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.

A case for a gas turbine engine includes a containment section with a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers. A method of manufacturing the case includes winding the plurality of unidirectional roving fiber layers around the plurality of non-crimp fabric layers.

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 fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine, including: a fan case having an annular casing element for encircling an array of fan blades and an annular fan track liner lining a radially inner side of the casing element, including a first fan track liner panel positioned circumferentially adjacent a second fan track liner panel. An engagement arrangement engages the first fan track liner panel to the second, extending along at least a portion of adjacent sides of the liner panels, and is configured and the liner panels are shaped such that axial movement of the first fan track liner panel by a distance less than the length of the engagement arrangement, being measured in a direction parallel to the adjacent sides of the liner panels, disengages the first liner panel from the second.

A test blade for use in a blade-release test in which the blade is mounted on a rotatable hub and at least a portion of the blade is released therefrom by the action of a controlled explosion. The blade has a root portion for mounting on said rotatable hub and the root portion comprises a radially inner surface having a channel extending at least partly along or proximal the camber line. The channel is for receiving at least one explosive charge and at least one detonator which may be contained within a charge carrier.

A fan case for use in a gas turbine engine of an aircraft includes an outer shroud and a liner extending along the outer shroud. The fan case provides a protective band that blocks fan blades from being thrown out of the fan case in case of a blade-off event in which a fan blade is released during operation of the gas turbine engine.

A frangible airfoil that mitigates adverse conditions associated with release of material resulting from impact damage to the composite blade is provided, the airfoil having provisions for dissipating energy, self-shredding, and predetermined release trajectory.

A frangible airfoil that mitigates adverse conditions associated with release of material resulting from impact damage to the composite blade is provided, the airfoil having provisions for dissipating energy, self-shredding, and predetermined release trajectory.

A method and apparatus for protecting downstream engine components from damage in the event of a turbine failure involves positioning a debris trap downstream of a turbo and upstream of an engine. The debris trap includes an outer body with an inlet opening at a first end of a first diameter, an outlet opening, and an interior of a second diameter which is larger than the inlet opening. An inner body extends into the interior of the outer body with air flow openings in the inner body communicating with the outlet opening. An impaction plate is supported by the inner body in axial alignment with the inlet opening. Turbo fragments strike and are slowed by impact with the impaction plate. The turbo fragments collect in the interior of the outer body with air escaping by entering the air flow openings of the inner body and passing to the outlet opening.

A safety apparatus for containing a release of energy from a tension stud of a rotor assembly. The safety apparatus includes a containment member configured to pivot about a pivot location. The containment member includes a tail located on a first side of the pivot location, an elongate region on a second side of the pivot location, the elongate region defining a longitudinal axis and an arm located towards a distal end of the elongate region and projecting away from the longitudinal axis. The containment member is configured to be connected to a tool apparatus. In use, the containment member is configured to pivot between an open position and a containment position in which the arm overlaps with at least part of the tool apparatus in the direction of the longitudinal axis of the elongate region to contain the load energy within the safety apparatus.