Abstract: A remote monitoring system including a sub-system, local to a nuclear power plant and a remote sub-system at an operations base. Process data is collected manually by a hand-held computer and automatically by instrumentation on the power plant. The data collected is stored on a storage device before being transmitted via a communication link to a remote computer. The remote computer runs data analysis and diagnostic simulations on the process data from the power plant to predict future events.

Abstract: The fan cowl (12) of a ducted fan gas turbine engine (10) has a downstream portion including an inner casing (30) that surrounds a honeycomb structure (36) in abutting engagement. Honeycomb structure (36) is made up of a number of closely spaced honeycomb blocks (36a) fixed about a liner (40), one or more of which blocks, if struck by a broken fan blade portion, will move relative to those not struck, in a radially outward direction, thus reducing the crushing force of the blow, and only flexing casing (30) instead of permanently deforming or puncturing it.

Abstract: Monitoring of clearance gaps between a rotating component and a surrounding cowling surface is difficult in view of the general packaging constraints. Furthermore, when such operation occurs at high temperature there may be distortion in view of natural expansion and contraction over thermal gradients of the monitoring arrangement. By provision of a diffractive optical element with light guided for reflection against an aperture end and a part of a rotating component, it is possible through shift in the reflective wavelength frequencies to monitor and determine clearance gaps between that aperture end and incident parts of the rotating component.

Abstract: A deflector element is provided, in order to improve temperature interface control with respect to directional solidification of a component casting. This deflector element is formed during the mould making process and is arranged to be positioned with respect to a part of a principal mould formation within which the final cast component is produced. The deflector element ensures a uniform temperature throughout the component cross-section relative to other parts of the component as it is solidified.

Abstract: A gas turbine engine fan blade (22) and disk assembly (30) is provided with levers (36) with which to apply a force to the radially inner end of respective blades (22) so as to move the roots (26) of the blades (22) into abutting engagement with the side walls of the inverted “V” shaped grooves (32) in the disk rim (34), and thereby prevent relative wearing movement therebetween. The levers (36) are appropriately moved by rotation of respective screws (52) that pass through exposed ends thereof in screw threaded engagement, and abut a fixed land (46) so as to apply a pivoting force on each lever (36).

Abstract: A turbofan gas turbine engine (10) comprises a fan rotor and a compressor rotor (62). The fan rotor (24) carries a plurality of circumferentially spaced radially outwardly extending fan blades (26). The compressor rotor carries a plurality of circumferentially spaced radially outwardly extending compressor blades (64). The fan rotor (24) is mounted on a fan shaft (38) and the compressor rotor (62) is mounted on a compressor shaft (68). The compressor shaft (68) is arranged around the fan shaft (38). The fan rotor (24) is rotatably mounted on a support structure (40) by a first bearing (50) and the compressor rotor (62) is rotatably mounted on the support structure (40) by a second bearing (58) spaced axially from the first bearing (50). The fan and compressor rotors (24, 62) are normally arranged coaxially with each other and with the support structure (40).

Abstract: A method of predicting telemetry data for a system under analysis is provided, the method including the steps of: linking a computational fluid dynamics model and a finite element analysis model at a system condition; converging said computational fluid dynamics model and said finite element analysis model to obtain a converged solution; and extracting data from discrete locations in said converged solution to provide predicted telemetry data for said system condition. The predicted telemetry data is typically thermocouple data, thus providing virtual thermocouples for further analysis. A method of validating a system model using the predicted telemetry data is also provided.

Abstract: A leakage drain is used to provide an indication that leakage of a fluid has occurred within an engine. Previously, such leakage was detected by visual inspection of a retained drop at the outlet of a drain. With the present invention, a sensor arrangement comprising electrodes is located within or about the leakage drain whereby leakage fluid creates a film across those electrodes. Relative presence or absence or thickness of film causes variation in a detected electrical response (capacitance, reactance, resistance or impedance) and this variation is utilized in order to determine whether fluid leakage has occurred. Additionally, by time of flight analysis using electrostatic sensors it is possible to determine fluid flow rate. By analysis at different incident frequencies, a characteristic response for a particular type of leakage fluid is obtained. Thus, it is possible to deduce the type of leakage fluid as well as the rate of leakage.

Abstract: A gas turbine engine (10) is provided with a stage of turbine blades (22) surrounded by hollow shroud segments (28). Cooling of the shroud segments (28) is achieved by providing a flow of engine leakage air from space volume (48) centrally of the engine (10) via an annular compartment (46) wherein it is diverted away from the blade cooling system and passed via piping (44) within each guide vane (20) to shroud segments (28). The flow impingement cools the shroud segments (28) and then passes into the gas annulus via slots (60).

Abstract: A computer-implemented method of generating an inspection program for a computer-controlled coordinate measuring probe comprises the steps of: (a) receiving nominal geometry data for a component, (b) receiving inspection requirement data specifying one or more selected shape characteristics of the component, (c) determining from the nominal geometry data and the inspection requirement data an inspection path for a computer-controlled coordinate measuring probe, the inspection path enabling the measuring probe to measure actual component coordinates associated with the selected shape characteristics, and (d) generating an inspection program for moving the computer-controlled coordinate measuring probe along the inspection path.

Abstract: A landing arrangement for an aircraft comprises an aircraft support assembly (22) to support the aircraft (10) when the aircraft is on the ground. The aircraft support assembly (2) is movable between a first ground engaging condition (22b) in which the aircraft nose (24) is spaced above the ground by a first distance (X) and a second ground engaging condition (22C) in which the aircraft nose (24) is spaced above the ground by a second distance (Y). The second distance (Y) is less than the first distance (X).

Abstract: An assembly for manufacture of a component by hot isostatic pressing comprises a first workpiece and a second workpiece. The first workpiece and second workpiece are assembled to define a cavity. Removable tooling pieces are provided to the assembly which further define the cavity and which are shaped to apply a forging load to a powder within the cavity during hot isostatic pressing.

Abstract: A casing arrangement (20) for surrounding a rotary component (16) of a gas turbine engine (10) especially a turbine is disclosed. The arrangement (20) comprises an annular casing member (22A) surrounding a bladed rotary section, such as a turbine stage. An array of gas path liner segments are suspended from the casing at a nominal clearance gap form the tips of the rotary blades. Running clearance is determined by expansion and contraction of the casing which, in turn, is controlled by a supply of heat transfer fluid passed through heat transfer holes in the casing. The casing arrangement described includes a passive pressure bleed effective during engine deceleration to reduce a pressure differential driving the fluid flow in order to avoid too rapid contraction of the casing as a result of overcooling.

Abstract: The fan duct of a ducted fan gas turbine engine has a fan case (20) lined with a honeycomb structure (22) that acts to absorb the energy of a separated part of a blade (16). A layer of composite material (24) lining honeycomb structure (22) delaminates/breaks when a separated blade part passes through a further, inner honeycomb liner (26) and hits it. The resulting free end of composite liner (24) wraps round the striking end of the blade part, thus blunting the cutting action of the blade part and spreading the generated forces to the extent that the blade part is de-energised sufficiently to prevent it penetrating the fan case (20).

Abstract: In a laser shock peening process, the shape of the spot generated by the laser beam is changed on the fly. This is achieved, for example, by a masking device which is movable into and out of the path of the laser beam. Laser shock peening spots can consequently be shaped so as to avoid the spots overlapping an edge of the workpiece, or any other feature which may be damaged by the laser energy.

Abstract: A turbine component, such as a turbine blade 1, 21, has a coolant supply passage 4, 24 and a cooling chamber 3, 23 connected by an injection passage 5, 25. The cooling chamber 3, 23 includes flow guides in the form of vanes 7, 8 or grooves 37 which act to create a coolant flow in a spiral direction. Thus, there is limited coolant flow impingement and greater cooling effect to allow the turbine component to operate at higher temperatures.

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: An adaptive control method is provided with particular relevance in methods which use a varying input frequency for analysis of an oscillatory response of a system, such as sine sweep testing. In one aspect the method includes the steps of applying a drive force having at least one sinusoidal component to said system, the frequency of the sinusoidal component being changed with time; and measuring an oscillatory response of said system; the method further including the step of providing a control signal based on at least a comparison between the frequencies of the sinusoidal component and the oscillatory response, wherein the rate at which the frequency of the sinusoidal component is changed is adjusted according to the control signal, so as to adapt the rate of frequency change to the region of the response spectrum being analyzed. A test apparatus capable of carrying out the methods of the invention is also provided.

Abstract: A gas turbine engine (10) comprises a second compressor (14), a first compressor (16), a heat exchanger (18), a combustor (20), a first turbine (22), a second turbine (24) and a third turbine (26) arranged in flow series. The first turbine (22) is arranged to drive the first compressor (16). The second turbine (24) is arranged to drive the second compressor (14). There are means to inject liquid into the gas turbine engine (10). The means to inject liquid is arranged to inject liquid upstream (46) of the second compressor (14), within (48) the second compressor (14), between (50) the second compressor (14) and the first compressor (16), within (52) the first compressor (16), between (54) the first compressor (16) and the heat exchanger (18) or within (56) the combustor (20) to boost the power of the gas turbine engine (10).

Abstract: An instrumentation system including a plurality of sensors attached to a test piece, each of the sensors provided with an electrical signal generating device and an electrical signal measurement device. Each sensor is located remotely from its electrical signal measurement device, and connected thereto by connectors. A method of testing connectivity of the instrumentation system including: inducing an electrical signal in a first sensor; and checking that the electric signal is received in the corresponding signal measurement device.