A gas turbine engine includes an electrical machine positioned at least partially inward of a core airflow path, the electrical machine including an electrical rotor component and an electrical stator component, a connecting member positioned between the electrical machine and a rotary member, a disconnection device that is positionable between a disengaged position, in which the disconnection device is disengaged from the connecting member, and an engaged position, in which the disconnection device is engaged with the connecting member, and a controller including a processor, where the processor receives a signal from the electrical machine indicative of a fault, and in response to receiving the signal from the electrical machine indicative of the fault, directs the disconnection device to move from the disengaged position to the engaged position.

A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier, a seal segment, and a mount assembly. The carrier is configured to be coupled to a turbine case. The seal segment is shaped to define a gas path boundary of the shroud assembly. The mounting assembly is configured to couple the seal segment to the carrier.

Fan (16), in particular for an aircraft cooling unit, having a wheel (128) comprising a hub (138) and an annular array of blades (140), a shaft assembly (136) for driving the wheel about an axis (A), and fusible means for connecting the hub of the wheel to the shaft assembly, said fusible connecting means comprising a first mounting sleeve through which the shaft assembly extends and which is surrounded by the hub, and fusible safety elements (174) which extend parallel to the axis (A) and are configured to break and to disengage the wheel from the shaft assembly when said wheel rotates and a driving torque of the wheel transmitted by the shaft assembly exceeds a certain threshold, characterised in that the connecting means comprise a second wearing sleeve (143) which is inserted between the first sleeve and the hub and through which the fusible elements extend, the second sleeve being made of a material which is different from that of the first sleeve and subject to wear by friction and/or by heating if the shaft assembly continues to rotate following the aforementioned disengagement.

A gas turbine engine has a bearing housing mounted to structure linked to the engine mounting pads. The bearing housing has bearing housing flanges with bearing housing flange openings aligned with attachment flange openings of the structure. Some of the bearing housing flange openings are slots. A first group of fasteners extends through one of the attachment flange openings and through one of the bearing housing flange openings. A second group of fasteners extends through one of the attachment flange openings and through one of the slots. The first group of fasteners are sacrificial fasteners configured to fracture in response to a load on the bearing housing exceeding a fracture load. The bearing housing is displaceable relative to the structure after fracture of the sacrificial fasteners via the second group of the fasteners moving within and relative to respective ones of the slots.

There is disclosed a containment assembly (500 for a gas turbine engine, comprising: an outer impact structure (56); an inner impact structure (54) disposed radially within the outer impact structure; wherein the outer impact structure and the inner impact structure axially extend between a fan portion (4) of the containment assembly corresponding to an axial location of a fan and a forward portion (2) of the containment assembly axially forward of the fan portion; and wherein at least one of the outer impact structure and the inner impact structure has a discontinuous profile between the forward portion and the fan portion so that there is a local reduction in compressive strength in the fan portion.

A bolted joint apparatus includes: a first component including a first row of first bolt holes extending therethrough; a second component including a second row of second bolt holes extending therethrough wherein the second bolt holes are aligned coaxially with the first bolt holes, a plurality of fasteners, each of fasteners disposed through aligned pairs of the first and second bolt holes to couple together the first and second components, each of the fasteners including a shank; and crushable spacers disposed around the shanks of the fasteners, the crushable spacers clamped in compression between the fasteners and one of the components, wherein each of the crushable spacers has a tubular body interconnecting first and second enlarged ends, the tubular body being defined by a peripheral wall which incorporates at least one weakening feature.

A turbocharger includes a turbine with a housing and a rotor for expanding a first medium; a compressor with a housing and a rotor for compressing a second medium utilizing energy extracted in the turbine during expansion of the first medium. A housing surrounds the turbine housing and/or the compressor housing and/or the bearing housing at least in sections, which housing is at least formed from a first housing section and a second housing section, which are connected to one another via screw connections. On the first housing section, shearing force absorption elements are formed or fastened which extend through the second housing section and in the event that shearing forces occur, absorb the shearing forces and thus relieve the screw connections of the shearing forces.

The invention relates to a torque limiting device in a torque bearing connecting structure between a gearbox and a stationary structure in a gas turbine engine, wherein the torque limiting device comprises a mechanical fuse in the connection structure comprising an at least partially circumferential weakening of the material. The invention also relates to a gas turbine engine.

A gas turbine engine component (50, 100, 150, 160, 174, 206, 236), including: a surface (54) subject to loss caused by a wear instrument during operation of the component in a gas turbine engine and a performance feature (80, 82, 102, 152, 162, 172, 200, 230) associated with the surface. The surface and the performance feature interact in a manner that changes with the loss such that a change in performance of the gas turbine engine resulting from the loss is mitigated.

A link for mounting a first component to a second component according to an example of the present disclosure includes a first piece connectable to the first component, a second piece connectable to the second component, the second piece includes a main body portion receivable in an opening in the first piece. A primary fastener is configured to retain the main body portion of the second piece in the opening. A secondary fastener is configured to retain the main body portion of the second piece in the opening, the secondary fastener capable of withstanding higher loads than the primary fastener. A gas turbine engine assembly and a method of constraining a gearbox with respect to an engine are also disclosed.