A nozzle guide vane for a gas turbine engine having a combined side wall thickness value which varies within a cavity region so as to provide a point with a maximum value of combined side wall thickness, which is advantageous for capturing debris travelling through the engine core.

Composite liners (such as acoustic panels, fan track liners, and/or ice impact panels or boxes for turbofan engines) and techniques for forming composite liners. In some examples, the composite liner includes at least one region comprising a reinforcement architecture comprising a matrix material, a plurality of relatively tough polymer-based reinforcement elements, and a plurality of second reinforcement elements. The plurality of relatively tough polymer-based reinforcement elements and the plurality of second reinforcement elements are embedded in the matrix material.

A device for making a fan or compressor for the aeronautical industry includes an annular casing with a main axis (A) and defines an internal flow duct for a gas flow along this axis. The device further includes a bladed wheel mounted inside the casing and having an axis of rotation coincident with the axis (A) of the casing. A system for retaining debris in the event of breakage of the bladed wheel has a retaining annulus mounted around the casing, which includes two radially outwardly projecting annular bosses located respectively upstream and downstream of the bladed wheel. Upstream and downstream edges of the retaining annulus are applied and attached to the bosses.

Methods and systems for detecting a shaft event of a gas turbine engine are described. The method comprises monitoring at least one engine parameter and comparing the at least one engine parameter to a schedule for the at least one parameter defining a first threshold and a second threshold greater than the first threshold; applying a limit to the at least one engine parameter when the at least one engine parameter is inside a parameter limiting region between the first threshold and the second threshold, the first threshold separating the parameter limiting region from a normal operating region, the second threshold separating the parameter limiting region from a hazardous operating region; and detecting the shaft event when the at least one engine parameter crosses the second threshold and issuing a signal in response to the detecting.

Methods and systems for detecting a shaft event of a gas turbine engine are described. The method comprises monitoring at least one engine parameter and comparing the at least one engine parameter to a schedule for the at least one parameter defining a first threshold and a second threshold greater than the first threshold; applying a limit to the at least one engine parameter when the at least one engine parameter is inside a parameter limiting region between the first threshold and the second threshold, the first threshold separating the parameter limiting region from a normal operating region, the second threshold separating the parameter limiting region from a hazardous operating region; and detecting the shaft event when the at least one engine parameter crosses the second threshold and issuing a signal in response to the detecting.

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.

An assembly for a turbine engine turbine includes a turbine rotor disc centered on a longitudinal axis, a turbine shaft centered on the longitudinal axis and driven in rotation by the rotor disc. The assembly further includes first means of transmitting torque from the rotor disc to the shaft, wherein the rotor disc is locked in translation relative to the shaft in the direction of the longitudinal axis by a screwed member on the said shaft and second means of transmitting torque from the rotor disc to the screwed member. The screwed member has an unscrewing direction identical to the direction of rotation of the rotor disc in operation, and the second means of transmitting torque are configured to transmit the rotational torque from the rotor disc to the screwed member when the first means of transmitting torque cease to transmit torque from the rotor disc to the shaft.

Woven preforms, for example those used for jet aircraft engine fancases, may need additional stiffeners to improve the strength and/or dynamic performance of the preform assembly, as well as to serve as attachment points. The present invention describes several improved woven preforms that include circumferential or axial stiffeners, as well as methods of manufacturing the same. One embodiment includes circumferential stiffeners added to a woven preform. Another embodiment includes sub-preforms with integral flanges that combine to make integral stiffeners. A further embodiment includes an intermediate stiffener wrapped onto a base sub-preform wrap, wherein the intermediate stiffener wrap incorporates intermediate stiffeners. Another embodiment incorporates bifurcations in one or more layers of an outermost wrap of a multi-layer fabric composite that forms a preform, wherein the bifurcated outer wrap is folded to form stiffeners that may be oriented circumferentially or axially.

A turbine assembly for a turbocharger and method of assembling is disclosed. The turbine assembly may comprise a turbine wheel coupled to a rotatable turbocharger shaft, and a turbine housing that at least partially encloses the turbine wheel. The turbine housing may include an exhaust diffuser configured to direct a flow of exhaust, a support member coupled to the exhaust diffuser by a clamp assembly, the clamp assembly, a diffuser gap and a support gap. The clamp assembly may be disposed on the exhaust diffuser and on the support member. The clamp assembly includes a containment ring and a clamp plate. The containment ring may include a channel. The clamp plate may be disposed in the channel. The diffuser gap may be disposed between the containment ring and the exhaust diffuser. The support gap may be disposed between the containment ring and the support member.

A turbine assembly for a turbocharger and method of assembling is disclosed. The turbine assembly may comprise a turbine wheel coupled to a rotatable turbocharger shaft, and a turbine housing that at least partially encloses the turbine wheel. The turbine housing may include an exhaust diffuser configured to direct a flow of exhaust, a support member coupled to the exhaust diffuser by a clamp assembly, the clamp assembly, a diffuser gap and a support gap. The clamp assembly may be disposed on the exhaust diffuser and on the support member. The clamp assembly includes a containment ring and a clamp plate. The containment ring may include a channel. The clamp plate may be disposed in the channel. The diffuser gap may be disposed between the containment ring and the exhaust diffuser. The support gap may be disposed between the containment ring and the support member.