Abstract: This invention relates to an aircraft having an auxiliary power system, the auxiliary power system, including: a reciprocating engine having an air inlet and an exhaust system; a compressed air source for providing compressed air to the air inlet; and, an electrical generator for providing electrical power.

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: This invention relates to a unison ring assembly, comprising: a first unison ring and a second unison ring concentrically aligned along a principal axis, the first and second rings being rotatable about the principal axis; and, a gear mechanism for simultaneously rotating the first and second unison rings about the principal axis.

Abstract: A method of designing a nacelle for a gas turbine engine includes defining an initial geometry for the nacelle, pivoting, at each of one or more positions on a highlight and in a plane of a respective longitudinal section, a front portion of a section of an intake lip lying in the respective longitudinal section about the highlight, and obtaining an altered geometry for the nacelle by adjusting surfaces of the intake neighbouring the pivoted front portion to smoothly blend the surfaces of the pivoted front portion to unadjusted surfaces of the intake further removed from the pivoted front portion.

Abstract: A leaf seal effects a seal between two, coaxial, relatively rotating components. The leaf seal has an annular pack of stacked leaves or a plurality of axially arranged annular packs of stacked leaves. The or each pack is mountable to one of the components with its leaves extending towards the other component such that the leaf edges of the pack are presented for wiping contact with the other component. The leaf seal further has upstream and downstream coverplates at the respective axial ends of the seal. Each coverplate is spaced from the adjacent annular pack by a respective axial gap. When viewed in the axial direction, each coverplate covers at least a portion of the radial extent of the adjacent pack. The upstream and/or the downstream coverplate is flexible to axially deflect under differential pressures which the seal experiences in operation.

Abstract: A consolidation device has a dispensing assembly configured to dispense a composite precursor material onto a surface of a mould, and a first nozzle assembly configured to direct a fluid stream onto the free surface of the dispensed composite precursor material. The use of a fluid flow to consolidate the dispensed composite precursor material onto the surface of the mould makes the device simpler, more cost effective and causes less damage to the surface of the composite article.

Abstract: A combustor head arrangement including a heatshield including an aperture therethrough. A meter panel having a cold side and a hot side, an aperture and a slot. At least one of the meter panel and the heatshield has a retaining feature on the cold side; one of the meter panel and the heatshield has an anti-rotation feature. The arrangement includes a burner seal sized to fit through the aperture in the meter panel from the hot side towards the cold side. The burner seal has a tang configured to pass through the slot when the burner seal is in a first orientation and to be retained by the retaining feature and the anti-rotation feature when the burner seal is rotated to a second orientation. Also a method of assembling the combustor head.

Abstract: This invention relates to a current limiter comprising a first circuit portion arranged in parallel with a second circuit portion, the first circuit portion comprising a superconductor element arranged in series with a switching arrangement, the second circuit portion comprising a load element, the superconductor element being disposed within a cooling chamber, and the cooling chamber and the switch being disposed within a vacuum chamber, wherein the switching arrangement comprises: a mechanical actuator which is operable between a closed condition in which current is conducted through the first circuit portion and an open condition in which current is diverted from the first circuit portion through the second circuit portion and a controller for monitoring and operating the switch.

Abstract: A bearing assembly that includes a substantially circular bearing race with a raceway on one of its radially inner or outer surfaces and a plurality of spherical bearing elements disposed around the raceway, and wherein the bearing race is configured to, in use, bias the bearing elements towards a bearing region of a shaft.

Abstract: A threaded fastener assembly comprising a threaded fastener (12) and a length of locking wire (16) comprising a shape memory alloy material. The locking wire (16) is pre-worked such that the wire contracts when the locking wire (16) is heated from a temperature below an austenite start temperature (As) of the locking wire (16) to a temperature above the austenite start (As) temperature of the locking wire (16).

Abstract: A control system 42 for a machine comprising a plurality of independently replaceable machine modules 38 comprises a controller 40 operable to control operation of the machine 36. Memory 46 stores machine data for use by the controller 40. Communication means 44 are operable to provide communication for data transfer between the controller 40 and the memory 46. The memory includes a plurality of memory modules associated with respective machine modules 38. Each of the memory modules 46 is replaceable with the respective associated machine module 38 and independently of other memory modules 46. The communication means 44 is operable to provide communication for data transfer between the controller 40 and a replacement memory module 46 associated with a replacement machine module 38.

Abstract: A method of sealing a gap between an aerofoil component (30) and a further component (32). The method comprises placing the aerofoil component (30) in close proximity with the further component (32) to define a gap (38) therebetween, applying a thermoplastic material (20) to the gap (38) in a molten phase and cooling the thermoplastic material (20) to set the thermoplastic material (20).

Abstract: A heat exchanger is provided in which heat exchanger shells are formed by electro forming about a mandrel. The shells are attached and joined to provide a heat exchanger module. As the shells are not press formed problems with respect to material elongation to achieve deep grooves in the shells are potentially avoided and shells can be created with more desirable thickness to achieve more efficient heat exchange. Furthermore, reduced shell thickness will also reduce weight and therefore improve the acceptability of heat exchangers in particular applications such as those associated with aerospace and automotive sports.

Abstract: The present invention provides an electrical raft comprising a rigid material having multiple electrical conductors embedded therein. The electrical raft comprises an electrical connector having a first set of electrical contacts connected to at least one of the electrical conductors, a second set of electrical contacts for electrical connection to another component, and a housing having a first end and a second end. The first set of electrical contacts is at the first end and the second set of electrical contacts is at the second end. The first end of the housing is at least partly embedded in the rigid material, and the second end of the housing is accessible from outside the electrical raft, allowing the electrical raft to be electrically connected to said other component. The electrical connector has a back-shell which sealingly encloses the first end of the housing to prevent ingress of contaminants into the connector.

Abstract: A method of selectively sealing at least one cooling hole provided on an aerofoil component (10). The method comprises applying a thermoplastic material to one or more selected cooling holes (12, 14) in a molten phase, and cooling the thermoplastic material to set the thermoplastic material.

Abstract: A gas turbine engine control apparatus comprises a controller 34, a memory 36 associated with the controller 34 and inputs 38 for measurement data from an engine. The controller 34 determines the start of a monitoring cycle at 73, receives measurement data at the inputs 38 during the monitoring cycle, manipulates the measurement data to provide an incremental deterioration value representing deterioration occurring within the engine and during the monitoring cycle, and uses the incremental deterioration value at 72 to update a deterioration value 74 stored in the memory 36, and determines the start of a further monitoring cycle.

Abstract: A turbomachine casing assembly includes a first casing element, located radially outward of one or more rotating aerofoil elements of a turbomachine, and a second casing element, located radially distal to the first element. A void is provided at a first end of the first element, between radially proximal faces of the first and second elements. The first end of the first element is located against a corresponding first end of the second element by an energy absorbing element. The first element includes a cantilever, arranged in a region extending along the first element from the first end with a pivot axis at its mid-portion. Release of one of the rotating aerofoil elements, resulting in impact with the first element, further results in the cantilever bending into the void between the first and second elements, enabling the rotating aerofoil element to be trapped within the casing assembly.

Abstract: A retaining bracket for retaining a plurality of threaded fasteners in position on a component, and a retaining assembly including the retaining bracket and at least one fastener. Each fastener includes a bead having a first face which, in use, lies adjacent a surface of the component against which the fastener is installed, a second face distal from the first face, and a side face extending between the first and second faces. The bracket includes a substantially rigid base member, and a plurality of engagement members extending from the base member at spaced locations therealong. Each engagement member is configured to engage with only the side face of each respective fastener head such that, in an installed condition, the base member extends only along the side faces of the fasteners between the respective first face and second face.

Abstract: A method of managing energy and/or power in a vehicle, including: one or more vehicle power systems adapted to control one or more power consuming components of the vehicle and one or more power producing components of the vehicle; and one or more propulsive power systems adapted to control a propulsive power unit of the vehicle. The method includes: proposing a vehicle route for a predetermined mission and/or destination; determining a time-based operational plan for each of the vehicle power consuming components; determining the power required by the vehicle power consuming components and the propulsive power required by the vehicle; determining the power required from the vehicle power producing components and the propulsive power required by the propulsive power unit as a function of time during the operational plan; and varying the proposed vehicle route and/or the operational plan to optimize a predetermined performance criterion for the vehicle.

Abstract: An apparatus 2 comprising a cryogenic chamber 4 and a galvanic input interface 6 to the cryogenic chamber 4 configured to receive a lower amplitude electric current 8. A converter 10 is located within the cryogenic chamber 4 and configured to convert the lower amplitude electric current 8, provided by the galvanic input interface 6, to a higher amplitude electric current 12 for supply to a load 14 within the cryogenic chamber 4. A controller 16 is configured to control the converter 10 and to detect the onset of quench by comparing the duration of the charge/discharge cycle of the convertor with a stored value. The controller 16 may also compare an instantaneous value of load current with a stored value of load current.