Abstract: A pneumatic tire has a radially outer tread. The tread has a plurality of circumferential grooves, a plurality of lateral grooves, and a plurality of shoulder grooves. The tread includes bottoms and sides of each circumferential groove being textured for improving snow traction, bottoms and sides of each lateral groove being textured for improving snow traction, and bottoms and sides of each shoulder groove being textured for improving snow traction.

Abstract: A fan track liner assembly for ducted fan engine which provides for reduced strain and deformation of front of fan case in the event of a fan blade off event. Various assemblies are proposed. In one aspect, assembly includes fan track liner panel and plurality of fasteners which are arranged to secure panel to fan case of engine, wherein: a forward portion of panel includes hinged portion which operates as trapdoor to permit blade or blade fragment to pass through, and fasteners are arranged to fail in the event of blade or blade fragment passing through trapdoor causing panel to be displaced rearwards in fan case. Other aspects provide for reduced height of support on fan case for attaching fan track liner and for collapsible comb box.

Abstract: A fan track liner assembly for a ducted fan engine which provides for ease of installation and replacement. The assembly includes a plurality of panels; and a plurality of fastening members which are arranged to secure the panels to the fan case of the engine, wherein: each fastening member has a base portion and an elongate arm member, and further wherein: the base portion has an attachment portion which is used to secure the fastening member to the fan case; and the arm member extends from the base portion, and each panel has slotted edge portions on opposing edges at one end of the panel which are each arranged to engage with respective arm members of fastening members on either side of the panel when the panel is assembled with the fastening members by sliding the panel onto the fastening members or vice-versa.

Abstract: A crankshaft includes a pin bearing journal, and a counterweight. The pin bearing journal defines a hollow pin core. The hollow pin core includes a first pin core section and a second pin core section, and an enlarged central section disposed between the first pin core section and the second pin core section. The first and second pin core sections each define a cross section having a first and second cross sectional area respectively, and the enlarged central section defines a third cross section defining a third cross sectional area, with the third cross sectional area larger than the first and second cross sectional areas. An isolation window extends through the counterweight. The crankshaft is cast from a high shrink steel alloy having a shrinkage factor equal to or greater than 1%. The enlarged central section and the isolation window improve the castability of the high shrink steel alloy.

Abstract: An aircraft propulsion system has an engine assembly having an axis of rotation, a fan assembly operatively connected to the engine assembly and comprising a plurality of fan blades arranged circumferentially around the axis of rotation and a monolithic nacelle assembly which circumferentially encloses the fan assembly. The propulsion system has a ratio of fan assembly outer diameter to nacelle assembly outer diameter of at least 0.87. As a result, the propulsion system provides for a significantly larger fan assembly outer diameter for a given nacelle assembly outer diameter than a conventional prior art turbofan engine, thereby increasing the specific power output or the bypass ratio of the propulsion system, which will result in improved propulsive efficiency without an increase in nacelle drag.

Abstract: A composite casing comprising a barrel and a stiffening ring provided around the barrel. The stiffening ring includes a section having a waved profile in a circumferential direction.

Abstract: A rotor assembly for a gas turbine engine, the rotor assembly has a disc supporting a plurality of radially extending blades. The blades define passages therebetween and each passage has an annulus filler assembly. The annulus filler assembly includes at least two bodies and a brace, each of the bodies being arranged to abut respective adjacent blades and the brace is arranged to occupy a position centrally of the two bodies. The brace is mounted to the disc and each body and the brace are arranged to engage one another to form an airwash surface. The airwash surface improves aerodynamic flow of air entering the gas turbine engine.

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. A void is provided between a radially proximal face of the first casing element and a radially proximal face of the second casing element, at the first end of the first casing element. The first end of the first casing element is located against a corresponding first end of the second casing element by an energy absorbing element, with the first casing element; including a cantilever. The cantilever is arranged in a region extending along the first casing element from the first end; and having a pivot axis at a mid portion thereof.

Abstract: A fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system comprises an annular casing element for encircling an array of fan blades. An annular fan track liner is positioned substantially coaxial to the annular casing element. A hook projects in a generally radially inward direction from the annular casing element and is positioned axially forward of an array of fan blades when the fan containment system is fitted around said fan blades. Tabs protrude from the hook in a generally rearward direction and are spaced circumferentially along the hook. Fasteners connect the fan track liner to the tabs. The fasteners are configured so as to permit movement of the fan track liner towards the annular casing element when the fan track liner is impacted by a released fan blade.

Abstract: A method of simultaneously manufacturing a plurality of crankshafts includes positioning a core system having a plurality of individual cores within a cavity of a mold having first and second halves forming an exterior shape of the crankshafts. The crankshafts' exterior shape includes a plurality of pin bearing journals and a plurality of main bearing journals. Each of the cores passes through each of the crankshafts. At least one core passes through at least one of the pin bearing journals and at least one other core passes through at least one of the main bearing journals. The method also includes introducing into the cavity molten metal to form the crankshafts. As the metal flows into the cavity and around the plurality of cores, a hollow section extending through at least one of the pin bearing journals and at least one of the main bearing journals of each crankshaft is formed.

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: 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 fibre/plastic composite material encasing a core of fire resistant material such as a metallic material or a ceramic matrix composite material.

Abstract: Fan containment system fitting around 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 array of fan blades and a hook projecting in radially inward direction from the annular casing element and positioned axially forward of an 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 and a second casing element located radially distal to the first casing element, with a void being defined between the first and second casing elements. Each of the first and second casing elements includes, at a first end thereof, respective co-operating first and second interface portions. In the event that an aerofoil element becomes detached from the turbomachine and impacts the first casing element, the second interface portion; slides along the first interface portion and the first end of the first casing element enters the void.

Abstract: Details of a highly cost effective and efficient implementation of a manifold array (ManArray) architecture and instruction syntax for use therewith are described herein. Various aspects of this approach include the regularity of the syntax, the relative ease with which the instruction set can be represented in database form, the ready ability with which tools can be created, the ready generation of self-checking codes and parameterized test cases. Parameterizations can be fairly easily mapped and system maintenance is significantly simplified.

Abstract: A method of simultaneously manufacturing a plurality of crankshafts includes positioning a core system having a plurality of individual cores within a cavity of a mold having first and second halves forming an exterior shape of the crankshafts. The crankshafts' exterior shape includes a plurality of pin bearing journals and a plurality of main bearing journals. Each of the cores passes through each of the crankshafts. At least one core passes through at least one of the pin bearing journals and at least one other core passes through at least one of the main bearing journals. The method also includes introducing into the cavity molten metal to form the crankshafts. As the metal flows into the cavity and around the plurality of cores, a hollow section extending through at least one of the pin bearing journals and at least one of the main bearing journals of each crankshaft is formed.

Abstract: A crankshaft includes first, second, third, and fourth main journals, each coaxially disposed along a crankshaft axis. A first, second, third, fourth, fifth, and sixth crank pin are each parallel with the crankshaft axis, and radially offset from the crankshaft axis. A first crank arm includes a first counterweight, and connects the first main journal and the first crank pin. A third crank arm includes a second counterweight, and connects the second crank pin and the second main journal. A seventh crank arm includes a third counterweight, and connects the third main journal and the fifth crank pin. A ninth crank arm includes a fourth counterweight, and connects the sixth crank pin and the fourth main journal. The first, second, third, and fourth counterweights are the only counterweights of the crankshaft.

Abstract: Processes associated apparatus and compositions useful for removing organic substances from substrates, for example, electronic device substrates such as microelectronic wafers or flat panel displays, are provided. Processes are presented that apply a minimum volume of a composition as a coating to the inorganic substrate whereby sufficient heat is added and the organic substances are completely removed by rinsing. The compositions and processes may be suitable for removing and, in some instances, completely dissolving photoresists of the positive and negative varieties as well as thermoset polymers from electronic devices.

Abstract: A method of simultaneously manufacturing a plurality of crankshafts includes positioning a single core within a cavity of a mold having a first half and a second half together forming an exterior shape of the plurality of crankshafts. The exterior shape of each of the plurality of crankshafts produced thereby includes a plurality of pin bearing journals and a plurality of main bearing journals. The method also includes introducing via a mechanism into the cavity a molten metal to form the plurality of crankshafts. As the molten metal flows into the cavity and around the single core, a hollow section extending through at least one of the plurality of pin bearing journals and at least one of the plurality of main bearing journals of each of the plurality of crankshafts is formed. A system for simultaneously manufacturing a plurality of reduced mass crankshafts using the above method is also disclosed.

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.