A power transmission apparatus for transmitting power generated by a power generation apparatus to a generator and a power generation system including the same are provided. The power transmission apparatus for transmitting power generated by the power generation apparatus to the generator may include a first disk part connected to one of the power generation apparatus and the generator, a second disk part connected to the other one of the power generation apparatus and the generator and disposed on a rear side of the first disk part, and a connection part configured to connect the first disk part and the second disk part and include a portion that decreases and then increases in diameter along a longitudinal direction.

A fan module for an aircraft turbomachine includes a fan with a disc carrying fan blades and a rotor of an electric machine. The rotor has an annular shape and is mounted coaxially downstream of the fan. The module further includes an annular support for the rotor with a downstream end fixed to the rotor and with an upstream end fixed to the fan disc. The support is fixed to the disc by shear bolts configured to break when a torque transmitted by the disc to the support exceeds a predetermined threshold.

A multi-mode microwave waveguide blade sensing system includes a transceiver, a waveguide, and a probe sensor. The transceiver generates a microwave energy signal having a first waveguide mode and a different second waveguide mode. The waveguide includes a first end that receives the microwave energy signal. The probe sensor includes a proximate end that receives the microwave energy signal from the transceiver and a distal end including an aperture that outputs the microwave energy signal. The probe sensor directs the microwave energy signal at a first direction based on the first waveguide mode and a different second direction different based on the second waveguide mode. The probe sensor receives different levels of reflected microwave energy based at least in part on a location at which the at least one microwave energy signal is reflected from the machine.

Disclosed is a compressor housing and method of assembling. The compressor housing may comprise an outer volute, a cavity, an impeller cover, a compressor diffuser and an inner volute. The outer volute includes a back wall and a curved casing. The back wall may include a receptacle and a first plurality of annular steps. The receptacle configured to receive an alignment pin. The cavity is configured to receive the compressor impeller and is at least partially defined by the back wall of the outer volute and the impeller cover. The impeller cover is configured to fragment during impact with the compressor impeller during a failure condition of the compressor impeller. The impeller cover is disposed between the inner volute and the cavity. The compressor diffuser is disposed between the back wall and the impeller cover.

A case for a gas turbine engine includes a cast case section cast case section configured to be welded between a forward case section and an aft case section.

An airfoil material loss control structure is provided. This structure includes at least one fuse zone that, during impact from a foreign object, fail before the surrounding structure. In a further aspect, a rotary machine is provided. This rotary machine includes a ducted fan gas turbine engine including a composite airfoil with at least one fuse zone.

An epicyclic gear assembly includes a carrier that includes a first plate axially spaced from a second plate. At least one epicyclic gear set is located between the first plate and the second plate. The first plate is configured to rotate with an output of the epicyclic gear assembly. A first bearing race is attached to the first plate for supporting a first bearing. A second bearing race is attached to the second plate for supporting a second bearing.

An angled face cap probe includes a housing having a radially inner end and a radially outer end, defining a cavity, and configured to be located radially outward from an airfoil. The angled face cap probe further includes a sensor located in the cavity at the radially inner end of the housing, having a sensor body with a sensing face that is angled to match or substantially match an angle of a radially outward face the airfoil, and having a sensor flat that is elongated in a first direction. The angled face cap probe further includes an outer cap located in the cavity, coupled to the housing, and having an outer cap main body and cap legs that extend radially inward from the outer cap main body to interface with the sensor flat to resist rotation of the sensor relative to the housing.

A fan case assembly adapted for use with a gas turbine engine includes a fan track liner and an annular case. The fan track liner extends circumferentially at least partway about a central axis of the gas turbine engine. The annular case is configured to support the fan track liner at a radial position relative to the central axis. The fan case assembly further includes an air recirculation duct configured to redirect air around the fan track liner.

A method for producing a run-in coating for a turbomachine for braking a rotor in the event of a shaft breakage, the run-in coating being formed as an integral, generative blade portion during a generative manufacture of a blade. A run-in system having an abradable ring that is configured circumferentially on a blade row and has a chamber-type material structure. A turbomachine having a run-in system of this kind, as well as a guide vane having such a run-in coating.