Abstract: The present invention is directed to a staged fuel injector that includes, inter alia, a main fuel circuit for delivering fuel to a main fuel atomizer and a pilot fuel circuit for delivering fuel to a pilot fuel atomizer which is located radially inward of the main fuel atomizer. The main fuel atomizer includes a radially outer prefilmer and a radially inner fuel swirler. Portions of the main fuel circuit are formed in the prefilmer and portions of the pilot fuel circuit are formed in the prefilmer and the fuel swirler and are positioned proximate to and in thermal contact with fuel exit ports associated with the main fuel circuit and formed in the prefilmer. As a result, the pilot fuel circuit cools the stagnant fuel located in main fuel circuit, including the exit ports, even when performing at engine power levels of up to 60% of the maximum take-off thrust.

Abstract: Engine health monitoring is used to assess the health of an engine, such as a gas turbine engine. Blades mounted on a shaft produce a modal response when excited. The shaft has an order related component that varies with the rotational velocity of the shaft. Modal responses are increased when the natural frequency range of the selected blade mode intersects with one of the order related components. By applying a short time chirp-Fourier transform with a frequency speed that is a function of a rate of change in the rotational velocity of the shaft a selected signal can be isolated. Cracks in the blades can be detected from the isolated signal.

Abstract: 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.

Abstract: This invention relates to a method and apparatus for controlling power distribution in an electrical aircraft propulsive system having at least one electrical propulsion unit which includes a plurality of rotatable blades, each blade having an adjustable pitch; a pitch adjusting mechanism for adjusting the pitch of the blades; at least one electrical machine electrically connected to the electrical propulsion unit so as to provide electrical power when in use; and, a control system, the method comprising the steps of: determining the required propulsion; determining whether the propulsive units are delivering the required propulsion; and, adjusting the pitch angle of the blades of at least one propulsive unit so as to increase or decrease the propulsion provided by that propulsive unit.

Abstract: A turbomachine blade comprising a blade tip and a metallic leading edge having a plurality of shear zones angled to the blade tip, wherein the shear strength of the shear zones is less than the shear strength of the remainder of the leading edge, such that in the event of an impact shear is initially initiated at the shear zones.

Abstract: A turbomachine blade comprising a metallic leading edge having a region having varying fracture resistance in a spanwise direction so as to increase energy absorption by the leading edge in the event of the blade being released from a turbomachine and impacting a casing of the turbomachine.

Abstract: A gas turbine engine intake duct 30, 80, 100 having an internal duct surface 54 comprising a main region 60, 82 having a particular finish and a secondary region 62, 84, 102 having a different finish. To be accompanied when published by FIG. 2.

Abstract: A turbomachine blade comprising a metallic leading edge having a weakened region extending in a spanwise direction; and a crack initiator for selectively initiating cracking of the metallic leading edge along the weakened region.

Abstract: A joint assembly has first to third end portions of first to third components and an elongate resilient connection member. The first end portion interconnects with the second in a castellated arrangement. The first and second end portions have repeating arrays of first and second, and third and fourth connection portions. The first connection portion is received inward the third, and its first location feature being aligned with a third location feature of the third forming a first cavity portion, and the second connection portion axially distal surface abutting against that of the fourth, with a second location feature of the second connection portion being aligned with a fourth location feature of the fourth connection portion forming a second cavity portion. The first and second cavity portions are aligned forming an annular cavity, with the connection member being receivable within the annular cavity interlocking the first component to the second.

Abstract: A method of forming a metal coated fibre (2). The method comprises: providing a sputter coating apparatus (10) comprising a deposition chamber (12) containing a target filament (6); applying a negative direct current biasing voltage to the filament (6); wherein the bias is alternately pulsed between a high power condition and a low power condition.

Abstract: A rotor arrangement including: a rotor stage having an annular array of rotor blades each blade having a tip; a casing that surrounds the rotor stage and defines a clearance between the tips and the casing; and an over tip leakage measurement system including a multi-hole total pressure probe mounted to a stationary component downstream of the rotor stage; the probe arranged such that the axis of at least one of the holes is substantially aligned with an expected flow direction from the rotor stage.

Abstract: An output member for a Direct Impact Hopkinson pressure bar includes an elongate tube portion and a disc-shaped cap portion. The tube portion has a first end and an opposite second end, while the cap portion includes a first face and an opposite second face. A circular stub protrudes from a centre of the first face, and a circular cavity is formed in the second face. Each of the stub and the cavity is concentric with the cap portion, with a diameter of the cavity being greater than a diameter of the stub. The second face of the cap portion is positioned in intimate contact with the first end of the tube portion, with the cap portion being concentric with the tube portion.

Abstract: An aerofoil blade or vane for the turbine of a gas turbine engine includes: an aerofoil leading edge; an aerofoil trailing edge; an aerofoil suction side; and at least one reverse-pass coolant passage, extending within the aerofoil blade or vane; wherein the at least one reverse-pass coolant passage includes a substantial reverse-pass portion in which, in use, coolant flows in a direction away from the trailing edge and towards the leading edge.

Abstract: A fuel delivery system comprises a pump, a fuel metering device located downstream of the pump, and a fuel spill loop from the fuel metering device to a discharge point at a location upstream of the pump. The fuel metering device regulates the fuel flow to a combustor and directs surplus fuel delivered by the pump through the fuel spill loop. The system further includes a means for controlling one or more of the pressure and volume of the fuel flow delivered to the fuel metering device independently of the engine operating conditions to thereby control the temperature of the fuel.

Abstract: A joint assembly includes a first end portion of a first hollow component, a second end portion of a second hollow component, and a first and second resilient connection member. First end portion interconnects with second end portion. First end portion includes a first and second location feature on an outwardly facing surface and axially distally facing surface respectively. Second end portion includes a third and fourth location feature on an inwardly facing surface and axially distally facing surface respectively. First end portion is slidably received inwardly of second end portion, with first location feature being aligned with third location feature to form a first annular cavity, and second location feature being aligned with fourth location feature to form a second annular cavity. First connection member is receivable within first annular cavity, and second connection member is receivable within second annular cavity, to interlock first component to second component.

Abstract: An arrangement of electrical machines including: a variable reluctance rotor. The arrangement also including an annular array of stators; each stator configured to function, in conjunction with the rotor, as an electrical machine.

Abstract: A bearing cage for an anti-friction bearing includes a plurality of cage pockets with each cage pocket being adapted to accommodate a rolling element. Each of the cage pockets has a cylindrical profile with a corresponding cylindrical axis. The cage pockets are arranged in an alternating circumferential array of first cage pockets and second cage pockets, with the cylindrical axis of each first cage pocket intersecting with a rotational axis of the bearing cage on a first side of the bearing cage, and the cylindrical axis of each second cage pocket intersecting with the rotational axis of the bearing cage on a second opposite side of the bearing cage.

Abstract: A waveguide for a sensor system for mounting in a casing structure to measure the clearance between the casing structure and a rotary blade. The casing structure, which may be a turbine casing structure, includes a radially outer casing portion and a radially inner casing portion (e.g. a segment seal). The waveguide includes a radially outer portion for mounting in the radially outer casing portion and a radially inner portion for mounting in the radially inner casing portion. The two portions are sealed together and bridged by a sealing portion having a deformable portion.

Abstract: 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.

Abstract: 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 normalize each transmitted waveform at each inspection location to the nominal axis; and identifying a signature signal from the normalized transmitted waveform at each inspection location.