Abstract: A rotor blade comprising a core blade section; and a trailing edge section, the trailing edge section being attached to the core blade section along a join interface. The trailing edge section comprises a shape memory material which is actuable so as to cause selective deformation of the trailing edge section between a first condition in which a trailing edge of the trailing edge section follows a substantially smooth profile and a second condition in which the trailing edge is perturbed. The direction of the perturbation may be oblique or perpendicular to the direction of flow over the blade in use. The rotor blade may be a fan or propeller for a gas turbine engine.

Abstract: A strain sensor apparatus for a rotatable shaft including a radiation emitter/receiver, a vibration element attached to the shaft and a reflector that is positioned to reflect radiation onto the vibration element.

Abstract: A rotor and a stator assembly, wherein the rotor (30) comprises at least one stage of rotor blades (32) and the stator (34) comprises at least one stage of turbine stator vanes (36). The rotor blades (32) have aerofoils and platforms (42) and the turbine stator vanes (36) having aerofoils and platforms (48). A seal (43,45) is defined between the rotor blade (32) platforms (42) and the stator vane (36) platforms (48) wherein a portion (42B) of the rotor blade platforms (42) and/or a portion (48B) of the stator vane (36) platforms (48) comprise a shape memory alloy member or a bimetallic member. The shape memory alloy member, or bimetallic member, controls the flow of cooling air through the seals (43,45) allowing a greater cooling flow at higher temperatures than at lower temperatures.

Abstract: A balancing assembly for a rotor comprises a mass, a displacement arrangement for displacing the mass along a guide arrangement. The guide arrangement extends circumferentially and the displacement arrangement can move the mass circumferentially around the principal axis of the rotor during rotation of the rotor.

Abstract: Control of blade clearance gaps between rotating turbine blades and an associated casing in a gas turbine engine is important in order to maintain operational efficiency. It is desirable to achieve accurate gap control but previous passive and scheduled thermal gap adjustment systems have been relatively course. By provision of a winding through which a specific electrical current is passed in order to create electro-magnetic force for displacement of an armature associated with a seal forming part of the casing it is possible to adjust the gap between that seal and a tip part of a rotating blade assembly. Normally a blade gap monitoring technique is used in association with specific operational requirements with respect to the gap by the control in order to determine the electrical current presented to the winding.

Abstract: A method for joining components comprises locating a region, such as an end region 24, of a shape memory alloy (SMA) material component 10 adjacent to a further component 12, and generating localized plastic deformation of the aforesaid region to create a joint between the components 10, 12. The localized plastic deformation of the shape memory alloy material component 10 is preferably generated by applying a shock load to the shape memory alloy material component 10.

Abstract: A boundary layer control arrangement comprises a pulse generator communicating with a surface having a fluid boundary layer thereacross. The boundary layer control arrangement further includes a fluid supply means for supplying a fluid to the surface via the pulse generator. The pulse generator is constructed such that fluid acts on the pulse generator to cause the fluid to pulse. Pulsing fluid passes from the pulse generator to the surface.

Abstract: An actuator (12) is disclosed for example controlling gas flow in a gas turbine engine. The actuator (12) comprises a first portion (14) having shape memory properties, and a second portion (16) formed of substantially the same material as the first portion and having reduced shape memory properties relative to the first portion. The first portion (14) is movable from a first position to a second position at a temperature above the phase transition temperature of the shape memory material of the first portion (14). The second portion (16) is arranged to urge the first portion (14) from the second position to the first position at a temperature below the phase transition temperature of the shape memory material.

Abstract: An arrangement for controlling flow of fluid to a component of a gas turbine engine, the arrangement comprising: a conduit, coupled to a supply of fluid, for providing fluid to the component of the gas turbine engine; a magnetic valve for at least partially restricting the conduit and having a valve member with at least a first configuration in which the conduit is at least partially restricted and a second configuration in which the conduit is relatively open, wherein the configuration of the valve member is controlled by magnetic flux in a magnetic circuit which includes at least one member comprising ferromagnetic material, whereby the configuration is responsive to the temperature of the ferromagnetic material.

Abstract: An actuator (12) is disclosed for example controlling gas flow in a gas turbine engine. The actuator (12) comprises a first portion (14) having shape memory properties, and a second portion (16) formed of substantially the same material as the first portion and having reduced shape memory properties relative to the first portion. The first portion (14) is movable from a first position to a second position at a temperature above the phase transition temperature of the shape memory material of the first portion (14). The second portion (16) is arranged to urge the first portion (14) from the second position to the first position at a temperature below the phase transition temperature of the shape memory material.

Abstract: A magnetic valve arrangement for controlling flow of fluid, the magnetic valve arrangement having at least one ferromagnetic element (28, 42, 52) forming a portion of a magnetic circuit, a valve member (28, 50) and a valve seat (35); the valve member (28, 50) has a passage (31) therethrough for the flow of fluid and is moveable between a first position, in which the valve member (28, 50) abuts the valve seat (35) to restrict a fluid flow (26), and a second position, in which the valve member (28, 50) is spaced from the valve seat (35) to allow a fluid flow (26) into and through the passage (31) in the valve member (28, 50), wherein the position of the valve member (28, 50) is dependent on the temperature of the ferromagnetic element (28, 42, 52).

Abstract: An arrangement for controlling flow of fluid to at least one component of a gas turbine engine, the arrangement comprising: a first conduit for providing fluid to the component; a flow valve, for controlling the flow of fluid in the first conduit, having first and second configurations; a second conduit for providing fluid to the flow valve to the control the configuration of the flow valve; and a magnetic valve, for controlling the flow of fluid in the second conduit, having first and second configurations and including at least one ferromagnet forming a portion of a magnetic circuit, whereby the configuration of the magnetic valve depends on the temperature of the ferromagnet; the member comprising ferromagnetic material (68) is thermally coupled to one of the group comprising the fluid in the first conduit (24), the fluid in the second conduit (54) and the component; and the configuration of the flow valve is dependent on the configuration of the magnetic valve.

Abstract: Control of blade clearance gaps between rotating turbine blades and an associated casing in a gas turbine engine is important in order to maintain operational efficiency. It is desirable to achieve accurate gap control but previous passive and scheduled thermal gap adjustment systems have been relatively course. By provision of a winding through which a specific electrical current is passed in order to create electro-magnetic force for displacement of an armature associated with a seal forming part of the casing it is possible to adjust the gap between that seal and a tip part of a rotating blade assembly. Normally a blade gap monitoring technique is used in association with specific operational requirements with respect to the gap by the control in order to determine the electrical current presented to the winding.

Abstract: A gas turbine engine exhaust nozzle arrangement for the flow of exhaust gases therethrough between an upstream end and a downstream end thereof comprising a nozzle and a plurality of tabs which extend in a generally axial direction from a downstream portion of the nozzle wherein the nozzle further comprises an actuation mechanism capable of moving the tabs between a first deployed position, where the tabs interact with a gas stream to reduce exhaust noise thereof, and a second non-deployed position, where the tabs are substantially aerodynamically unobtrusive.

Abstract: A method is provided whereby confidence in a validation parameter set is achieved by comparison with a known sample of a parameter in terms of the expected template comparison score as well as mean values and deviation from that score. Thus, with respect to user individual identification, biometric parameters such as fingerprint or handwriting or voice recognition can be utilised to compare the stored template for that individual with the putative biometric response in order to determine deviation from the mean. Previous systems provided a stored template and then ranging either side to simply give a pass/fail response. By adaptation of the ranging quotient for a particular individual, a percentage confidence in the pass/fail response can be achieved. For example an individual -may have a wider range of deviation than another individual and therefore close repetition of the biometric data may be indicative of a lower percentage confidence than with an individual with a narrower deviation.

Abstract: A turbofan gas turbine engine (10) comprises a compressor rotor (24) carrying a plurality of circumferentially spaced radially extending rotor blades (26) and a casing (28) surrounding the compressor rotor (24) and compressor rotor blades (26). A compressor rotor blade tip seal (48) comprises an annular member (30) secured to and arranged within the casing (28). The annular member (40) has a plurality of circumferentially spaced axially extending corrugations (32) and a plurality of radially spaced circumferentially extending corrugations (34). A lining (40) is secured to and arranged within the annular member (30). The lining (40) is spaced radially from the tips (27) of the compressor rotor blades (26) to form a clearance (29). An actuator (56) is provided to move the annular member (30) and lining (40) radially to control the size of the clearance (29).

Abstract: A turbofan gas turbine engine (10) comprises a compressor rotor (24) carrying a plurality of circumferentially spaced radially extending rotor blades (26) and a casing (28) surrounding the compressor rotor (24) and compressor rotor blades (26). A compressor rotor blade tip seal (48) comprises an annular member (30) secured to and arranged within the casing (28). The annular member (40) has a plurality of circumferentially spaced axially extending corrugations (32) and a plurality of radially spaced circumferentially extending corrugations (34). A lining (40) is secured to and arranged within the annular member (30). The lining (40) is spaced radially from the tips (27) of the compressor rotor blades (26) to form a clearance (29). An actuator (56) is provided to move the annular member (30) and lining (40) radially to control the size of the clearance (29).

Abstract: A joint between a first component (30) and a second component (32) and the second component (32) comprises a shape memory material component. The first component (30) has a half dovetail shaped slot (34) and the shape memory material second component (32) has a half dovetail shaped attachment feature (36) and the half dovetail shaped attachment feature (36) of the shape memory material second component (32) locates in the half dovetail shaped slot (34) in the first component (30).

Abstract: A device (10) for use in the verification of handwriting, comprising: a body (12) having a surface (11) over which a writing instrument (8) is moved during the generation of a piece of handwriting; a transducer (14) for transducing stress-wave activity in the body (12) to an analogue time varying signal (15); and digitizing means (22) for converting the analogue time varying signal (15) into a digital signal (27, 31, 11), the digitizing means (22) comprising a sampler (22) arranged to under-sample the analogue time varying signal (15).

Abstract: Actuators utilising shape memory alloy materials are known with regard to gas turbine engines. Such shape memory alloys have been used with respect to deformation provided in vanes and blades as well as nozzle elements in order that variations can be made in engine configuration dependent upon thermal cycling. Unfortunately, pedestals in order to provide spacing between the shape memory alloy and an antagonistic bias has resulted in uneven stress distribution as well as a higher thermal mass for the shape memory alloy. An uneven stress distribution will limit operational life whilst a higher thermal mass will result in slower reaction times. By separation of the shape memory alloy or material from its antagonistic bias through use of a slide element, a reduction in thermal mass is achieved and, more importantly, stress differentiation across the actuator is reduced.