Abstract: A panel attachment device for removably connecting a panel to a casing comprises a first bracket, a second bracket, and a link. The link has a first end and an opposite second end, with the first end being removably connected to the first bracket and the second end being removably connected to the second bracket. Each of the first end and second ends is located by, and rotatable relative to, the first bracket and second bracket respectively to thereby constrain the panel relative to the casing.

Abstract: 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.

Abstract: 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.

Abstract: A fluid impingement arrangement comprising a supply manifold and at least one nozzle exit coupled to the supply manifold. The nozzle exit is arranged as a Coanda surface having a restriction and has at least one static pressure tapping that cross-connects two regions of the restriction to induce passive oscillation in a fluid jet passing through the nozzle exit.

Abstract: 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.

Abstract: An aircraft gas turbine engine has first and second electrical harnesses formed from respective first and second flexible printed circuit boards which each provides a plurality of spaced conductive tracks. The conductive tracks carry signal types which either (i) provide engine control and can cause hazardous engine conditions in the event of their failure, (ii) detect or prevent hazardous conditions of the engine, or (iii) are not of type (i) and/or of type (ii). The first flexible printed circuit board provides all the conductive tracks which carry signals of type (i) or the first flexible printed circuit board provides all the conductive tracks which carry signals of type (ii). The second flexible printed circuit board provides all the remaining conductive tracks. The first electrical harness is fire-resistant for a period of five minutes without any exposure of its conductive tracks so that the conductive tracks can carry their signals.

Abstract: A total temperature probe comprising a hollow elongate shroud defined by a shroud wall that envelops a first cavity. The shroud wall is comprised of an inner skin and an outer skin which enclose a second cavity therebetween. A temperature sensor mounted in the first cavity. In use, fluid flow is received into the first cavity, passes through at least one aperture in the inner skin into the second cavity and then passes out of the shroud through at least one aperture in the outer skin. Beneficially, heat conduction across the inner skin is minimal.

Abstract: A method of inhibiting ice accretion within a turbine engine, including the steps: (a) operating the turbine engine at a predetermined engine speed; and (b) driving the compressor of the turbine engine at an elevated speed which is greater than the nominal speed of the compressor at the predetermined engine speed so as to inhibit ice accretion within the compressor.

Abstract: A vane is provided for directing hot gases in a gas turbine engine. The vane includes a hollow aerofoil portion, which in use spans the working gas annulus of the engine. The vane further includes an impingement tube which forms a covering over the interior surface of the aerofoil portion and which has jet-forming apertures formed therein for the production of impingement cooling jets. The impingement tube includes two tube portions which are separately insertable into position into the aerofoil portion to form the covering. The impingement tube further includes an expansion member which, when the tube portions are in position in the aerofoil portion, is locatable in the aerofoil portion to urge each tube portion outwardly and thereby holds the tube portions in position against the aerofoil portion.

Abstract: A fuel injector for a gas turbine engine includes a nozzle body defining a central axis and having a main fuel circuit. An air circuit is formed within the nozzle body inboard of the main fuel circuit. A primary pilot fuel circuit is formed within the nozzle body inboard of the air circuit. A secondary pilot fuel circuit is formed within the nozzle body inboard of the air circuit and outboard of the primary pilot fuel circuit.

Abstract: An electrical machine includes a stator including a plurality of electrical phases and a rotor having a plurality of magnets. Each electrical phase includes at least one coil and power electronics. There are means to detect an electrical short circuit in a faulted coil and means to supply an electrical current to the faulted coil when an electrical short circuit is detected in the faulted coil. The means to supply the electrical current to the faulted coil includes one or more un-faulted electrical phases of the electrical machine. The un-faulted electrical phases of the electrical machine are arranged to supply the electrical current to the electrical phase containing the faulted coil. The power electronics of the un-faulted electrical phases are arranged to supply the electrical current from the un-faulted electrical phase to the power electronics of the electrical phase having the faulted coil. This overcomes a problem of a fault in the DC or AC busbar of the electrical machine.

Abstract: A biasing means is provided for securing a plurality of sealing components which are arranged to seal gaps between adjacent structural components in a turbine, the biasing means having three foot regions joined in a substantially linear fashion by two resilient curved arms, wherein each arm has securing means for securing the biasing means to one of said structural components such that when the biasing means is secured to said one of said structural components, each of said foot regions contacts one of said sealing components and the curved arms urge the sealing components towards one of said structural components so that the sealing components collectively create a seal over the gap between said structural components. An apparatus for sealing gaps between adjacent structural components which includes the biasing means is also provided as is a method of sealing gaps in a turbine.

Abstract: A method of detecting a flow blockage in a pipe includes: arranging a fluid flow along the pipe, the pipe in fluid communication with a pressure sensor; configuring the pressure sensor to measure a pressure within the pipe; recording plurality of measurements of pressure within the pipe; sampling ‘n’ successive values of pressure within the pipe; performing an analytical test on the ‘n’ successive values, the analytical test producing an output value, the output value representative of a variation in the individual ones of the ‘n’ successive values; comparing the output value to a pre-defined threshold value, the threshold value indicative of a lack of variation in the individual ones of the ‘n’ successive values; and if the output value is less than the threshold value, generating an alert to provide a user with an indication of the presence of flow blockage in the pipe.

Abstract: The present disclosure relates to a vortex reducer (100) for a bleed flow (104) in an axial turbomachine comprising a rotor disc (113). The vortex reducer may comprise one or more guide channels (122) arrangeable adjacent to a first side (113a) of the rotor disc to at least partially de-swirl the bleed flow. The vortex reducer may further comprise a passage (130) connecting the first side of the rotor disc to a high pressure flow source capable of providing flow (134) to the first side of the rotor disc to mix with the bleed flow on the first side of the rotor disc.

Abstract: 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.

Abstract: A method of determining the orientation of a grain structure of a turbine blade or vane using an optical technique, illuminates a surface with a beam from a light source and then manipulates the relative orientation of the surface, a light beam and detector to determine the relative orientation which provides the peak reflectance of the beam from the surface to the detector. Further surfaces of the component are similarly manipulated and illuminated and the orientation of the grain structure calculated from the determined relative peak reflectance orientations of the surface, first further surface and second further surface. Determination of the grain orientation allows the value of high angle boundaries to be determined. Also disclosed is apparatus suitable for performing the method.

Abstract: A flow directing device for imparting swirl on a fluid includes a flow directing body having an inboard surface and opposed outboard surface. A flow channel is defined in the outboard surface of the flow directing body for conducting fluids flowing through the flow directing body. The flow channel includes a channel floor and a sidewall extending from the channel floor to the outboard surface of the flow directing body. A swirl port extends from the sidewall of the flow channel though the flow directing body to the inboard surface of the flow directing body for mitigating pressure loss when discharging fluid from the flow channel.

Abstract: This invention relates to a superconducting electrical machine, comprising: a superconducting winding at least partially surrounded by a magnetic flux guide, wherein the magnetic flux guide includes a binder loaded with a magnetic material.

Abstract: A turbomaehine 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.

Abstract: A system and method for measuring oil level and quality is provided. The system and method uses an alternating current (AC) to determine oil level, and a lower frequency alternating current, or a direct current (DC), to measure oil quality. The system may comprise a single sensor that is used to measure both oil quality (by providing the lower frequency alternating current or direct current) and oil level (by providing the higher frequency alternating current). Using the lower frequency AC, or DC, enables the resistance of the oil to be determined, which gives an accurate indication of the oil quality.