ROLLS-ROYCE PLC Patent applications |
Patent application number | Title | Published |
20160139087 | METHOD OF DETERMINING THE MAGNITUDE OF A FIELD VARIABLE OF AN ENERGY WAVE - Determining magnitude of a field variable of an energy wave through domain of interest, including steps of: defining plurality of master-particles spaced within domain, master-particles being representative of field variables of energy wave at location of respective master-particle, and defining supporting domain Ω | 05-19-2016 |
20160108817 | GAS TURBINE ENGINE SUPPORT STRUCTURES - A ducted fan gas turbine engine has a propulsive fan, a fan case surrounding the fan, a core engine, and a plurality of support structures which transmit loads from the core engine to the fan case. Each support structure has two support struts which extend from the core engine to a joint radially outwardly of the fan case. The support struts are spaced apart at the core engine but converge to meet at the joint. Each support structure further has two structural elements which extend from the joint to respective fixing positions on the fan case at opposite sides of the joint. | 04-21-2016 |
20160102751 | COUPLING AND A METHOD OF USING THE SAME - A fluid transfer coupling includes a first and second shaft assembly. The first shaft assembly includes a shaft and annular fin attached to shaft, annular fin having one or more internal passages extending therethrough. The or each internal passage connects a centre portion of shaft to a radially outwardly facing side of annular fin. The second shaft assembly includes a shaft and annular trough extending radially outwardly of shaft. The first shaft is concentrically accommodated within second shaft with annular fin being accommodated within annular trough. In use, first shaft assembly rotates at a first rotational speed and second shaft assembly rotates at a second rotational speed, with second rotational speed being greater than first rotational speed. The difference between second and first rotational speeds cause a fluid contained within annular trough to be driven radially inwardly through the or each internal passage to centre portion of first shaft. | 04-14-2016 |
20160097539 | COMBUSTION CHAMBER AND A METHOD OF MIXING FUEL AND AIR IN A COMBUSTION CHAMBER - A combustion chamber including a first fuel injector and a second fuel injector, the first and second fuel injectors being arranged to inject fuel into a mainstream flow of air with the second fuel injector arranged downstream of the first fuel injector. A method of mixing fuel and air in a combustion chamber, including injecting fuel into a mainstream flow of air with a first fuel injector; injecting fuel into the mainstream flow of air with a second fuel injector, which is arranged downstream of the first fuel injector; injecting fuel into the mainstream flow with the first fuel injector such that the resulting mixture between the first and second fuel injectors has an equivalence ratio less than the lean flame stability limit; and injecting fuel into the mainstream flow with the second fuel injector such that a combustion zone is provided downstream of the second fuel injector. | 04-07-2016 |
20160097300 | FAN TRACK LINER ASSEMBLY - 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. | 04-07-2016 |
20160083075 | AIRCRAFT - An aircraft ( | 03-24-2016 |
20160069186 | LIQUID-CAPTURING SHAFT - There is provided a liquid-capturing shaft ( | 03-10-2016 |
20160061107 | Low Pressure Shaft - A low pressure shaft is provided for interconnecting a fan or low pressure compressor of a gas turbine engine with a low pressure turbine of the engine. The shaft has an aft section whose diameter expands progressively with distance along the rearward direction of the engine. The shaft further has an annular joint portion at the rear end of the aft section for joining the shaft to a drive arm of the low pressure turbine. The rate of expansion of the diameter of the aft section decreases with distance along the rearward direction of the engine. | 03-03-2016 |
20150346066 | Asset Condition Monitoring - Invention concerns a machine fault diagnostic system. Sensors are provided for sensing an operational parameter of the machine over time in use and outputting corresponding sensor signals. A machine operation diagnosis tool is arranged to receive the sensor signals and has a data store for operational parameter data indicative of a normal mode of machine operation and operational parameter data indicative of one or more known machine faults. The diagnosis tool has one or more processor arranged to compare the received sensor signals with the operational parameter data in the data store in order to determine a match with either the normal mode of operation or the one or more known machine fault, and wherein the processor sentences an unknown fault in the event that said match is not established. The system may record unknown faults and update the diagnosis tool as unknown faults become recognizable faults. | 12-03-2015 |
20150345295 | DEVELOPMENTS IN OR RELATING TO ROTOR BALANCING - A method of reducing dynamic imbalance in a bladed rotor assembly by axially adjusting one or more of the blades so as to redistribute mass along the geometric axis of the assembly. The blades may be axially adjusted to form a counterbalancing couple. Additional correction masses may be added for supplemental correction of couple imbalance or residual static imbalance in the bladed rotor assembly. The invention offers a reduction in the weight penalty associated with conventional balancing corrections carried out on the bladed rotor assembly. | 12-03-2015 |
20150251378 | CERAMIC MATRIX COMPOSITE - The invention concerns an article ( | 09-10-2015 |
20150251371 | METHOD OF SEALING COOLING HOLES - A method of sealing a gap between an aerofoil component and a further component. The method comprises placing the aerofoil component in close proximity with the further component to define a gap therebetween, applying a thermoplastic material to the gap in a molten phase and cooling the thermoplastic material to set the thermoplastic material. | 09-10-2015 |
20150192067 | HARNESS CABLE - A conduit assembly for the communication of electricity, light or fluid, including at least one conduit, wherein the conduit assembly also includes a core member, the at least one conduit in contact with the core member and arranged in a convoluted path defined with respect to the shape of the core member, the at least one conduit thereby having a first direct length between its ends such that removal of at least a portion of the core member permits the at least one conduit to straighten in the region of the core member removal to increase its direct length to a second direct length, the second direct length being greater than the sum of the first direct length and the length removed from the core member. | 07-09-2015 |
20150083488 | ELECTRICAL HARNESS CONNECTOR - A connector is provided for joining two electrical harnesses. Each harness is formed from a flexible printed circuit board which provides a plurality of conductive tracks, and each harness has a substantially planar terminating region at which the conductive tracks of the harness fan out. One or more receiving holes are formed in each terminating region to extend to respective conductive tracks. A connector includes a connection formation which is between respective terminating regions of the two electrical harnesses. The connector further includes a housing configured to hold the respective terminating regions of the two electrical harnesses in face-to-face relationship with the connection formation sandwiched therebetween. | 03-26-2015 |
20140369830 | BEARING ARRANGEMENT - A bearing arrangement is disclosed. The bearing arrangement includes first and second bearings, with each bearing including a respective support element and a respective set of rolling elements and defining a respective load path extending through the respective support element and rolling elements. The support elements are coupled such that a load applied to either support element is transmitted through both the first and second load paths. The arrangement further includes a pair of superelastic titanium alloy elements located in the respective load paths to provide resilient movement between the bearings when a load is applied to the bearing arrangement. | 12-18-2014 |
20140367367 | ADDITIVE LAYER MANUFACTURING METHOD - An additive layer manufacturing method includes the steps of: a) laying down powder layer on powder bed, and b) focussing energy on an area of powder layer to fuse area of powder layer and thereby form a cross-section of the product; wherein steps a) and b) are repeated to form successive cross-sections of product, and wherein at least one of said steps b) involves focussing energy on an area of respective powder layer which is unsupported by a previously formed cross-section of product to thereby form a downwardly facing surface of product. Method is at least some of said successive steps b) involve focussing energy on a support area of respective powder layer, to fuse support area and thereby form successive cross-sections of a support pin within powder bed, support pin extending outwardly from downwardly facing surface of product when it is formed, so as to support downwardly facing surface. | 12-18-2014 |
20140366453 | PANEL ATTACHMENT SYSTEM AND A METHOD OF USING THE SAME - A panel attachment system comprises a panel and a casing. The panel has one fixed mount bracket, and at least one sliding mount bracket. The casing has one fixed mount boss, and at least one sliding mount boss. When the panel attachment system is in use, the fixed mount bracket is fixedly secured to the fixed mount boss, and the or each sliding mount bracket is slidingly engaged with a corresponding respective one of the or each sliding mount boss. This enables the panel to be detachably connected to the casing, such that any relative in-plane thermal expansion between the panel and the casing is accommodated by corresponding relative movement between the one or more sliding mount brackets and the corresponding one or more sliding mount bosses. | 12-18-2014 |
20140365166 | BLADE TIP TIMING - A method of analysing blade tip displacements (dijk) derived from a rotor having an array of blades that rotate at a rotational speed (ω). The blades are monitored by an array of stationary timing probes for at least two revolutions (j) of the rotor. Define asynchronous displacement (dijk_A) as a sum of a sinusoidal term (Va) and an offset per probe term (Oo). Define synchronous displacement (dijk_S) as a sum of a sinusoidal term (Vs) and a common offset term (Cc). Solve the asynchronous displacements (dijk_A) using the blade tip displacements (dijk) to give asynchronous amplitude (|a|), offset per probe (ok) and asynchronous residuals (rijk_A). Solve the synchronous displacements (dijk_S) using the blade tip displacements (dijk) to give synchronous amplitude (|s|), common offset (cj) and synchronous residuals (rijk_S). | 12-11-2014 |
20140363274 | BLADE TIP TIMING - A method of analysing blade tip timing data obtained from an array (P | 12-11-2014 |
20140361649 | COOLING ARRANGEMENT FOR AN ELECTRICAL MACHINE - This invention relates to a laminated core for an electrical machine, including: a plurality of laminations configured to define a channel in a surface of the laminated core for the flow of a cooling fluid, wherein the channel has a base and at least one side wall, the at least one side wall having a stepped profile. | 12-11-2014 |
20140360206 | AIRCRAFT POWERPLANT - An aircraft propulsion power plant for use in an aircraft includes one or more core engines housed in an airframe of the aircraft, one or more secondary propulsion units, each of the one or more secondary propulsion units being removably attached to the airframe, and one or more power transmission means, each of the one or more power transmission means being configured to transmit mechanical power from the or each core engine to a corresponding one of the or each secondary propulsion unit when the or each secondary propulsion unit is attached to the airframe. | 12-11-2014 |
20140355007 | BLADE TIP TIMING - A method of determining rotor blade axial displacement (b | 12-04-2014 |
20140348689 | NICKEL ALLOY - A nickel-base alloy having the following composition (in weight percent unless otherwise stated): Cr 10.5-15.0; Co 1.7-8.8; Fe 0-5.9; Si 0-0.65; Mn 0-0.65; Mo 0.3-2.3; W 2.3-4.4; Al 2.7-4.1; Nb 1.0-4.2; Ti 1.0-3.0; Ta 2.0-5.0; Hf 0.0-0.6; C 0.02-0.06; B 0.015-0.035; Zr 0.035-0.11; S<20 ppm; P<60 ppm; the balance being Ni and incidental impurities. The alloy has an improved combination of properties (principally resistance to surface environmental damage and dwell fatigue crack growth) compared with known alloys, and is intended to operate for prolonged periods of time above 700° C., and up to peak temperatures of 800° C. | 11-27-2014 |
20140348648 | AEROFOIL RECAMBERING - A method of recambering an aerofoil section. A position on one of the surfaces that intersects with a passage shock between adjacent aerofoils is determined and then projected as a shock position onto the camber line. A shock region encompassing the shock position and extending in a chordal direction towards the leading and trailing edges is defined. The camber line is recalculated in an upstream region using semi-inverse design. The camber line is extrapolated across the shock region to match a geometric criterion. The camber line is recalculated in a downstream region using semi-inverse design. | 11-27-2014 |
20140342165 | ELECTRICAL APPARATUS ENCAPSULANT - An encapsulant composition has a silica containing inorganic-organic nano-hybrid matrix, particles of refractory ceramics suspended in the inorganic-organic nano-hybrid matrix, and, optionally, glass or ceramic fibres. The encapsulant may also contain ceramic coated metallic particles, and in some embodiments, a solvent or binder. The formulations can include a solvent, which may be removed during a curing process, or may be solvent-less | 11-20-2014 |
20140341721 | SHROUD ARRANGEMENT FOR A GAS TURBINE ENGINE - Described is a shroud arrangement for a gas turbine engine, comprising: a seal segment for bounding a hot gas flow path within the gas turbine engine, the seal segment being attached to a casing of the engine via at least one fore attachment and at least one aft attachment, the fore and aft attachment restricting radial movement of the seal segment relative to the engine casing; and, an axial restrictor which prevents axial movement of the seal segment relative to the engine casing, the axis being the principal rotational axis of the engine, wherein the fore and aft retention features are slidably engaged with a carrier segment or engine casing from a common direction. Also described is a gas turbine engine having the shroud arrangement. | 11-20-2014 |
20140341717 | SHROUD ARRANGEMENT FOR A GAS TURBINE ENGINE - A seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine is described. The seal segment is upstream of a second component of the gas turbine engine relative to the hot gas flow path. The seal segment comprises: a plate having: a downstream trailing edge; an inboard side which faces the hot gas flow path when in use; an outboard side; and a first part of a two part seal attached on the outboard side, wherein a second part of the two part seal is attached to the second component such that in an assembled gas turbine engine the two part seal provides an isolation chamber which is in fluid communication with the hot gas flow path via the trailing edge of the plate. A gas turbine having the seal segment is also described. | 11-20-2014 |
20140341711 | SHROUD ARRANGEMENT FOR A GAS TURBINE ENGINE - A seal segment for bounding a hot gas flow path within a gas turbine engine, including: a plate having an inboard side which bounds the hot gas flow path in use, an outboard side and fore and aft cooling circuits, wherein the fore and aft cooling circuits are fluidically separated from one another within the plate and each has at least one tortuous path between an inlet on the outboard side of the plate and an exhaust. | 11-20-2014 |
20140341707 | SHROUD ARRANGEMENT FOR A GAS TURBINE ENGINE - A seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine, including: a plate having an inboard hot gas flow path facing side and an outboard side; a bulkhead extending from the outboard side of the plate which defines a fore portion and an aft portion; a first cooling circuit within the plate for cooling a first portion of the plate; a second cooling circuit within the plate for cooling a second portion of the plate; wherein the first cooling circuit is in fluid communication with the fore portion and the second cooling circuit is in fluid communication with the aft portion and the first and second cooling circuits are fluidically isolated from one another. Also described is a method of cooling a seal segment in a gas turbine engine. | 11-20-2014 |
20140341704 | HEAT EXCHANGE ARRANGEMENT - A heat exchange arrangement for a gas turbine engine. The arrangement includes a first conduit for an engine component cooling fluid and a second conduit for a second fluid. The arrangement further includes a heat exchange portion in which fluids flowing through the first and second conduits are in a heat exchange relationship. A valve is provided, which is configured to moderate the mass flow rate of one of the fluids through the heat exchange portion. The arrangement includes divert valve in the first conduit which diverts flow to the second conduit as the flow in the second conduit is moderated to reduce thermal shock in the heat exchange portion. | 11-20-2014 |
20140341256 | METHOD AND SYSTEM FOR MONITORING THE PERFORMANCE OF A HEAT EXCHANGER - A system for monitoring the performance of a fluid heat exchanger for use with an engine includes a heat exchanger having a first fluid flow path therethrough and a second fluid flow path therethrough, a first temperature sensor positioned in the first fluid flow path at an exit from the heat exchanger, a second temperature sensor positioned in the second fluid flow path at an entry to the heat exchanger, a processor and an alert generator. The processor is adapted to receive a first temperature measurement value from the first temperature sensor, and a second temperature measurement value from the second temperature sensor, the processor being further adapted to calculate a temperature difference between the first and second temperature measurement values. The alert generator is adapted to generate an alert signal to a user, the alert signal being generated if the temperature difference is greater than a threshold value. | 11-20-2014 |
20140338193 | BALANCING METHOD - A method of balancing a set of retaining and locking plates used to retain a row of gas turbine engine aerofoil blades in attachment to a rotor disc, includes: (i) providing a weighing plate having a circular track; (ii) providing a non-rotating, static balancing apparatus capable of detecting unbalance in the weighing plate; (iii) positioning the weighing plate on the static balancing apparatus, and positioning the set of retaining and locking plates on the track in an arrangement corresponding to a possible arrangement for the set of plates in use in the engine; and (iv) repositioning the retaining and locking plates on the track to arrive at a balanced arrangement for the set of plates. | 11-20-2014 |
20140335344 | METALLIC FOAM MATERIAL - The invention provides a metallic foam material with better mechanical properties than known foamed materials, and a method of making such a material. Although known foamed metals are light in weight, and sandwich structures formed of such materials can be formed into structural components, the tendency for the structure to crush and fracture under compressive loading, with consequent crack propagation, limits their use in applications in which the integrity of the component is important. The invention addresses this problem by providing a fibre-reinforced foam that combines the tensile strength of a high strength fibre such as carbon fibres with the impact resistance (through crushing and deformation) of metallic foam. The metal foam imparts a greater strength to the carbon-fibre-reinforced plastics (CFRP) part of the structure than it would have by itself. Under tensile loads, the fibre reinforcement gives the metallic foam enhanced strength and low creep. | 11-13-2014 |
20140333127 | AIRCRAFT ELECTRICAL SYSTEM - An aircraft electrical network including a first starter generator mechanically coupled to a first shaft of an aircraft main engine. The first starter generator is configured to turn the first shaft of the main engine in a starting mode, and to generate electricity from the first shaft of the gas turbine engine in a generating mode. The network further includes a DC electrical bus electrical coupled to one or more electrical loads and an AC electrical bus electrically coupled to the first starter generator. The DC electrical bus is electrically coupled to the AC electrical bus via a bi-directional AC/DC converter, which is configured to provide AC electrical power from the DC electrical bus to power the first starter generator when the first starter generator is in a starting mode, and DC electrical power to the DC electrical bus when the first starter generator is in a generating mode. | 11-13-2014 |
20140333126 | ELECTRICAL SYSTEM FOR AN AIRCRAFT - This invention relates to an electrical system for an aircraft, comprising: a first main generator connected to at least one load via a first bus; a second main generator connected to at least one load via a second bus; a first and a second auxiliary generator associated with the first and second buses, the auxiliary generators being driven by a common prime mover. | 11-13-2014 |
20140331751 | EQUIPMENT MONITORING SYSTEM - The invention concerns an asset monitoring system ( | 11-13-2014 |
20140328668 | ELECTRO-MAGNETIC COUPLING SYSTEM - An electro-magnetic coupling system for transferring torque between a pair of coaxial spools of a gas turbine engine is provided. The system includes a first rotor rotatable with one of the spools, a second rotor rotatable with the other of the spools, and a stator. The first and second rotors and the stator are coaxial with each other. The second rotor operably couples the first rotor and the stator. The first rotor carries a plurality of magnetic flux-producing formations which produce a first magnetic field. The stator carries a plurality of electrical winding coils which are energisable to generate a second magnetic field. The second rotor carries an arrangement of interpoles which modulate the first and second magnetic fields such that the modulated fields interact to transfer torque between the spools. | 11-06-2014 |
20140328030 | ELECTRICAL HARNESS CONNECTOR - An electrical connection between two electrical harnesses is provided. The electrical harnesses include flexible printed circuits with embedded conductive tracks, each of which terminates in a receiving hole in a respective terminating region The terminating regions are connected together using conductive pins. The connection formation is then encapsulated by an encapsulating body formed of an insulating. The encapsulating body seals and protects the electrical connection, which is thus reliable and robust. | 11-06-2014 |
20140325994 | ELECTRICAL CONNECTORS - An electrical raft is provided comprising a rigid material having multiple electrical conductors embedded therein. An electrical connector is provided to the raft that has a back-shell which is embedded in the rigid material and which joins to a connector body to enclose a first end of a housing of the connector body. The housing also has a second end at which electrical contacts are provided for connection to another component. The connector body is detachable from the back-shell to electrically disconnect it from the embedded electrical conductors and allow removal of the connector body from the electrical raft. In this way, the connector body may be readily removed, for example for upgrade or repair, whilst retaining a robust and reliable connection. | 11-06-2014 |
20140325992 | ELECTRICAL UNIT WITH ELECTRICAL CONNECTOR - An electrical unit comprises an electrical connector having a set of elongate electrical terminals which are each a one-piece component. The terminals extend into the unit such that first ends of the terminals are connected to multiple electrical conductors within the unit and second ends of the terminals project from a surface of the unit. A collar is formed at the surface of the unit to at least partially encircle the projecting second ends. This arrangement allows the unit to be electrically connected at the electrical connector by press fitting to a terminating region of a flexible electrical harness, the collar defining a recess in which the terminating region is located. | 11-06-2014 |
20140322068 | ALLOY COMPOSITION - A molybdenum based alloy composition including between 15% and 20% niobium and 0.05% and 0.25% carbon | 10-30-2014 |
20140321985 | ROTOR TIP CLEARANCE - A method of characterising mechanical and thermal growth of a rotor tip clearance arrangement and a method of controlling such an arrangement. The characterisation method comprising constructing a finite element model and calibration cases; run the model for the calibration cases to obtain displacements; and calculating component growth therefrom. The growth is characterised and scaled for the operating conditions. The clearance is calculated in a time step from the growths and input to a control arrangement for subsequent time steps. | 10-30-2014 |
20140318759 | METHOD OF CONTROLLING A COOLING SYSTEM - A method of controlling an aircraft gas turbine engine cooling system. The cooling system includes a heat exchanger having a first fluid path through which fan air flows, and a second fluid path through which relatively hot compressor air flows. The cooling system includes a valve configurable between an open position corresponding to a first operating mode, where fan air flows through the first path cooling the compressor air in the second path to a lower temperature, and a closed position corresponding to a second operating mode, where fan air may flow through the first path at a reduced rate, thus the compressor air in the second path could be cooled to a lesser extent. The valve is operated in first mode when the aircraft is in a descent mode, or when turbine entry temperature is above a predetermined amount. Otherwise, the valve is operated in second mode. | 10-30-2014 |
20140316555 | METHOD OF GENERATING A TOOL PATH - Method for determining an adaptive tool path: provides an aerofoil with deposition plane; determines deposition plane points corresponding to leading and trailing edges and circle centre constrained by suction and pressure surfaces at their greatest distance apart; determines circle centre point edge position passing through deposition plane points; determines trailing and leading edge reference lines extending from the circle centre point through trailing and leading edge points, respectively and mid-reference line(s) extending from the circle centre point through mid-reference point(s) between leading and trailing edge points; trims and determines each mid reference line to the bounds of the suction and pressure surfaces; applies an adaptive factor to each mid reference line providing an adaptive point for each mid-reference line; determines an spline extending through the leading and trailing edge points and each adaptive point; and traverses a tool along the spline or offset path from the spline by a factor. | 10-23-2014 |
20140314577 | PROPELLOR BLADE RETENTION - A propeller blade retention arrangement having a propeller blade comprising in radial sequence an aerofoil portion, a shank portion and a root portion. The root portion having first cross-sectional area close to the shank portion and second cross-sectional area at the end distal to the aerofoil portion, wherein the second cross-sectional area is greater than the first cross-sectional area. At least two cheeks each having an inner surface arranged to abut the root portion, an outer surface that is threaded and edge surfaces that abut another of the at least two cheeks; wherein the at least two cheeks are arranged to surround the root portion in circumferential abutment. A collar having a threaded inner surface arranged to threadingly engage the outer surfaces of the at least two cheeks. | 10-23-2014 |
20140311580 | AIR INTAKE AND A METHOD OF CONTROLLING THE SAME - An air intake guide for a jet propulsion power plant for a supersonic aircraft comprises an intake aperture, an intake centre body and an intake adjustment device. | 10-23-2014 |
20140308136 | METHOD OF MANUFACTURING A COMPOSITE MATERIAL INCLUDING A THERMOPLASTIC COATED REINFORCING ELEMENT - A method of through-thickness reinforcing a laminated material is disclosed, in which a reinforcing element is coated with a thermoplastic layer. The reinforcing element is inserted into a base material, and a matrix material, such as a polymeric, is included in the base material. The combination is then cured, or heated, such that the thermoplastic layer and the matrix material diffuse into each other, thereby forming an interphase region around the reinforcing element. This interphase region helps to prevent cracks from propagating from the reinforcing element. | 10-16-2014 |
20140308135 | METHOD OF THROUGH-THICKNESS REINFORCING A LAMINATED MATERIAL - A method of providing through-thickness reinforcement of a laminated material which includes a matrix material including a step of creating a locally heated zone in the laminated material so as to locally soften the matrix material by focussing a set of at least two energy beams at a location where through-thickness reinforcement is required and a step of inserting a reinforcement element through the thickness of the laminated material at the location of the locally heated zone to through-thickness reinforce the laminated material. | 10-16-2014 |
20140305270 | SHAPING OF AEROFOIL EDGES - A portable device for shaping an edge of an aerofoil comprises a housing, a cutting tool mounted in the housing (the cutting tool having a cutting edge to remove material from the edge) and a plurality of guides mounted in the housing, so that in use the aerofoil engages with the guides to locate the edge of the aerofoil relative to the cutting edge and to permit movement of the housing in a cutting direction so as to remove material from the edge of the aerofoil. The device is characterised in that the cutting tool is mounted so that in use the cutting edge can move relative to the edge of the aerofoil in a direction generally perpendicular to the cutting direction. | 10-16-2014 |
20140305136 | MOUNTING ARRANGEMENT - A gas turbine engine is provided that has a rigid dressing raft mounted to a rigid part of the gas turbine engine. The rigid dressing raft includes at least a part of a component or system of the gas turbine engine. For example, the rigid dressing raft may have electrical conductors embedded therein that are a part of the electrical system of the gas turbine engine. | 10-16-2014 |
20140305133 | DUAL CHANNEL ACCELEROMETER AND METHOD OF MANUFACTURING THE SAME - A dual output accelerometer having first and second output channels, comprises a supporting base, a first transducer comprising a plurality of inter-connected first piezoelectric elements, a second transducer comprising a plurality of inter-connected second piezoelectric elements and a seismic mass. | 10-16-2014 |
20140301836 | VANE ASSEMBLY AND METHOD OF MAKING THE SAME - A vane assembly for a gas turbine engine comprises at least one vane, a first platform and a second platform. The at least one vane has a first end and an opposite second end with the first end of the at least one vane being secured in a corresponding first aperture in the first platform, and the second end of the at least one vane being secured in a corresponding second aperture in the second platform. | 10-09-2014 |
20140294572 | WALL SECTION FOR THE WORKING GAS ANNULUS OF A GAS TURBINE ENGINE - A seal segment is provided for a shroud ring of a rotor of a gas turbine engine. The seal segment is positioned, in use, radially adjacent the rotor. The seal segment has two or more spaced passageways. In use, a respective support bar can be contained within each passageway. The support bars allow attachment of the seal segment to the engine casing. Each passageway has an elliptical or substantially elliptical cross-section with a minor diameter and a major diameter, the minor diameter being substantially aligned with the radial direction. The respective support bar has a correspondingly elliptical or substantially elliptical cross-section for a close fit in the passageway. | 10-02-2014 |
20140294571 | SEAL SEGMENT - A seal segment is provided for a shroud ring of a rotor of a gas turbine engine. The seal segment is positioned, in use, radially adjacent the rotor. The seal segment includes a body portion having front and rear sides which each contain a respective slot that extends in the circumferential direction so that a respective hook formation is insertable into each slot for attaching the seal segment to the engine casing. The body portion is formed from continuous fibre reinforced ceramic matrix composite, reinforcing fibres of the composite wrapping around each slot so that, at the base of the slot, the reinforcing fibres are parallel to the surface of the body portion. | 10-02-2014 |
20140290271 | MOUNTING ARRANGEMENT - A rigid electrical raft is provided to a gas turbine engine via a fusible mount arrangement. The rigid electrical raft may be a part of an electrical system of the gas turbine engine, for example a part of the electrical harness. The fusible mount is arranged to break when a predetermined load is applied. The rigid electrical raft may be attached to a fan case of the engine, and the predetermined load may that which results from a fan blade being released from the hub. This ensures that the rigid electrical raft is protected from the load. | 10-02-2014 |
20140288865 | BLADE TIP TIMING - A method of zeroing displacement data derived from a rotor having an array of features monitored by an array of stationary timing probes. The method includes steps to calculate the displacement at each probe for each of at least two measured revolutions from time of arrival measurements. Each displacement is defined as a sum of a common term and a unique term. The set of displacements is solved for the common term and the unique terms. A probe offset is calculated from each unique term. The zeroed displacements are determined by subtracting the common term and probe offset from the calculated displacements for each probe. | 09-25-2014 |
20140286765 | COMPOSITE AEROFOIL VANE - 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 fibres extending in a generally radial direction and a plurality of second reinforcing fibres extending in generally axial and circumferential directions. The second fibres are interlaced with the first fibres so as to form a more unified and integrated structure, and to prevent the first reinforcing fibres from moving relative to one another. | 09-25-2014 |
20140271227 | MANUFACTURE OF HOLLOW AEROFOIL - A method of manufacturing a hollow aerofoil component for a gas turbine engine includes using a capping panel to cover a pocket in a pocketed aerofoil body. During manufacture, the outer surface of the capping panel is located relative to the pocketed aerofoil body. This ensures that the outer surface of the capping panel is located as accurately as possible. This means that the capping panel can be made to be as thin as possible, which in turn reduces weight and material wastage. Once the capping panel has been located in position, it may be welded to the aerofoil body in order to produce the hollow aerofoil component. | 09-18-2014 |
20140271220 | EROSION RESISTANT COATING - A platinum plus chromium coating applied to the roots and firtrees of turbine blades where the inclusion of chromium creates a single phase outer zone which minimises diffusion paths for sulphur which can preferentially diffuse down phase boundaries and enables a chromium rich outer oxide scale to form on top of the coating. | 09-18-2014 |
20140271207 | FAN BLADE - A rotor blade assembly for a gas turbine engine includes two aerofoil members joined together at their roots by a blade assembly attachment web. The rotor blade assembly is made from a composite material, for example an organic fibre composite material. The blade assembly attachment web is used to attach a plurality of rotor blade assemblies to the rest of the gas turbine engine in order to form a rotor stage. The rotor stage may, for example, be the fan stage of a turbofan gas turbine engine. | 09-18-2014 |
20140271157 | FAN CONTAINMENT SYSTEM - A fan containment system arranged to be fitted around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. Each fan blade has a respective tip. The system includes: a cylindrical fan case including a hook projecting in a radially inward direction and positioned axially forward of the radial array of fan blades; a fan track liner disposed on the radially inner surface of the fan case; and a damaging tool which projects radially inwards from the fan case towards the tips. The damaging tool has a tip radially outward of the fan blade tips. The damaging tool is configured that in the event that one of the fan blades is released from the hub, the tip of the damaging tool damages the fan blade tip of the released fan blade to promote penetration of the fan blade into the fan track liner. | 09-18-2014 |
20140271148 | ENGINE CASING ASSEMBLY - A gas turbine engine casing assembly has a first casing element which is located radially outward of one or more rotating aerofoil elements of the gas turbine engine. The first casing element is radially enclosed by a track element, a septum layer, a second casing element and a fan case. The track element is formed from an abrasion resistant material in order to prevent abrasion of the septum layer during excoriation of the first casing element. | 09-18-2014 |
20140271119 | METHOD AND APPARATUS FOR CONTROLLING MODULATED COOLING OF A GAS TURBINE COMPONENT - A method of modulating the cooling of a gas turbine component is disclosed. The method includes determining a target component temperature at which the gas turbine component can be maintained without the gas turbine component experiencing a failure over the course of an indicated life of the gas turbine component; scheduling a cooling air value to the target component temperature; and determining one or more of a demanded cooling air temperature and a demanded cooling air mass flow rate based on the scheduled cooling air value. | 09-18-2014 |
20140260755 | MULTI-JOINTED ARM ASSEMBLY - A multi jointed robot arm includes at least first and second link members connected by a connection arrangement and at least a first control cable. First and second ends of the first control cable engage with first and second engagement point of the first link member and first and second attachment points of the second link member. The assembly further includes a first actuator configured to selectively tension the first and second ends of the first control cable such that the second link member pivots toward a first or second side, wherein the connection arrangement is arranged to pivot at a first pivot point located substantially along a notional line extending between the first and second attachment points, and to pivot at a second pivot point extending between the first and second engagement points. | 09-18-2014 |
20140260625 | ULTRASONIC INSPECTION METHOD - An ultrasonic inspection method for inspecting a first article. The method includes, in a first inspection process: measuring the distance between a first surface of the first article and a nominal axis at three or more measurement locations along the axis of the surface; using the measured distances to produce a mathematical model of the surface of the first article; transmitting an ultrasonic wave from a first side of the first article through the first surface of the first article at a plurality of inspection locations along the axis of the first surface, and receiving a transmitted waveform which has passed through at least part of the first article; using the model to normalise each transmitted waveform at each inspection location to the nominal axis; and identifying a signature signal from the normalised transmitted waveform at each inspection location. | 09-18-2014 |
20140255170 | CMC TURBINE ENGINE COMPONENT - A component of a gas turbine engine is formed from a continuous fibre reinforced ceramic matrix composite (CMC). The component has a sealing portion which, in use, makes sealing contact with an adjacent component of the engine. The sealing portion comprises a recess formed in the CMC and filled with a finer grade ceramic relative to the surrounding CMC, a metal or an intermetallic. | 09-11-2014 |
20140252159 | ENGINE INSTALLATION - A fuselage mounted gas turbine engine installation the installation includes at least one propeller stage and a gas turbine core arranged in use to drive the propeller stage. The core is external to the fuselage and the rotational axes of the core and propeller stage are offset with respect to each other. | 09-11-2014 |
20140250917 | COMBUSTION CHAMBER HEAT SHIELD AND SEAL ASSEMBLY AND A METHOD OF MANUFACTURING A COMBUSTION CHAMBER HEAT SHIELD AND SEAL ASSEMBLY - A gas turbine engine combustion chamber heat shield and seal assembly comprises a heat shield and a seal. The heat shield has an aperture and the seal is located in the aperture in the heat shield. The seal comprises an annular member having an upstream end, a middle and a downstream end. The upstream end of the seal has a diameter greater than the diameter of the aperture in the heat shield, the middle has a diameter less than the diameter of the aperture in the heat shield and the downstream end of the seal has a diameter greater than the diameter of the aperture in the heat shield. | 09-11-2014 |
20140248142 | GAS TURBINE ENGINE IMPELLER SYSTEM FOR AN INTERMEDIATE PRESSURE (IP) COMPRESSOR - A gas turbine engine includes a compressor assembly that is rotationally coupled to a shaft, the compressor assembly having a centrifugal impeller and a shroud covering a bladed portion of the centrifugal impeller. The compressor assembly includes a diffuser that is attached to the shroud via a pair of flanges, the diffuser including a strut that is mounted through an aft-extending leg to a base of an intercase. A sealing assembly is attached to the diffuser and is attachable to a transition duct that is positioned to receive air from the diffuser. The sealing assembly is configured to prevent air from passing through the sealing assembly while allowing relative motion to occur between the transition duct and the diffuser. | 09-04-2014 |
20140248125 | CHAMBER FLUID REMOVAL SYSTEM - A chamber fluid removal system including a pump and an ejector is disclosed. The system is arranged in use to pump fluid from a chamber using the pump and deliver it to the ejector as a motive fluid and the system being further arranged to draw fluid from the chamber or from a second chamber as an entrained fluid by entraining it using the ejector and the motive fluid. | 09-04-2014 |
20140248122 | HIGH PRESSURE COMPRESSOR THERMAL MANAGEMENT - A gas turbine engine includes an inner shaft extending axially along the gas turbine engine, a plurality of disks extending radially inwardly and toward the inner shaft, at least one hole in at least one of the plurality of disks, and an obstruction positioned between the inner shaft and an end of the disk having the at least one hole, such that a bore flow that flows along an axial length of the inner shaft is obstructed from flowing along the shaft by the obstruction, and forced to flow radially outward from the obstruction, through the at least one hole, and radially inward toward the inner shaft. | 09-04-2014 |
20140245741 | STATOR VANE ROW - In a gas turbine engine, each vane has pressure and suction surfaces extending radially from an inner to outer endwall of an annular working gas engine passage, and extending axially from a leading to a trailing edge of the vane. Each vane has transverse sections providing respective aerofoil sections. Neighbouring vanes are arranged in unequally-shaped pairs in which either: (i) the first vane of each pair exhibits compound lean, and the second vane of the pair exhibits reverse compound lean or has substantially no tangential lean, (ii) the first vane of each pair has substantially no tangential lean, and the second vane of the pair exhibits reverse compound lean, or (iii) the first vane of each pair exhibits reverse compound lean, and the second vane of the pair exhibits greater reverse compound lean. Within each unequally-shaped pair the first vane is on the pressure surface side of the second vane. | 09-04-2014 |
20140241871 | VANE STRUCTURE AND A METHOD OF MANUFACTURING A VANE STRUCTURE - A fuel injector comprises a swirler and the swirler comprises a plurality of vanes, a first member and a second member. The second member is arranged coaxially around the first member and the vanes extend radially between the first and second members. The vanes have leading edges and the second member has an upstream end. The leading edges of the vanes extend with radial and axial components from the first member to the upstream end of the second member and the radially outer ends of the leading edges of the vanes form arches with the upstream end of the second member. The arrangement of the swirler enables the fuel injector to be built by direct laser deposition. | 08-28-2014 |
20140236548 | METHOD AND SYSTEM FOR DESIGNING A MATERIAL - A method of designing a material by optimising values for design variables includes the steps of: (i) providing one or more property models that produce a prediction for a value of a respective property of the material as a function of the design variables and produce a value for the uncertainty in the prediction, (ii) setting a specification target for a desired value for each property and a probability for that specification target to be met or exceeded, (iii) determining a probabilistic target for a value for each property, the probabilistic target being based on the specification target and the probability, and defining a merit index factor based on the degree to which a given prediction satisfies the probabilistic target, (iv) constructing an overall merit factor from the individual merit index factors of the properties, and (v) determining a set of optimal design variables that optimise the overall merit factor. | 08-21-2014 |
20140236450 | DETERMINING THE DETERIORATION OF A GAS TURBINE ENGINE IN USE - This invention relates to the operation of gas turbine engines, and in particular to determining deterioration of components during operation. In a specific embodiment, the invention is concerned with determining the actions to be taken when a foreign body impact has been detected, for example on a fan blade. | 08-21-2014 |
20140234151 | METHOD OF MANUFACTURING AN ARTICLE FROM POWDER MATERIAL AND AN APPARATUS FOR MANUFACTURING AN ARTICLE FROM POWDER MATERIAL - An apparatus for manufacturing an article from powder material includes a canister, a sorter, a plurality of hoppers and at least one valve. The canister has a predetermined internal shape to define the shape of the powder metal article. The sorter sorts the powder material by the size of the powder particles, the shape of the powder particles and/or the flow characteristics of the powder particles. The hoppers contain powder material with different sizes of powder particles, different shapes of powder particles and/or powder particles with different flow characteristics. The hoppers are arranged to supply the sorted powder material to the canister. The at least one valve controls the proportions of the different powder materials supplied from the one or more of the different hoppers into the canister to control the packing density of the powder material in the canister at all positions in the canister. | 08-21-2014 |
20140234112 | ROTOR BLADE - A blade at least part of which is arranged in use to rotate outside of a casing of a gas turbine engine. The blade has a main body, a tip fence and a blend region defining a curve between the main body and the fence. The blend region has a radius of curvature below five inches and the fence extends anhedrally from the blend region with respect to the main body. | 08-21-2014 |
20140234095 | AEROFOIL FOR AXIAL-FLOW MACHINE - An aerofoil, such as a vane, for an axial flow machine, the aerofoil having first and second ends and opposing pressure and suction surfaces extending between said first and second ends in a span-wise direction. A first portion of the span of the aerofoil towards the first end the aerofoil has a location of greatest camber which is closer to a trailing edge than a leading edge of the aerofoil. In a further portion of the aerofoil span the camber is either uniform between the leading and trailing edges or else a location of greatest camber is closer to the leading edge than the trailing edge. In the first portion of the span of the aerofoil the pressure and/or suction surface may turn to a greater extent towards the trailing edge than towards the leading edge of the aerofoil. | 08-21-2014 |
20140230440 | COMBUSTION CHAMBER - A combustion chamber comprises an outer wall and an inner wall. The outer wall has mounting apertures extending there-though and the inner wall has threaded studs extending there-from. The threaded studs extend through the mounting apertures in the outer wall. Cooperating nuts locate on the studs. Walls are positioned between the outer wall and the inner wall. Each wall is spaced from and extends around a respective fastener to form a chamber around the respective fastener. Apertures extend through the outer wall. Each aperture is spaced from a respective mounting aperture. Each aperture allows a flow of coolant into the associated chamber and around the associated fastener to cool the fastener. Each wall has an opening at a position diametrically opposite to associated aperture to allow the flow of coolant out of the chamber to a space between the outer wall and the inner wall. | 08-21-2014 |
20140220377 | METHOD OF FORMING A BONDED ASSEMBLY - A method of forming a bonded assembly ( | 08-07-2014 |
20140219707 | PANEL MOUNTING ARRANGEMENT - A panel mounting system comprises a panel, a foundation and a plurality of hangers connecting the panel to the foundation. The panel comprises a plurality of first attachment points, and the foundation comprises a plurality of second attachment points. | 08-07-2014 |
20140217838 | MAGNETIC GEAR ARRANGEMENT HAVING A VARIABLE GEAR RATIO - A magnetic gear arrangement is provided having a magnetically active gear member that generates a first magnetic field, which is modulated by interpoles. The modulated magnetic field generates magnetic poles on a magnetically passive gear member, and these poles form a second magnetic field. The material of the passive gear member is sufficiently magnetically hard that the first and second magnetic fields interact to couple the motion of the active and passive gear members according to a given gear ratio. | 08-07-2014 |
20140212317 | METHOD OF MANUFACTURING A WALL - A method of manufacturing an annular wall ( | 07-31-2014 |
20140212299 | PROPULSION ENGINE - A propulsion engine for an aircraft, the propulsion engine comprising: one or more fans ( | 07-31-2014 |
20140212287 | FLUIDFOIL - A fluidfoil is disclosed including a leading edge and a leading edge zone behind the leading edge. The leading edge zone extends spanwise for the full length of the fluidfoil. The leading edge zone includes one or more deflected regions which locally reduce the angle of attack of the fluidfoil. | 07-31-2014 |
20140210207 | SENSOR ARRANGEMENT FOR A TIDAL GENERATOR - This invention relates to a generator arrangement, including: a generator located within a flow passage wherein the flow passage has an inlet and an outlet, and the generator includes at least one contra-rotating blade arrangement which is configured to be rotated about a principle axis of the generator by a flow of liquid in the flow passage, and wherein the at least one blade has an adjustable pitch; an array of sensors located downstream of the blade arrangement for detecting the outlet flow conditions; a controller for determining the outlet flow conditions on the basis of conditions sensed by the sensor array; and, a pitch control system for adjusting the pitch of the at least one blade so as to affect the flow conditions at the outlet of the flow passage. | 07-31-2014 |
20140209572 | CONTACT DEVICE FOR CONTOURED SURFACES - There is provided a contact device ( | 07-31-2014 |
20140209408 | EXHAUST CONE - A gas turbine engine exhaust cone ( | 07-31-2014 |
20140208770 | COMPONENT HAVING INSERT FOR RECEIVING THREADED FASTENERS - A component formed of a plastic matrix composite material is provided. The component has a metal liner which is fixed in a correspondingly shaped recess formed in the composite material. The liner has a threaded bore into which is screwed an externally threaded, hollow cylindrical, metal insert. The insert has an internal thread for receiving threaded fasteners. The mouth of the bore has engagement formations which engage with the insert to prevent rotation of the insert in the bore, an adjacent part of the insert being plastically deformed to engage with the engagement formations after being screwed into the bore. | 07-31-2014 |
20140208768 | COOLANT SUPPLY SYSTEM - A cooling system for a gas turbine engine ( | 07-31-2014 |
20140208712 | COMPONENT HAVING A HEAT PROTECTION SYSTEM - A component having a heat protection system is provided. The heat protection system includes an intumescent coating which extends over a surface of the component. The heat protection system further includes a heat resistant wrapping which covers the coating on the component. The wrapping is expandable when the coating intumesces to maintain the wrapping's coverage of the coating. | 07-31-2014 |
20140193249 | ELECTRICAL CONDUCTOR PATHS - A component, for example an aerofoil vane or other gas path structure in a gas turbine machine such as a gas turbine engine, in which an insulated electrical conductor path is embedded structurally integrally, and in which electromagnetic shielding, for the embedded electrical conductor path is provided structurally integrally. | 07-10-2014 |
20140192049 | MEDIAL SURFACE GENERATION - A method of generating a medial mesh of an object. The method first includes obtaining a surface mesh of the object. Define a set of node normal vectors, each having its origin at a node and being directed towards the interior of the object. For each node: select a node normal from the set having their origins at that node; define a sphere wherein a surface of the sphere includes the node and the centre point is positioned at a scalar multiple of the node normal; increment the centre point along the scalar multiple; iterate until the surface of the sphere includes another node or element. The centre point is recorded as a medial point and the diameter as a thickness. The medial mesh is generated from the set of medial points and object thicknesses. | 07-10-2014 |
20140190166 | COMBUSTION CHAMBER - A combustion chamber comprises an outer wall and an inner wall spaced from the outer wall. The outer wall has at least one mounting aperture extending there-through and the inner wall has threaded studs extending there-from. The threaded studs extend through the mounting apertures in the outer wall. Cooperating nuts locate on the studs and washers are positioned between the outer wall and the cooperating nuts. Each washer has a rim and a bore. The washers have one or more passages extending there-through from the rim to the bore of the washer to provide a flow of coolant through the passages in the washers, the mounting apertures in the outer wall and around the threaded studs to cool the threaded studs to increase the working life of the inner wall. Other cooling arrangements for the threaded studs are disclosed. | 07-10-2014 |
20140178207 | TURBINE BLADE - A rotor stage of a turbine has a rotational axis, a shroud and radially inward thereof a turbine blade defined partly by a pressure side wall, a suction side wall and a tip portion. The tip portion has a pressure side tip rib and a tip cavity floor defining a tip cavity. The pressure side tip rib has a width W | 06-26-2014 |
20140169953 | DRUM SEAL - A gas turbine engine comprising at least one drum pack having two or more annular discs | 06-19-2014 |
20140165688 | FORGING APPARATUS - A forging apparatus and method is disclosed in which a punch | 06-19-2014 |
20140165531 | HEATED RIGID ELECTRICAL SYSTEM - A rigid electrical raft has electrical conductors embedded in a rigid material. The electrical conductors transmit electrical signals through the rigid electrical raft, which may form part of an electrical system of a gas turbine engine. The rigid electrical raft also has electrical heating elements embedded therein. The electrical heating elements provide heat which may be used, for example, to prevent condensation and/or ice build-up and/or to raise the temperature of electrical components to be within a desired range. | 06-19-2014 |
20140161520 | JOINT STRUCTURE AND METHOD - The invention relates to a joint including a substrate, optionally a metal substrate, and a body of material joined to the substrate, the body of material typically having a composite portion. An outer surface of the substrate is provided with a fastening projection for fastening the substrate to body of material, wherein the fastening projection has a stem and a plurality of branches having dendritic geometry projecting into the material of the body. | 06-12-2014 |
20140161510 | JOINT ASSEMBLY AND METHOD OF USING THE SAME - A joint assembly includes an end portion of a first component that is accommodated within an end portion of a second component, with each respective first and second end portion having a corresponding first and second location feature, and an elongate resilient helical connection member. When the joint is assembled, the first and second location features together define an annular cavity into which is accommodated the connection member to interlock the first and second components to one another. | 06-12-2014 |
20140159317 | AIR-RIDING SEAL - There is disclosed a rotary air-riding seal between a first structure and an adjacent second structure, including: first and second seal members defining respective seal surfaces facing to one another. The first seal member is provided on the first structure and the second seal member is mounted to the second structure towards the first seal member. At least one of said seal members is configured to generate a riding film of air between said seal surfaces. One of said seal members is supported for axial oscillation relative to the other seal member by a secondary support arrangement configured to bias said seal member towards the other seal member. The said secondary support arrangement accommodates relatively high frequency axial movements between the seal members. | 06-12-2014 |
20140158232 | A HYDRAULIC SEAL ARRANGEMENT - A hydraulic seal arrangement for a rotating machine, the hydraulic seal arrangement comprising: a hydraulic seal; and an annular reservoir ( | 06-12-2014 |
20140157781 | FUEL INJECTOR AND A GAS TURBINE ENGINE COMBUSTION CHAMBER - A gas turbine engine lean burn fuel injector includes a fuel injector head which has a first air swirler, a second air swirler arranged around the first air swirler, a pilot fuel injector arranged radially between the first air swirler and the second air swirler. A third air swirler arranged around the second air swirler, a fourth air swirler arranged around the third air swirler and a main fuel injector arranged radially between the third air swirler and the fourth air swirler. A shroud is arranged around the fourth air swirler. A downstream end of the shroud is generally circular in cross-section in a plane perpendicular to the axis (Y) of the fuel injector head and an upstream end of the shroud is generally elliptical in cross-section in a plane perpendicular to the axis (Y) of the fuel injector head. | 06-12-2014 |
20140154470 | MACHINING METHOD - A method of machining an article. The method includes: scanning the article to determine an initial surface profile; determining a cross sectional area removed from the article by a material removal tool in a material removal pass under controlled conditions; using the cross sectional area to determine one or more material removal tool contact angles for at least one material removal pass by the material removal tool under the controlled conditions required to conform the initial surface profile to a nominal surface profile; and machining the article to conform the initial surface profile to the nominal surface profile. | 06-05-2014 |
20140150919 | DUCT ARRANGEMENT - A duct arrangement | 06-05-2014 |
20140147245 | MONITORING AND CONTROL SYSTEM - A method of controlling the angular orientation of at least one variable fluidfoil. The method includes the steps of receiving detected fluidfoil angular orientation data for the at least one fluidfoil; receiving a fluidfoil angular orientation demand; generating a modified angular orientation demand by modifying the fluidfoil angular orientation demand before it is used to control adjustment of the at least one fluidfoil, the modification being performed using the detected fluidfoil angular orientation data; and outputting the modified demand and controlling the at least one fluidfoil angular orientation in accordance with the modified demand. | 05-29-2014 |
20140145008 | GAS TURBINE ENGINE EXHAUST NOZZLE - An exhaust nozzle | 05-29-2014 |
20140144145 | GAS TURBINE COMBUSTION CHAMBER - The present invention relates to a gas-turbine combustion chamber with an outer combustion chamber wall concentric to a gas-turbine center axis and with an inner combustion chamber wall, with several burners arranged spread over the circumference of the combustion chamber, and with air inlet recesses which in at least one radial plane are provided spread over the circumference on an outer combustion chamber wall and on an inner combustion chamber wall, where the burner is designed to form a flow provided with a swirl and where air inlet recesses assigned to a burner are dimensioned in differing size in order to generate airflows of differing size, characterized in that at least one of the respective air inlet recesses is designed for supplying air in the flow direction of the swirl of the combustion chamber flow and is provided with flow guidance walls. | 05-29-2014 |
20140141174 | METHOD OF MANUFACTURING A THERMAL BARRIER COATED ARTICLE - A method of manufacturing a thermal barrier coated article including: forming an article having a first and second surface, the article having projections extending from the first surface away from the first and second surface, each projection having a first end adjacent the first surface and a second end remote from the first surface, each projection having a blind passage extending therethrough from the second surface through the article towards the second end of the projection, the blind passage in the projection being closed at the second end of the projection, depositing a thermal barrier coating on the first surface around each of the projections and on the second ends, removing the thermal barrier coating from the second ends, and removing the second end of each projection to form a passage through the projection extending from the second surface through the article to the second end of the projection. | 05-22-2014 |
20140140860 | AEROFOIL COOLING - An aerofoil component of a gas turbine engine is provided. The component has a longitudinally extending aerofoil portion which spans, in use, a working gas annulus of the engine. The aerofoil portion contains an internal chamber for a flow of coolant. The chamber includes a helical passage which spirals in a plurality of turns around an axis that extends in the length direction of the aerofoil portion. | 05-22-2014 |
20140140809 | HEAT PROTECTION ASSEMBLY - A flexible component includes a core element provided with a heat protection assembly. The heat protection assembly includes an intumescent coil wrap that extends around the core element. The coil wrap is arranged such that it is interlaced with a coil-shaped gap. This arrangement allows the component to retain flexibility, whilst still ensuring an adequate level of heat protection to the core element. | 05-22-2014 |
20140133963 | APPARATUS AND METHOD FOR MEASURING GAS FLOW THROUGH A ROTARY SEAL - A method of measuring a flow rate of a first fluid through a rotary seal of a gas turbine engine comprising controlling a probe flow of a second fluid at an intra-seal cavity and measuring a pressure change in the first fluid caused by the probe flow. | 05-15-2014 |
20140131426 | FRICTION WELDING - A welding tool for friction welding a workpiece, the tool including: a probe having a core including a ceramic material, the probe having a surface coating including a metallic material covering at least part of a contact zone of the probe. | 05-15-2014 |
20140130583 | INSPECTION ARRANGEMENT - An inspection arrangement including an inspection element and a positioning tool for positioning the inspection element, the inspection element being attachable to the positioning tool by an attachment arrangement, and having a fixing element to present the inspection element in use, the fixing element including a plurality of radially extending resilient elements. | 05-15-2014 |
20140127457 | CERAMIC MATRIX COMPOSITE COMPONENT FORMING METHOD - A method of forming a ceramic matrix composite gas turbine engine includes: providing green sub-elements, each sub-element containing stacked plys of continuous fibre reinforcement embedded in a green ceramic matrix; assembling the sub-elements so that each sub-element contacts at least one other; and sintering the assembled sub-elements to fuse the ceramic matrix within each sub-element and between contacting sub-elements, forming a composite unitary body. An alternative method includes the steps of: providing a sintered sub-elements, each sub-element containing stacked plys of continuous fibre reinforcement embedded in a sintered ceramic matrix; assembling the sintered sub-elements so that each sub-element contacts at least one other, ceramic cement being provided at the contact interfaces between the sub-elements; and the assembled sub-elements to fuse the ceramic cement, forming a ceramic matrix composite unitary body. | 05-08-2014 |
20140125121 | METHOD OF CONTROLLING AN AIRCRAFT ELECTRICAL POWER GENERATION SYSTEM - A method of operating an electrical power generation system on an aircraft. The method includes assessing a required electrical power of the aircraft, assessing whether a first and a second electrical power source are able to provide the required electrical power in combination, assessing a predetermined condition, determining an operating mode of the first and second electrical power sources to match the predetermined condition, and operating the first and second electrical power sources according to the determined operating mode. | 05-08-2014 |
20140123676 | GAS TURBINE ENGINE END-WALL COMPONENT - An end-wall component of the mainstream gas annulus of a gas turbine engine has a cooling arrangement including one or more circumferentially extending rows of ballistic cooling holes through which, in use, dilution cooling air is jetted into the mainstream gas to reduce the mainstream gas temperature adjacent the end-wall. A portion of the cooling holes are first cooling holes angled such that the direction of the dilution cooling air jetted therethrough has, on entry into the mainstream gas annulus, a component in one tangential direction. A portion of the cooling holes are second cooling holes angled such that the direction of the dilution cooling air jetted therethrough has, on entry into the mainstream gas annulus, a component in the opposite tangential direction. The first and second cooling holes are arranged such that the cooling air from jets having entry components in opposing tangential directions collide and coalesce. | 05-08-2014 |
20140123625 | ENGINE CONTROL PARAMETER TRIMMING - A method of re-trimming an engine control parameter. Measure an engine parameter over time. Calculate change in the measured parameter per engine cycle. Determine change of thrust due to the calculated change in the measured parameter from a reference database. Define a new trim value for the engine control parameter that is a function of the change of thrust. Apply the new trim value to the engine control parameter. | 05-08-2014 |
20140119942 | TURBINE ROTOR BLADE OF A GAS TURBINE - The present invention relates to a turbine rotor blade of a gas turbine with a blade tip, said blade tip having at least on its suction side, extending from a stagnation point on the blade leading edge to an intersection point of the suction-side profile line of the blade with a trailing-edge circle, an overhang which is substantially zero at the stagnation point and at the intersection point and which has a maximum value at around 40% of the running length of the suction-side overhang. | 05-01-2014 |
20140112765 | FLUIDIC ACTUATOR - A fluidic actuator comprising: a fluid nozzle for delivering fluid and a tube having an open end and a closed end, the open end spaced from the fluid nozzle. Also a pair of electrodes mounted in the tube and spaced apart to create a spark gap therebetween. A voltage source is arranged to supply a voltage across the pair of electrodes wherein the voltage causes plasma formation in the spark gap thereby shortening the effective length of the tube. | 04-24-2014 |
20140112757 | CLEARANCE CONTROL - A clearance control device including a segment having a passage to deliver fluid towards a component rotating past the segment. Also a fluid flow device having a first fluid path coupled to the passage and a second fluid path that is decoupled from the passage. A first plasma generator is located in the fluid flow device that directs fluid towards the first fluid path; a second plasma generator is located in the fluid flow device that directs fluid towards the second fluid path; and a control arrangement is configured to alternately energise the first and second plasma generators at an energising frequency to deliver fluid to the passage at a frequency coincident with the passing frequency of the component. | 04-24-2014 |
20140106922 | OIL SCAVENGE ARRANGEMENT - An epicyclic gearbox including: a sun gear, a ring gear, an array of planet gears that each mesh with the sun gear and the ring gear and rotate relative thereto, and a planet carrier that couples the planet gears in relative position to each other. The planet carrier includes interplanetary portions that are located between adjacent pairs of planet gears and have a first and a second circumferential surface facing each adjacent planet gear; and direction features on at least one of the circumferential surfaces that, in use, direct fluid ejected with a radial component from the planet gears and direct it with an axial component. | 04-17-2014 |
20140106665 | WIRELESS SIGNAL PROPAGATION APPARATUS - There is provided apparatus for propagation of a wireless signal through a barrier comprising a first antenna for location on a first side of the barrier, a second antenna for location on a second side of the barrier and a waveguide. The waveguide comprises a conducting member passing through the barrier between the first and second sides. The conducting member is held within an insulator sleeve such that it is spaced from a surrounding metal wall of the waveguide. A wireless signal received by the waveguide on the first side of the barrier is transmitted through the barrier by Transverse Electro-Magnetic (TEM) mode propagation along the waveguide is re-radiated on the second side. | 04-17-2014 |
20140099198 | DUCT ASSEMBLY - A duct for a gas turbine engine system is used to convey exhaust gas and bypass air away from the engine system, towards an exhaust nozzle. The duct includes an inlet face having at least two inlet portions and defines the outer extremity of a path for the gas and/or air through the duct. The duct includes a plurality of flat panel members which together define the outer extremity of the path. | 04-10-2014 |
20140098836 | TEMPERATURE INDICATING PAINT - A temperature indicating paint is provided. The paint is spreadable onto a surface of an article. The paint includes particles of an alloy of two or more metals. The particles vary in relative composition of the metals such that particles having different compositions have different solidus and liquidus melting temperatures. | 04-10-2014 |
20140096518 | EXHAUST ARRANGEMENT - An exhaust arrangement for an internal combustion engine. The exhaust arrangement includes a diffuser duct including a wall surface which diverges between an inlet and a first outlet. The arrangement further includes an auxiliary duct extending from a second outlet of the diffuser duct. The second diffuser duct outlet being located on the wall surface between the diffuser duct inlet and the first outlet. The auxiliary duct includes a heat recovery device configured to convert heat energy from exhaust gases passing through the auxiliary duct in use to mechanical or electrical energy. | 04-10-2014 |
20140090923 | ACOUSTIC PANEL - An acoustic panel includes a first cellular layer with cells having a first axis, a second cellular layer with cells having a second axis, and a perforated septum layer separating the first layer and the second layer. The cells of both layers have an end distal to the septum layer and an end which meets the septum layer, and the maximum diameter of the cells of the first layer is less than the maximum diameter of the cells of the second layer. | 04-03-2014 |
20140090395 | GAS TURBINE ENGINE - A cooling system for a gas turbine engine ( | 04-03-2014 |
20140087632 | MACHINING OF AN ARTICLE - A method of forming a profile of a leading edge on an aerofoil having a leading edge extending along an axis and providing a fluid jet that has a Gaussian energy distribution profile. The jet is traversed along a path that substantially follows the axis, the maximum energy of the fluid jet being directed to a location offset from the axis. | 03-27-2014 |
20140086751 | ANNULUS FILLER FOR AXIAL FLOW MACHINE - A fluid-washed assembly for an axial flow machine, such as a fan blade assembly for a gas turbine engine. The assembly has an array of members circumferentially spaced about the machine axis, each member extending from a radially inner end to a radially outer end with respect to the axis of rotation of the machine. Each member has opposing outer surfaces extending between a leading edge and a trailing edge thereof with respect to the direction of oncoming fluid flow in use. A plurality of annulus fillers are provided between each member, wherein each annulus filler is affixed against an outer surface of an associated member at a location between the inner and outer ends in a manner which supports the annulus filler in use. In preferred embodiments, the annulus fillers comprise a composite material which is bonded to the associated member using an adhesive. | 03-27-2014 |
20140086724 | GAS TURBINE ENGINE COMPONENT - An internally cooled gas turbine engine component has a line of cooling air discharge holes, an internal cooling channel, an internal feed cavity for feeding cooling air from the channel to the discharge holes, and flow disrupting pedestals arranged in rows. A method of configuring the component includes: | 03-27-2014 |
20140077772 | TURBINE ARRAY AND A METHOD OF CONTROLLING A TURBINE ARRAY DURING A LOSS-OF-GRID EVENT - A turbine array including: a plurality of turbines; an electrical machine connected to each of the turbines and to an electrical grid; wherein at least one of the electrical machines is a motor-generator which can operate in a motor mode or a generator mode, and wherein the other electrical machines are generators; and a controller for detecting a loss-of-grid event; wherein the controller sets the motor-generator to the motor mode when a loss-of-grid event is detected, the motor-generator being driven by the generators and thereby providing a load to the generators. | 03-20-2014 |
20140076864 | BOROSCOPE AND A METHOD OF LASER PROCESSING A COMPONENT WITHIN AN ASSEMBLED APPARATUS USING A BOROSCOPE - A boroscope includes a working head having first and second ends. A first optical fibre extends through the boroscope to a position between the first and second ends. A second optical fibre extends through the boroscope to the second end of the working head. A laser optical fibre extends through the boroscope. At least one lens is arranged between the first end and the second end of the working head and a mirror is gimballed to the second end of the working head. The laser optical fibre directs laser light transmitted through the laser optical fibre onto the lens and then onto the mirror. A first LED is arranged at a position between the first end and the second end of the working head and a second LED is arranged at the second end of the working head and an actuator devices adjust the position of the mirror. | 03-20-2014 |
20140076060 | METHOD AND SYSTEM FOR PREDICTING THE SERVICEABLE LIFE OF A COMPONENT - The remaining serviceable life of a component of a gas turbine engine can be predicted by monitoring one or more topographical features of the component which are arranged so as to cause a non-hazardous crack to be initiated at one or more of the topographical features during the course of operation of the gas turbine engine. | 03-20-2014 |
20140072426 | TURBOMACHINE CASING ASSEMBLY - 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. | 03-13-2014 |
20140072407 | FILLED STATIC STRUCTURE FOR AXIAL-FLOW MACHINE - A stator assembly for a rotary machine having a rotor arranged to rotate about an axis in use. The stator assembly has a circumferential support member or casing arranged about said axis and a plurality of elements extending in a substantially radial direction from the support. The elements have a platform at an end thereof for engagement within the support, wherein the elements each comprise a hollow internal cavity having an opening through the platform at the end of the element, wherein said internal cavity is filled with a vibration damping material. The elements may be filled vanes in a gas turbine engine compressor. The platforms may also be filled with the vibration damping material. | 03-13-2014 |
20140070496 | LEAF SEAL - A leaf seal for effecting a seal between two, coaxial, relatively rotating components. The leaf seal has an annular pack of stacked leaves. The pack is mountable to a first one of the components with interleaf gaps formed between working portions of neighbouring leaves. The leaves extend towards the other component such that end edges of leaf working portions are presented for wiping contact with the other component. At least adjacent its end leaf edge, each leaf has a rear section at or adjacent the low pressure side of the pack and a front section which extends from the rear section to the high pressure side of the pack. The rear sections of the leaves are thicker than their respective front sections to reduce the interleaf gaps at the rear sections such that most of the pressure drop across the pack is over the rear sections. | 03-13-2014 |
20140069460 | BOROSCOPE AND A METHOD OF PROCESSING A COMPONENT WITHIN AN ASSEMBLED APPARATUS USING A BOROSCOPE - A boroscope ( | 03-13-2014 |
20140064967 | AEROFOIL COOLING ARRANGEMENT - An aerofoil typically for a blade or vane for a gas turbine engine comprises a pressure wall, a suction wall and a web that extends therebetween. One of the walls comprises an inner leaf and an outer leaf which defines a cavity, the other wall defines a first outlet, the aerofoil defines at least one first passage extending from the cavity through the web and to the outlet. Coolant in the cavity on one side wall of the aerofoil is thereby routed across the web to be used to cool the other wall by convention and formation of a coolant film. | 03-06-2014 |
20140064956 | GUIDE VANE ASSEMBLY - A guide vane assembly for a stator vane stage comprises at least two aerofoil members joined together using a vane assembly attachment web. The vane assembly attachment web may be provided at the inner and/or outer radius of the aerofoil members. The vane assembly attachment web allows the guide vane assembly to be attached to an inner and/or outer attachment ring, thereby forming a stator vane stage. Such an arrangement may allow composite fibre reinforced guide vane assemblies to be readily assembled together to form stator vane stages. Stator vane stages that comprise such composite fibre reinforced guide vane assemblies may be lighter than conventional metallic stator vane stages. | 03-06-2014 |
20140064949 | TURBOMACHINE CASING ASSEMBLY - 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. 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. Release of one of the rotating aerofoil elements results in the element, or part thereof, impacting the first casing element which results in the cantilever bending into the void provided between the first and second casing elements. | 03-06-2014 |
20140060079 | AEROENGINE ARRANGEMENT - A core engine for a gas turbine engine, the core engine having a rotational axis, a casing and further comprises a gearbox assembly, a radial drive arrangement, pipes and connections and a connection structure; the radial drive arrangement drivingly connects the core engine to the gearbox assembly; the pipes and connections extend from the gearbox assembly to the core engine and the gearbox assembly is radially spaced from the casing by connection structure. A method of assembling the gas turbine engine includes the steps of axially translating the core engine and the fan casing so that the gearbox is adjacent the fan casing and attaching the gearbox assembly to the fan casing. | 03-06-2014 |
20140033733 | FLOW DISCHARGE DEVICE - A bleed flow discharge device ( | 02-06-2014 |
20140027538 | VARIABLE GEOMETRY STRUCTURE - A variable geometry ( | 01-30-2014 |
20140026583 | FLUID MANAGEMENT APPARATUS AND METHOD - A fluid management apparatus and method, the apparatus including: a fluid conduit for the passage of a dispersion containing particulate matter; a laser arranged to provide laser light inside the fluid conduit; wherein, in use, the laser light heats the particulate matter sufficiently to generate incandescence; one or more sensors for detecting the incandescence of the particulate matter so as to determine a characteristic of the dispersion; and an electromagnetic wave generator operable to provide electromagnetic waves inside the fluid conduit at a position downstream of the laser light so as to vaporise at least a portion of the dispersion. | 01-30-2014 |
20140010635 | FLUID INTAKE AND SYSTEM FOR ROTARY MACHINES - This invention relates to a fluid supply system for a rotary machine, the system comprising: a rotor assembly comprising an array of blades arranged to be driven about a primary axis in use, the rotor assembly comprising a casing structure, wherein the casing structure is rotatable in unison with the blades about the primary axis; a directional fluid intake, said intake being rotatably mounted at an outer surface of the casing structure about a second axis which is angularly offset from the primary axis. | 01-09-2014 |
20130343958 | FUEL SYSTEM - A fuel system ( | 12-26-2013 |
20130343892 | PROPFAN ENGINE - The present disclosure relates to a propfan engine comprising: one or more rotor stages comprising a plurality of rotors; and an outer wall comprising an outer profile, at least a portion of the outer profile defining a substantially circular cross-section, wherein the diameter of the substantially circular cross-section increases in the direction of flow over the outer wall and downstream of a leading edge of the rotors, and the diameter increases at substantially all points defining the circumference of the substantially circular cross-section. | 12-26-2013 |
20130343872 | COOLED COMPONENT FOR THE TURBINE OF A GAS TURBINE ENGINE - A component for the turbine of a gas turbine engine is provided. The component two facing walls interconnected by one or more generally elongate divider members to partially define side-by-side, generally elongate, cooling fluid passage portions which form a multi-pass cooling passage within the component. The passage portions are connected in series fluid flow relationship by respective bends formed by joined ends of neighbouring of the passage portions. The component further includes one or more core tie linking passages formed in the divider members. One or more differential pressure reducing arrangements are formed in the multi-pass cooling passage adjacent respective of the core tie linking passages. | 12-26-2013 |
20130340834 | FUEL DELIVERY SYSTEM - A method includes i) identifying a period of operation corresponding to a fuel supply requirement; ii) determining at least one ambient air condition in which the machine will operate during the period; iii) determining a duration of time in which, whilst in the ambient air condition, it is required to achieve a predetermined vapour trail characteristic; iv) determining a resultant fuel composition for use by the machine in the ambient air condition to achieve the characteristic, where the resultant fuel composition includes at least one of the first and second fuel compositions; v) determining the ratio of at least the first and second fuel compositions required for sufficient resultant fuel composition for the duration of time determined in step iii); and vi) producing a first signal indicative of the ratio of at least the first and second fuel compositions required for the duration of time determined in step iii). | 12-26-2013 |
20130340521 | ROTOR BALANCING METHOD - A method of balancing a physical rotor includes: determining a first balance state of the physical rotor at one or more rotational frequencies; identifying one or more balance zones on a surface of the rotor; providing a computerised simulation of the rotor having the first balance state; providing a first test mass in a first test location within one of the balance zones on the rotor simulation; determining a second balance state of the rotor simulation; providing at least one subsequent test mass in at least one subsequent test location within a balance zone on the rotor simulation and determining at least one subsequent balance state of the rotor simulation; selecting a mass and location from one of the first and subsequent test masses and test locations; and performing a material deposition process to add the selected mass of material to the selected location on the physical rotor. | 12-26-2013 |
20130340324 | FUEL SYSTEM - A fuel system ( | 12-26-2013 |
20130336781 | AIRCRAFT - An aircraft includes a propulsive fan arrangement having an intake and an exhaust. The fan arrangement is mounted adjacent a gas washed surface of the aircraft in the form of a suction surface of a wing. The intake is separated from the suction surface to define a channel therebetween. The aircraft further includes a Venturi device positioned downstream of the fan exhaust to draw boundary layer air through the channel. | 12-19-2013 |
20130336761 | TURBOMACHINE CASING ASSEMBLY - 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. | 12-19-2013 |
20130331222 | OIL SCAVENGE ARRANGEMENT - An epicyclic gearbox oil scavenge arrangement. The epicyclic gearbox is of the planetary or differential type and comprises an input sun gear ( | 12-12-2013 |
20130329846 | ROTARY ACTUATOR - A rotary actuator has a driven element including a plurality of recesses that are spaced in a circumferential arrangement around an axis of rotation of the driven element by a spacing angle, and first, second and third latch elements that are each movable between a retracted position, and an extended position in which it is engageable with a corresponding one of the recesses. Sequential movement of the first, second and third latch elements between retracted and extended positions causes rotation of the driven element. | 12-12-2013 |
20130319092 | SHAFT BREAK DETECTION - A shaft break detection system and a method of detecting shaft break for a gas turbine engine. A first indication is calculated from measured rotational speed of a shaft. A second indication is calculated from the rotational speed. A shaft break signal is generated if both indications are true. | 12-05-2013 |
20130318773 | APPARATUS FOR IMMOBILISING A COMPONENT DURING A MACHINING OPERATION - An apparatus for immobilising a component during a machining operation is provided. The component has a securing region and an elongate body to be machined extending therefrom. The apparatus has a clamp which is configured to immobilise the component at the securing region. The clamp, in use, exerts clamping forces on the securing region. The apparatus further has a support fixture which is movable relative to the clamp to confine the elongate body at a support region thereof distal from the securing region. The support fixture is configured such that, without exertion of clamping forces on the support region by the support fixture, the confined support region is unable to move during the machining operation. | 12-05-2013 |
20130315701 | AIRCRAFT PROPULSION SYSTEM AND A METHOD OF CONTROLLING THE SAME - An aircraft propulsion system has a propulsive rotor assembly rotatable about an axis of rotation and comprising a plurality of blades and a rotationally fixed vane assembly located adjacent to the propulsive rotor assembly and arranged circumferentially around the axis of rotation. As airflow enters the propulsive rotor assembly, a portion of the airflow passes over the vane assembly which is configured to direct the airflow away from the rotor blades so as to reduce the relative velocity of the redirected airflow over the rotor blades. This results in a reduced tendency of the airflow through the propulsive rotor assembly to become choked. | 11-28-2013 |
20130313782 | SEAL AND METHOD OF FORMING A SEAL - A method of forming a seal for effecting a seal between two, coaxial, relatively rotating components is provided. The seal has an annular pack of elongate flexible members. The pack is mountable to a first one of the components at the root portions of the flexible members and extending towards the other component. End portions of the flexible members are presented for wiping contact with the other component. The method includes the steps of: (i) forming a plurality of pack segments, wherein each segment contains a respective subset of the flexible members of the annular pack, and wherein the end portions of the flexible members of each subset, when viewed in the axial direction of the seal, lie on a straight line; and (ii) assembling the pack segments in a substantially circular pack holder such that each pack segment forms a respective angular sector of the annular pack. | 11-28-2013 |
20130312423 | METHOD OF DETECTING SHAFT BREAK - A method of detecting shaft break in a gas turbine engine having a shaft system. The shaft system including a shaft that couples a compressor and a turbine. First construct a frequency model of the shaft system. Then determine a notch frequency and a first torsional frequency for the shaft system from the model. Then in real time measure a rotational speed of the shaft; detect the presence or absence of a feature at at least one of the notch frequency and the first torsional frequency in the measured speed; and generate a shaft break signal in response to the absence of at least one of the features. | 11-28-2013 |
20130306265 | HEAT EXCHANGER - The invention relates to a heat exchanger | 11-21-2013 |
20130306024 | DUCT - The invention relates to a duct for a vehicle, comprising: an elongate passageway defined by at least one wall, the passageway having first and second ends relative to the longitudinal axis of the passageway; a non-annular inlet at the first end of the passageway for receiving a first fluid flow from the boundary layer of the vehicle when in use; and, an annular outlet at the second end of the passageway having an radially inner circumferential wall and a radially outer circumferential wall, the annular outlet being in fluid communication with a propulsive unit when in use, wherein the radially inner and outer circumferential walls extend continuously to the inlet. | 11-21-2013 |
20130302154 | CASING - A containment case for a gas turbine including: a cylindrical outer casing extending about an axis and having a radially outer and a radially inner surface; a coaxially arranged cylindrical inner skin formed of a harder material than the outer casing joined to the inner surface of the cylindrical outer casing; and an array of ribs extending radially from the inner skin towards the axis. The case for can have the coaxially arranged cylindrical inner skin formed of a harder material than the outer casing joined to the inner surface of the cylindrical outer casing by a galvanic isolation layer. | 11-14-2013 |
20130298693 | METHOD OF FATIGUE TESTING A COMPONENT - A method of fatigue testing a component comprising the steps of machining a channel of predetermined depth and predetermined width in a surface of a component, applying a salt solution into the channel in the surface of the component and heating the component to a suitable temperature to evaporate the solvent from the salt solution to deposit the salt in the channel in the surface of the component, placing the component in an atmosphere containing air and sulphur dioxide at a predetermined temperature for a predetermined period of time to precondition the grain boundaries, and fatigue testing the component. The method is useful for determining the fatigue life of gas turbine engine discs or gas turbine engine rotor blades particularly the firtree shaped disc posts or the firtree shaped rotor blade roots. | 11-14-2013 |
20130292941 | ELECTRICAL MACHINE - An electromagnetic machine, comprising: a first stator winding having a first number of pole pairs; a second stator winding having a second number of pole pairs which is different to the first number of pole pairs; and, a modulator having a plurality of pole pieces arranged relative to the first and second stator windings so as to modulate the electromagnetic fields produced by the first and second stator windings, thereby matching harmonic spectra of the first and second stator windings. | 11-07-2013 |
20130280054 | TURBINE ENGINE STATOR AND METHOD OF ASSEMBLY OF THE SAME - A turbine engine stator stage includes a plurality of vanes with each of the plurality of vanes having a camber angle. The plurality of vanes is arranged in a plurality of groups with each group including a pre-determined sequence of vanes. The ordering of vanes within each group is determined by the camber of the individual vanes. This results in an arrangement of vanes within the stator stage which can modify the flow characteristics of the air entering the stator stage to reduce the circumferential pressure variation in the flow region immediately downstream of the stator stage. | 10-24-2013 |
20130272852 | VARIABLE STATOR VANE ARRANGEMENT - A variable guide vane assembly comprising a variable guide vane having an aerofoil and a spindle at one end of the aerofoil; wherein the vane further comprises a platform positioned between the aerofoil and the spindle, the platform having a surface facing in the direction of the spindle and at least one side face; the assembly also having a washer with an aperture through which the spindle extends, the washer having a portion which overhangs the at least one side face. | 10-17-2013 |
20130266447 | ANNULUS FILLER - 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. | 10-10-2013 |
20130266419 | ACTIVE FLOW CONTROL INTAKE FOR A GAS TURBINE ENGINE - Intakes of gas turbine engines are subject to cross winds and high incidence cross flows which can affect the stability of air to the propulsive fan. An active flow control arrangement for an intake comprises a compressed gas supply pipe, a valve arrangement, a controller, and a compressed gas distribution pipe. The supply pipe is fluidly connects between a compressed gas source and the valve arrangement. The distribution pipe fluidly connects between the valve arrangement and intake surface for supply of compressed gas thereto. The active flow control arrangement is operable to supply compressed gas to the intake surface to prevent separation of a main air flow passing through the intake from the inlet surface thereby maintaining stability of the intake air flow to the fan. | 10-10-2013 |
20130264757 | VIBRATION DAMPING - A vibration damping insert configured to seat within a cell of a cellular structure and to span the cell cavity. The insert comprises a first portion formed of a first material and a second portion formed of a second material having lower stiffness than the first material. The first portion is arranged to constrain deformation of the second portion to be in a predetermined direction. The invention also comprises a vibration damping body comprising a cellular structure formed of a plurality of tessellating cells and a vibration damping insert as described. The vibration damping insert is mounted in at least one of the cells in the cellular structure. The invention also comprises a method of manufacturing a vibration damping body. | 10-10-2013 |
20130264110 | ELECTRICAL GROUNDING PLANE - An electrical assembly including electrical raft having electrical conductors embedded in a rigid material is provided. The electrical assembly has an electrically conductive screen layer. The electrically conductive screen layer provides electromagnetic protection to the electrical conductors. The electrically conductive screen layer is electrically connected to a mounting fixture, which in turn may be electrically connected to an apparatus on which the electrical assembly may be mounted. The electrical raft is used to transport electrical signals (which may be, for example power and/or control signals), for example around a gas turbine engine. | 10-10-2013 |
20130263601 | INTAKE LINER FOR A GAS TURBINE ENGINE - A gas turbine engine having a rotational axis, an intake and a compressed gas source; the intake includes a lining having a facing which defines an inlet surface and an array of holes; the array of holes includes at least a first set of holes and a second set of holes, the holes of the first set of holes are angled a relative to a radial line and the holes of the second set of holes are angled β relative to the radial line; the angles α and β are different. An active flow control arrangement including a compressed gas supply pipe, a valve arrangement, a controller, a compressed gas distribution pipe may be provided. Compressed gas may be provided to prevent the formation of separation of a main gas flow through the intake and prevent or remove ice accretion. | 10-10-2013 |
20130255278 | EFFUSION COOLED SHROUD SEGMENT WITH AN ABRADABLE SYSTEM - A turbine casing assembly, comprising an annular seal segment assembly for surrounding the turbine adjacent to the turbine blades. An abradable coating is provided on the inboard surface of the seal segments of the assembly and one or more coolant ducts extend from the outboard surface of the seal segment assembly through respective seal segments and the abradable coating, for carrying a coolant towards the blade tips. One or more annular grooves are formed in the inboard surface of the abradable coating, the or each coolant duct opening into one of the one or more annular grooves. | 10-03-2013 |
20130251941 | THERMAL BARRIER COATED ARTICLE AND A METHOD OF MANUFACTURING A THERMAL BARRIER COATED ARTICLE - A method of manufacturing a thermal barrier coated article including the steps of: a) forming an article having a first surface and a second surface, the article having a plurality of projections extending from the first surface in a direction away from the first surface and away from the second surface, each projection having a first end adjacent the first surface and a second end remote from the first surface, b) depositing a thermal barrier coating on the first surface of the article around each of the projections and on the second ends of the projections, c) removing the thermal barrier coating from the second ends of the projections, and d) forming at least one passage through each projection extending from the second surface of the article through the article and through the respective projection to the second end of the respective projection. | 09-26-2013 |
20130248495 | ELECTRICAL DISCHARGE MACHINING - A method for electrical discharge machining a workpiece includes the steps of: presenting an elongate electrode to the workpiece with a spark gap therebetween; flowing a dielectric fluid in the gap; eroding the workpiece by electrical discharge between the tip of the electrode and the workpiece; displacing the electrode in a direction aligned with the long axis of the electrode to maintain the gap as the electrode wears and the workpiece is eroded; and simultaneously with the displacement, producing vibratory movement of the electrode, the vibratory movement being aligned with the long axis of the electrode. | 09-26-2013 |
20130247540 | INSPECTION DEVICE FOR AN INTERNAL COMBUSTION ENGINE - This invention relates to an internal combustion engine having a cavity for inspection, comprising: an inspection device mounted within a housing, the housing at least partially located within the cavity to be inspected and having a shutter which is actuable between a closed configuration and an open configuration; and an actuation mechanism for moving the shutter between the closed configuration and the open configuration. | 09-26-2013 |
20130236320 | BLADE - A fan blade for a gas turbine engine has an aerofoil part and a root part. The root part includes a root former; the root former includes a zone of weakness, which reduces the ability of the root part to withstand an impact force. Thus, in an impact situation in which the fan blade has separated from the fan rotor and the fan blade has itself separated into fragments, the root part will fracture or buckle more easily than would be the case with conventional arrangements. This will lower the impact force of the root part upon the fan casing, thus permitting the fan casing to be designed to withstand lower impact forces. The fan casing can therefore be made lighter, and cheaper, than in conventional arrangements. | 09-12-2013 |
20130226518 | BLADE TIP TIMING UNCERTAINTY - A method of determining blade tip timing measurement uncertainty comprising measuring time of arrival of each of a set of blades at each of a reference set of stationary probes. A reference blade tip parameter is derived from the measurements and the position of each of the probes. A reference condition number is calculated from the position of each of the probes and each targeted engine order, and then a mean calculated. Combinations of fewer probes are determined. For each combination, a condition number is calculated and then a mean condition number is calculated. The combination means are ordered relative to the reference mean and a predetermined number of combinations are selected. A blade tip parameter is derived for the selected combinations. Finally uncertainty of the blade tip parameter for each selected combination is calculated as a percentage of the reference blade tip parameter. | 08-29-2013 |
20130224029 | BALANCING OF ROTORS - A balanced rotor comprising a circumferential slot and a plurality of aerofoils each secured in the slot by a respective root, the root having a root block having circumferentially facing flanks and a seal wing extending circumferentially from one of the flanks, characterised in that the seal wing has a notch engaging a balance weight positioned between adjacent roots. | 08-29-2013 |
20130219914 | APPARATUS AND METHOD FOR CONDITIONING A FLUID - A fuel conditioning apparatus for de-oxygenating a liquid hydrocarbon fuel has a catalyst portion which, in turn, has an inlet portion and an outlet portion. A hydrocarbon fuel stream is fed through the inlet portion and into the catalyst portion where it passes over a catalytically active component. The catalytically active component promotes the reaction of the fuel with the dissolved oxygen in the fuel stream, converting it into less chemically reactive forms and thereby reducing the fuel's propensity to form carbonaceous deposits. | 08-29-2013 |
20130216364 | AIRCRAFT PROPULSION SYSTEM NACELLE - 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. | 08-22-2013 |
20130214178 | SURFACE COATING FOR INSPECTION - A method of inspecting an article includes: applying an organic liquid substance over at least a portion of the article to be inspected so as to form a surface layer thereon, wherein said surface layer is luminescent; irradiating the article with the surface layer thereon; and scanning the article to determine its shape. | 08-22-2013 |
20130214091 | AUXILIARY POWER SYSTEM - 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. | 08-22-2013 |
20130210572 | UNISON RING GEAR ASSEMBLY - 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. | 08-15-2013 |
20130206912 | MOISTURE DISPERSION - A method of reducing the amount of water in a region of air including: forming seed ice crystals; dispensing the seed ice crystals towards the region of air; allowing water in the region of air to freeze or deposit onto the seed ice crystals; and allowing the resulting ice crystals to move from the region of air so as to reduce the amount of water in the region of air. An ice crystal seeding assembly arranged to reduce the amount of water in a region of air, the seeding assembly includes an ice crystal seeder and dispensing means, the dispensing means being arranged to dispense seeded ice crystals towards the region of air so that water in the region of air freezes or deposits onto the seed ice crystals and that the resulting ice crystals move from the region of air. | 08-15-2013 |
20130200569 | LEAF SEAL - 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. | 08-08-2013 |
20130199721 | CONSOLIDATION DEVICE AND METHOD OF USING THE SAME - 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. | 08-08-2013 |
20130199624 | GAS TURBINE ENGINE NACELLE - 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. | 08-08-2013 |
20130199194 | COMBUSTOR HEAD ARRANGEMENT - 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. | 08-08-2013 |
20130195392 | BEARING ASSEMBLY - 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. | 08-01-2013 |
20130194703 | CURRENT LIMITER - 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. | 08-01-2013 |
20130192051 | THREADED FASTENER ASSEMBLY AND METHOD OF LOCKING A THREADED FASTENER - A threaded fastener assembly comprising a threaded fastener ( | 08-01-2013 |
20130191004 | GAS TURBINE ENGINE CONTROL - A gas turbine engine control apparatus comprises a controller | 07-25-2013 |
20130190928 | CONTROL SYSTEMS FOR MACHINES - A control system | 07-25-2013 |
20130189868 | ELECTRICAL CONNECTORS - 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. | 07-25-2013 |
20130189095 | TURBOMACHINE CASING ASSEMBLY - 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. | 07-25-2013 |
20130187307 | METHOD OF SEALING COOLING HOLES - A method of sealing a gap between an aerofoil component ( | 07-25-2013 |
20130186606 | HEAT EXCHANGER - 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. | 07-25-2013 |
20130185937 | METHOD OF SEALING COOLING HOLES - A method of selectively sealing at least one cooling hole provided on an aerofoil component ( | 07-25-2013 |