A disk spring may include an annular base body, a central longitudinal axis of which defines an axial direction of the base body. A profile of the base body in a profile plane containing the central longitudinal axis may have a wave-shaped contour with two minima including a radially inner minimum and a radially outer minimum and with an intermediate maximum disposed between the two minima. The wave-shaped contour may extend from a radially inner end point to a radially outer end point. The radially inner end point may be arranged offset in the axial direction with respect to the radially outer end point.

A latch assembly includes a housing including a first housing portion and a second portion including. The latch assembly further includes a first latch member disposed within the first housing portion and configured for translation along the latch axis. The first latch member includes at least two rotatable arms configured to rotate between an arm retracted position and an arm extended position in which the at least two rotatable arms extend in a first direction away from the latch axis. The latch assembly further includes a second latch member disposed within the second housing portion and configured for translation along the latch axis. The second latch member includes a second latch member body including a base portion and at least one axially extending portion extending from the base portion in a second direction toward the interior surface of the lateral wall.

A gas turbine engine includes a fan rotor driven by a fan drive turbine about an axis through a gear reduction to reduce a speed of the fan rotor relative to a speed of the fan drive turbine. A fan case surrounds the fan rotor, and a core engine with a compressor section, including a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection is between the fan case and the core engine includes three triangular-frame connecting members rigidly connected to the fan case at a fan case connection point, and to the core engine at a core engine connection point. The triangular-frame connecting members each are defined by two rigid legs which extend between the fan case and to the core engine, along directions each have a component extending radially inwardly and a component in opposed circumferential directions to each other. A plurality of non-structural fan exit guide vanes and the non-structural fan exit guide vanes are provided with an acoustic feature to reduce noise. The non-structural fan exit guide vanes are rigidly mounted to at least one of the fan case and the core engine.

A turbine vane assembly adapted for use in a gas turbine engine includes a spar, a turbine vane, and load transfer pins. The spar comprises metallic materials and is configured to support other components of the turbine vane assembly relative to an associated turbine case. The turbine vane comprises ceramic matrix composite materials and is shaped to include an airfoil configured to direct the flow of hot gasses through a primary gas path of the turbine vane assembly.

A shroud segment including a forward radial wall, an aft radial wall and at least one interlocking subcomponent. The forward radial wall, an aft radial wall and the at least one interlocking subcomponent are each formed of a ceramic matrix composite (CMC) including reinforcing fibers embedded in a matrix. The shroud segment further including an interlocking mechanical joint joining each of the forward radial wall and the aft radial wall to the at least one interlocking subcomponent. Methods are also provided for joining the forward radial wall and the aft radial wall to the at least one interlocking subcomponent using an interlocking mechanical joint.

A pressure relief latch includes a housing configured to be mounted to a pressure relief door. A bolt is coupled to the housing about a first axis and is rotatable about the first axis between a first bolt position and a second bolt position. The bolt includes a bearing centered about a second axis. The bearing is configured to rotate about the second axis. A spring assembly includes a first assembly end mounted to the bearing and a second assembly end in rotational communication with the housing about a third axis. The spring assembly is rotatable about the second and third axes and further includes a spring extending between the first and second assembly ends. The bolt is configured to permit movement of the pressure relief door from the closed position to the open position as the bolt rotates from the first bolt position to the second bolt position.

The invention relates to a blade pivot with adjustable orientation for a turbomachine fan hub, comprising a stud having means for retaining a fan blade root and coupling means for the transmission of a torsional torque, a rolling bearing for absorbing the centrifugal forces having an inner bushing mounted in transverse abutment against an external radial portion of the stud, a ring for radially retaining the stud relative to the rolling bearing housed in an annular groove formed in the stud, a plurality of clamping parts each mounted in transverse abutment against the retaining ring and in radial abutment against the inner bushing of the rolling bearing, and a clamping nut screwed onto an outer thread of the stud to come into conical abutment against the clamping parts such that said clamping parts ensure a clamping of the inner bushing of the rolling bearing on the stud and a clamping

An air supply device, a gas turbine system and a using method thereof are disclosed. In the air supply device, an air intake compartment includes a connection end; a combustion air intake filter is located in the air intake compartment and connected with the combustion air intake filter; a combustion air intake interface is located on a tail plate and is connected with the combustion air silencer; and a sound insulation turnover mechanism includes a sound insulation flap and a turnover mechanism, the air intake compartment includes a first bottom plate and the tail plate that is located at the connection end, the sound insulation flap is located at the connection end, and the turnover mechanism is connected with the sound insulation flap, and is configured to drive the sound insulation flap to rotate relative to the tail plate.

A ceiling fan having a dual redundant motor mounting assembly for suspending a motor comprising a downrod, a hollow motor shaft suspending the motor from the downrod, a retaining pin extending through the hollow motor shaft, and a retaining rod coupled to the retainer pin for redundantly suspending the motor.

A method of producing compressed air for use onboard an aircraft includes receiving compressor discharge air into an air channel of a fuel injector. The method also includes cooling the compressor discharge air within the air channel by heat exchange with fuel flowing in the fuel injector, and issuing cooled air from the internal air channel out of an engine case as a source of compressed air.