Abstract: The present invention relates to a fire resistant fan casing for a gas turbine engine. The casing has a projection such as a reinforcing rib or a mounting pad. The projection comprises at least one shell portion formed of a fiber/plastic composite material encasing a core of fire resistant material such as a metallic material or a ceramic matrix composite material.

Abstract: Systems and methods efficiently bring additional variables into a Pseudo-Random Pattern Generator (“PRPG”) in the early cycles of an automatic test pattern generation (“ATPG”) process without utilizing any additional hardware or control pins. Overscanning (e.g., scanning longer than the length of the longest channel) for some additional cycles brings in enough variables into the PRPG. Data corresponding to earlier cycles of the ATPG process is removed.

Abstract: A turbomachine casing assembly including an inner casing element for arrangement radially outward of a turbomachine fan; an outer casing element for arrangement radially further outward of the turbomachine fan; a retaining lip arranged radially inward of a portion of the inner casing element; and a separator extending between the inner and outer casing elements and arranged to urge a portion of the inner casing element against the lip. The separator is arranged in compression between the inner and outer casing elements to urge the portion of the inner casing element against the lip. The separator is arranged to engage a frangible region of the inner casing element such that the frangible region is configured to break in response to an impact satisfying predetermined conditions, allowing the inner casing element to displace radially outwards exposing features to improve retention of a released fan blade.

Abstract: Fan containment system fitting around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system includes a fan case having an annular casing element for encircling the array of fan blades and a hook projecting in a radially inward direction from the annular casing element and positioned axially forward of the array of fan blades when the fan containment system fitted around fan blades. An annular fan track liner positioned substantially coaxial to the annular casing element. Clamping arrangement connects fan track liner to the hook. Clamping arrangement is configured under the condition that a fan blade impacts the fan track liner, the clamping arrangement releases connection between the hook and a portion of fan track liner so that a portion of the fan track liner can move towards the annular casing element to encourage the fan blade to impact the hook.

Abstract: A turbomachine casing assembly includes a first casing element locatable radially outward of one or more rotating aerofoil elements of a turbomachine, a second casing element located radially distal to the first casing element and one or more arcuate fence elements positioned between the first and second casing elements. Following impact of a detached fan blade, a radially outward movement of the first casing element causes the or each fence element to project into the air flow passing through the turbomachine.

Abstract: Systems and methods disclosed herein provide for efficiently loading mask data to the mask register bits from the decompression network outputs of an ATPG system. The systems and methods also provide an elastic interface utilized between a tester and a decompressor network (e.g., sequential and combinational decompressors) in order to expand the number of input variables utilized during the loading of the mask data to the mask register bits.

Abstract: A composite aerofoil vane for a gas turbine engine extends in use in a generally radial direction across an axially- and circumferentially-extending annular duct. The vane comprises a plurality of first reinforcing fibers extending in a generally radial direction and a plurality of second reinforcing fibers extending in generally axial and circumferential directions. The second fibers are interlaced with the first fibers so as to form a more unified and integrated structure, and to prevent the first reinforcing fibers from moving relative to one another.

Abstract: A connecting rod for a device includes a rod having a large end, and a cap attached to the large end. The large end of the rod and the cap cooperate to define a first side surface and a second side surface disposed opposite to each other. The large end of the rod and the cap further define a crankshaft bore that extends along a crank axis between the first side surface and the second side surface. A thrust surface is defined by at least one of the first side surface or the second side surface, and is disposed on a thrust plane. The thrust surface includes at least one recessed region that extends inward away from the thrust plane of the thrust surface. Each of the thrust surfaces include ramps that extend between the recessed regions and the flat regions at the thrust plane of the thrust surface.

Abstract: A crankshaft includes a plurality of counterweights. Each of the counterweights includes a counterweight body. The counterweight body has a first lateral portion, a second lateral portion, and a central portion between the first lateral portion and the second lateral portion. A method of balancing the crankshaft includes: (a) removing material from the first lateral portion of the counterweight body of at least one of the counterweights; and (b) removing material from the second lateral portion of the counterweight body of at least one of the counterweights in order to balance the crankshaft.

Abstract: A fan containment system having a generally cylindrical fan case including a hook projecting in a generally radially inward direction and positioned axially forward of a radial array of fan blades; a fan track liner disposed on the radially inner surface of the fan case; and a panel which is positioned axially rearward of the hook and positioned axially forward of the radial array of fan blades and forms a substantially continuous air washed surface with the fan track liner. The panel is temporarily deformable so as to absorb the impacts of any foreign bodies, which enter the gas turbine engine, without compromising the structural integrity of the panel while being weak enough so that in the event that one of the fan blades is released from the hub, the fan blade tip of the detached fan blade is not inhibited from moving radially outward of the hub.

Abstract: Systems and methods disclosed herein provide for utilizing extra variables in the decompression equation set of an ATPG process for test patterns requiring an excess number of care bits than can be supported efficiently by the current hardware. An elastic interface is utilized between a tester and a decompressor network (e.g., sequential and combinational decompressors) in order to expand the test pattern length and/or the number of input variables. The systems and methods also provide care bits in early scan cycles of the ATPG process for sequential decompressors starting from a fixed state.

Abstract: A system and method are provided for selective bit-wise masking of X-values in scan channels in an integrated circuit (IC) during a built-in self test (BIST). The composite mask pattern is selectively generated according to locations of X-values identified in a simulation of the IC. The composite mask pattern is stored on the IC and cyclically maintained while being applied to the operational scan results of the IC. The composite mask pattern is recycled over a plurality of scan iterations to effectively prevent the X-values from influencing the resulting signature of the BIST that represents a functional fingerprint of the IC and minimize storage requirements for the composite mask pattern.