer periphery and is operable to elastically deform in response to changes in the axial positions of the first and second bodies relative to one another. The coupling assembly also includes a socket assembly engaged with the radially outer periphery of the first diaphragm plate for concurrent axial movement in response to changes in the axial positions of the first and second bodies relative to one another. The socket assembly is also operable to transmit torque between the second body and the diaphragm plate. The socket assembly includes a radially-accommodating structure operable to at least partially move in response to changes in an outer profile of the second body.

Abstract: An apparatus and method for transmitting a rotary input into counter-rotating outputs is disclosed herein. An exemplary apparatus for performing the method includes a planetary gear set having a sun gear rotatable by a rotary input, a plurality of planet gears in meshed engagement with the sun gear, a carrier coupling the plurality of planet gears together, and a ring gear encircling and in meshed engagement with the plurality of planet gears. The exemplary apparatus also includes a first shaft member coupled to the carrier for transmitting motion in a first rotational direction. The exemplary apparatus also includes a second shaft member coupled to the ring gear for transmitting motion in a second rotational direction opposite the first rotational direction. The first shaft member at least partially encircles the second shaft member.

Abstract: A coupling assembly for transmitting torque between a first body and a second body is disclosed herein. The coupling assembly includes a diaphragm plate extending radially between a radially inner periphery fixed for rotation with the first body. The diaphragm plate extends to a radially outer periphery and is operable to elastically deform in response to changes in the axial positions of the first and second bodies relative to one another. The coupling assembly also includes a socket assembly engaged with the radially outer periphery of the first diaphragm plate for concurrent axial movement in response to changes in the axial positions of the first and second bodies relative to one another. The socket assembly is also operable to transmit torque between the second body and the diaphragm plate. The socket assembly includes a radially-accommodating structure operable to at least partially move in response to changes in an outer profile of the second body.

Abstract: A gas turbine engine blade comprises a housing, a composite core located within the housing, and a gas damper located within the housing for damping vibration of the blade.

Abstract: A unit fuel injector is provided which includes a threadless injector body attaching device for attaching an upper body section of the fuel injector to a lower body section while avoiding imparting a transverse load to the upper body section thereby minimizing bore distortion, plunger wear and the likelihood of injector failure. The threadless injector body attaching device includes a groove formed in the lower end of the upper body section and one or more apertures extending through the lower body section for positioning adjacent the groove. Also, one or more pins are provided for insertion into a respective aperture and connection to the lower body section. The groove and opposing aperture or apertures are sized to create a slip fit to avoid a contact force between the pin or pins and the upper body section.

Abstract: An improved unit fuel injector is provided which effectively and precisely controls the timing of fuel injection by avoiding outside influences acting on a timing plunger. The unit fuel injector includes a timing plunger positioned between upper and lower plungers, a timing chamber positioned between the timing plunger and upper plunger and a spring chamber positioned between the timing plunger and a metering chamber for containing one or more springs for biasing the plungers. A spring chamber drain valve device is provided for directing fuel in the spring chamber to a low pressure drain while isolating the spring chamber from the low pressure drain system thereby preventing pressure variations in the drain system from entering the spring chamber and acting on the timing plunger. In addition, a scavenge circuit is provided to direct a scavenging flow of fuel and combustion gas from the injector directly to the low pressure drain without communication with the spring chamber.

Abstract: A unit fuel injector is provided which includes a threadless injector body attaching device for attaching an upper body section of the fuel injector to a lower body section while avoiding imparting a transverse load to the upper body section thereby minimizing bore distortion, plunger wear and the likelihood of injector failure. The threadless injector body attaching device includes a groove formed in the lower end of the upper body section and one or more apertures extending through the lower body section for positioning adjacent the groove. Also, one or more pins are provided for insertion into a respective aperture and connection to the lower body section. The groove and opposing aperture or apertures are sized to create a slip fit to avoid a contact force between the pin or pins and the upper body section.

Abstract: A top stop assembly for a fuel injector is provided which includes a top stop housing having a threadless injector engaging portion positioned at one end of the housing for threadlessly engaging the outer diameter portion of an injector barrel to minimize inward bore distortion. The top stop is preferably formed integrally on the top stop housing body to create a predetermined axial length of the housing which defines a predetermined outer limit of a retraction stroke of an injector plunger assembly, i.e. a top stop position. The top stop position is set by selecting a top stop housing having a predetermined axial length corresponding to the desired top stop position thereby reducing costs and avoiding loosening problems associated with multi-part top stop assemblies.