Abstract: Apparatus for adaptive cooling comprising a first component having at least one aperture extending therethrough with a sacrificial component positioned within the at least one aperture. The first component is operable at a maximum duty temperature and the sacrificial component has a melting or sublimation point below the maximum duty temperature of the first component. The sacrificial component defines an effective aperture the size of which may be increased if, in use, the sacrificial component is subjected to a temperature between the melting or sublimation point of the sacrificial component and the maximum duty temperature of the first component.

Abstract: A component comprises a multiplicity of cooling passages arranged in two intersecting arrays to form a multiplicity of cooling passage intersections. Air jet interactions are generated at cooling passage intersections when air is passed through the cooling passages. The spacing of the passages in at least one of the arrays is chosen to provide a predetermined range of intersection density in a selected region or regions of the component.

Abstract: A fuel injector for a gas turbine engine has a swirl slot that supplies fuel to a prefilmer. The swirl slot has an upstream lip and a downstream lip that are arranged eccentrically. The slot is thus provided with an area of high static pressure and an area of low static pressure caused by the flowing over the eccentrically arranged lips.

Abstract: A containment casing 1 is provided in which tubular composite layers 2, 3 are arranged in an angular staggered relationship to minimise overlap between the interstitial spacing between tubes in each respective layer 2, 3. In such circumstances, with a continuous planar layer 4, 5 on one or both sides, operational integrity is maintained with a lightweight containment casing 1 in comparison with prior arrangements but retaining resistance to fragment penetration.

Abstract: There are a number of sensors (2, 22) such as thermocouples which can provide a putative measurand signal which is within a predicted range for such signals whilst the sensor is incorrectly operating, such as as due to an open circuit. Techniques and processes are available to determine by interrogation sensor operational validity, but these can distort the measurand signal if correct. By time division multiplex techniques the present arrangement takes a putative measurand signal from a sensor (2, 22) in order that either within the same time division or more normally a separate time division, an interrogation of the sensor is performed in order to determine accuracy and therefore validity of the sensor 22.

Abstract: In order to create titanium components with a titanium composite insert, a method is provided whereby an initial pre form 1 has a groove 2 formed in it. An encapsulating member 4 is then provided about the groove 2 in order to create a cavity 5 which is filled with titanium alloy powder 6. This titanium alloy powder 6 is densified and then accurately machined in order to create a groove insert form 7 which can accommodate a titanium composite material pre form insert 8 and further titanium alloy powder 9 such that through a high temperature isostatic pressing (HIP) process, the insert 8 is embedded. The original component form 1 can then be machined in order to create the final component elements such as aerofoils 13.

Abstract: With an active magnetic bearing 1 there is a limit to the available rapidity of response to transient loadings upon a target or rotor 4. Thus, in accordance with the present invention, storage devices 25, 125, 225, 35 hold an electrical voltage VS significantly greater than the normal supply voltage V provided by a normal electrical source 22, 32. In such circumstances when a very large transient loading is detected on the bearing 1 a switch 26, 37 discharges the supply voltage VS across the coil 23, 33 in order that a more rapid increase and higher value inductance current IT is presented to the coil 22, 32 in response to that variable loading upon the target/rotor 24, 34. The electrical discharge from the storage device 25, 125, 225, 35 can be adjusted using the switch 26, 37 or mixing the storage devices 25, 125, 225, 35 as required for an appropriate discharge signal shape.

Abstract: A method for operating a multi-stage combustor of a gas turbine engine comprises: (a) determining a combustor air entry temperature; (b) determining the combustor air entry flow rate; and (c) controlling the fuel split ratio to stages of the combustor on the basis of the combustor air entry flow rate and the combustor air entry temperature.

Abstract: A fan turbine engine arrangement is provided in which a core engine is aligned such that an input of a nacelle is aligned with the upwash of a wing to which the arrangement is secured. The engine drives a fan such that bypass flows produced by the fan are guided by a duct to present a downward component for uplift. The core engine presents its output flow through a nozzle which is aligned with the fundamental axis Y—Y of the engine. In such circumstances, the bypass flows cross the core engine flow from the nozzle unless that engine is adjustable during operation in order to maintain alignment dependent upon lift requirements.

Abstract: A method for filtering spurious resonances from an NMR dataset comprises the steps of: (a) creating a first, non-oscillating magnetic field of a predetermined field strength across a sample, (b) intermittently exposing the sample to a second, oscillating magnetic field orthogonal to the first to generate an NMR signal, (c) detecting the NMR signal from the sample, (d) adjusting the first magnetic field to a different predetermined field strength and repeating steps (a) to (c), and (d) comparing the detected signals to obtain an NMR dataset from the sample from which spurious resonances have been filtered.

Abstract: A lubrication system comprises a reservoir for lubricant, lubricant delivery means to deliver lubricant to at least one component to be lubricated, an injector associated with each component, a control system to control the opening and closing of each injector and scavenge means to remove surplus lubricant from around each component and return it to the reservoir. Each injector comprises a pulsative injector, controlled by the control system to deliver lubricant to its associated component in a series of discrete pulses. In a preferred embodiment both the delivery of oil to each component and the scavenging of oil from each component are controlled in response to sensed conditions of that component.

Abstract: In order to regulate fuel flow to the combustor (36) of the combustion turbine engine (10) having a primary combustion zone (64) and at least one further combustion zone, the temperature of the inlet and outlet of the combustor (36) are determined, as are first and second values representing first and second properties, with the first property being one of: the total enthalpy rise in the combustor (36), the equivalence ratio of the combustor (36), the fuel/air ratio of said combustor (36), the fuel flow through the combustor, and the second property being one of: the enthalpy rise in the primary zone (64), the equivalence ratio of said primary zone (64), the fuel/air ratio of the primary zone(64); the temperature rise across the primary zone(64), or the fuel flow through the primary zone (64). The second property is determined from the first value and the current value of the ratio of the fuel to the primary zone (64) to the total fuel to the combustor (36).

Abstract: An electrical machine, such as a transverse flux motor, incorporates a stator core assembly 1. The stator core assembly 1 comprises a stator frame 4 upon which stator cores 2,3 are located with spacer elements 7 therebetween. A number of stator pole members 10,11 are located such that channels 13 in these members 10,11 accommodate limbs 5,6 of the cores 2,3. The stator pole members 10,11 straddle more than two limbs 5,6 in order to provide greater structural stability for the assembly 1 despite magnetic flux cycling and other distortion effects. By such greater structural stability more accurate control of a gap between the stator core assembly 1 and a rotor in the machine can be maintained.

Abstract: There are difficulties with regard to observing a rotating component in an obscuring environment such as typical of a gas turbine engine where there may be soot, flames, light signals and moisture. It will be understood that simply increasing the light intensity will increase scatter and therefore may “blind” a camera in terms of viewing distinctive features and targets within a rotating component. The present arrangement provides a mirror with an aperture such that an illuminating light source is directed towards a rotating component such that reflection is similarly incident upon the reflective mirror and light deflected to the camera. In such circumstances the camera is less susceptible to light scatter obscuration.

Abstract: A mounting arrangement 1 is provided in which clamping pairs comprising a clamping pad 2 and seating pads 3 are arranged about a mounting end of a component 4. Thus, the component 4 is appropriately presented to a machining device but the component 4 can slip relative to the pads 2, 3 in order to relieve residual stresses in the component due to initial forging processes. A damper 8 is provided in order to augment vibration control in association with the contact abutments between the pads 2, 3. In such circumstances accurate machining of a component 4 to a final profile 6 from an initial rough profile 5 can be achieved more efficiently without periodic release of the component 4 so that distortions are avoided in the final component as a result of retained residual stresses by previous clamping.

Abstract: A seal arrangement (73) is provided in which seal elements (77) incorporate passages (90) allowing an air flow to be presented to tip edges (78) of the seal elements, in order to create air suspension and diminish excessive wear. These passages (90) are created by recesses in the respective adjacent juxtaposed seal elements (77). In a seal assembly (71) a seal arrangement (73) is secured within a float chamber (70) whereby radial movement is allowed to accommodate for movements in the shaft (72). The radial movement is resisted by a bias created by air flow (86) into the float chamber (70). The air flow (86) may also be presented through the passages (90) in order to create the desired air suspension of the seal elements (77).

Abstract: A drive apparatus (10) for propelling a vehicle across a body of water is described. The apparatus (10) comprises a prime mover, for example a gas turbine engine (12), and a propelling arrangement (26) driven by the prime mover for propelling the vehicle across the body of water and thereby provide a reaction force on the prime mover. The apparatus (10) also includes a braking arrangement (42) to apply a braking force to the propelling arrangement (26).

Abstract: A sensor 10 comprises an array of electrostatic sensor elements 12, each centred at a respective sensing position 14. Each element produces a respective output signal at 16. The outputs 16 can be used to drive respective pixels of a display. This allows an image to be created to represent the electrostatic charge distribution across the region to which the sensor is directed.

Abstract: An assembly comprising a clipping bracket mounting a first component to a second component, the second component having an array of fixings, the bracket comprises a first leg attached at one end to one of the fixings; the bracket further comprises a clipping member extending from the second end and partly defined by two fingers engaging around, but not under, either side of an adjacent fixing.

Abstract: A turbine stage of a gas turbine engine (10) is surrounded by a ring of liner segments (34). The liner segments (34) can be moved radially in unison towards and away from the tips or fins (38) of blades (36), by rotation of a connected unison ring (18), so as to avoid blade fin rub. Alternatively, the segments (34) can be moved in a common direction by bodily movement of the connected unison ring (18) so as to avoid blade fin rub during off axis rotation of the turbine stage.