Patent application number | Description | Published |
20100014968 | Centering device - A gas turbine engine ( | 01-21-2010 |
20100158421 | Shaft stabiliser - A load transfer arrangement is provided to act as a stabiliser for utilisation in centring rotational instabilities which may occur in rotor devices such as those within a gas turbine engine. By providing a fixed screw thread path which comprises a groove having channels and having constrictions and which define clearance crowns an acceptable eccentricity range it is possible to slow screw thread driving motion and therefore load transfer only to the positions where the rotational eccentricity enters tapers leading to the constrictions. In such circumstances an orbit thread is then progressively brought into confinement and continuous engagement with a fixed screw thread defined by crowns of channels of the fixed screw thread path defined by the continuous groove through the channels. In such circumstances wide eccentricity is allowed initially but as rotational speed reduces greater and more continuous driving motions are provided whilst avoiding excessive loading during early stage operation. High loads on final rundown contact are controlled by a diaphragm mount, the whole serving to restore the support stiffness of the rotor post fusing. | 06-24-2010 |
20100278639 | CONTROL MECHANISM - A control mechanism is provided for moving at least two components of a gas turbine engine. The control mechanism comprises a moveable actuation rod. The control mechanism further comprises a first linkage arrangement which includes a first bell crank and which operatively connects the actuation rod to a first component of the gas turbine engine. Movement of the actuation rod produces an output motion of the first bell crank which in turn drives movement of the first component. The control mechanism further comprises a second linkage arrangement which includes a second bell crank and which operatively connects the actuation rod to a second component of the gas turbine engine. Movement of the actuation rod produces an output motion of the second bell crank which in turn drives movement of the second component. The first linkage arrangement and the second linkage arrangement are configured so that over a predetermined range of movement of the actuation rod the first component is moved by the first bell crank while the second component is not moved by the second bell crank. | 11-04-2010 |
20100284788 | DUCT WALL FOR A FAN OF A GAS TURBINE ENGINE - A duct wall of a fan casing of a gas turbine engine comprises an intake section and a containment casing, which are interconnected by bolts at flanges. An acoustic flutter damper is provided between the flanges to reduce or eliminate flutter arising in blades of the fan at certain important operating conditions. The damper provides flexibility at the connection between the intake section and the containment casing so that, in the event of detachment of a blade or a bladed fragment, the resulting deflection wave in the containment casing can be accommodated by displacement and/or deformation of the acoustic flutter damper, reducing the risk that the bolts will shear to allow the intake section and the containment casing to become detached from each other. The acoustic flutter damper may comprise a circumferential array of separate segments. | 11-11-2010 |
20100284790 | DUCT WALL FOR A FAN OF A GAS TURBINE ENGINE - A gas turbine engine fan casing duct wall comprises an intake section and a containment casing, provided respectively with flanges. An acoustic flutter damper is secured between the flanges. The acoustic flutter damper has a skin accommodating an internal structure that dampens fan blade flutter. The skin is secured to the flanges at separate locations. In normal operation of the engine, the internal structure is sufficiently robust to support loads transmitted through the acoustic flutter damper between the intake section and the containment casing. If a blade or blade fragment detaches, the resulting deflection wave in the containment case ruptures the internal structure, and the load path between the intake section and the containment casing passes along the skin, which consequently maintains the connection between the intake duct and the containment casing, while permitting substantial radial deflection of the containment casing relative to the intake section. | 11-11-2010 |
20120091265 | SUPPORT STRUCTURE - A support structure is provided for attaching a gas turbine engine to a pylon. The gas turbine engine has an engine casing surrounding an engine core, and the pylon has first and second attachment positions, the second attachment position being forward of the first attachment position relative to the working gas flow direction through the engine. The support structure has three elongate members joined to form a triangular frame encircling the engine casing. A first vertex of the triangular frame attaches to the pylon via a first attachment arrangement at the first attachment position. Two thrust struts respectively extend from the other two vertices of the triangular frame and attach to the pylon via a second attachment arrangement at the second attachment position. Three engine connection formations extend from the respective vertices of the triangular frame to positions on the engine casing to connect the support structure to the engine casing. | 04-19-2012 |
20120315141 | FLOW MIXER - An annular flow mixer is provided for use in a gas turbine engine. A core generator of the engine provides an annular duct for the flow of working gas, which exhausts from the duct through the flow mixer. The flow mixer has a plurality of circumferentially spaced exhaust chutes from which the working gas exits in respective exhaust plumes. The exhaust chutes are configured such that, at the discharge end of the flow mixer, a radially outer portion of each exhaust chute radially overlaps with a radially inner portion of at least one adjacent exhaust chute. | 12-13-2012 |
20120321470 | MOUNTING SYSTEM - A mounting system for mounting a blade to a rotor body includes a pitch control mechanism including an anchor and a pitch change rod extending radially outwardly from the anchor to join to a base of the blade. The anchor and the rod are rotatable about the longitudinal axis of the rod to vary the blade pitch. The pitch control mechanism further includes a torque-transmitting formation between the blade and the anchor such that pitch-varying torque can be transmitted to the blade through the torque-transmitting formation while allowing relative radial movement between the blade and the anchor. The system includes a primary bearing formation, which transmits blade centrifugal loads to the rotor body while accommodating variation of the blade pitch, and secondary bearing formation, which transmits pitch change mechanism centrifugal loads to the rotor body while accommodating rotation of the anchor and the rod during variation of the blade pitch. | 12-20-2012 |
20130000313 | HYDRAULIC FLUID TRANSFER COUPLING - A hydraulic fluid transfer coupling has a stator, a first coaxial rotor, and a second coaxial rotor. The first rotor is radially inwards of the stator, the second rotor is radially outwards of the stator, at least part of the first rotor axially overlapping with the stator, and at least part of the second rotor axially overlapping with the stator. The first rotor carries one or more first rotating fluid lines, and the second rotor carries one or more second rotating fluid lines. The stator carries one or more first static fluid lines and second static fluid lines. Each pair of a first rotating fluid line and the corresponding first static fluid line are fluidly coupled and each pair of a second rotating fluid line and the corresponding second static fluid line are fluidly coupled. Hydraulic fluid is transferable between each static fluid line and the corresponding rotating fluid line. | 01-03-2013 |
Patent application number | Description | Published |
20080245925 | Aircraft configuration - Some aircraft configurations have an engine arrangement comprising engines as part of an aft fuselage. In order to accommodate such engine arrangement positions, wings are rearwardly displaced compared to other aircraft configurations for balance across the fuselage. By creating empennage functions utilising the nacelle of engines as well as flaps to create rudder and elevator functions, it is possible to accommodate larger engine sizes more suitable for noise control with a reduced necessity for designed rearward movement of wings. | 10-09-2008 |
20080290215 | Hollow aerofoil and a method of manufacturing a hollow aerofoil - A hollow aerofoil ( | 11-27-2008 |
20100142871 | Bearing arrangement - In order to accommodate loading in a number of situations such as with regard to thrusts in a gas turbine engine it is known to provide thrust bearings. These thrust bearings can be large and may be difficult to accommodate. By providing a duplex or multiplex thrust bearing which may be of increased axial length but reduced radial width easier accommodation may be achieved. By providing a thrust element | 06-10-2010 |
20100251688 | CONTAINMENT SYSTEM FOR A GAS TURBINE ENGINE - A containment system for a gas turbine engine comprises a force absorbing arrangement for absorbing the force exerted thereon by an ejected portion of a failed component of the engine. The force absorbing arrangement circumferentially surrounds a major proportion of the axial length of the engine. | 10-07-2010 |
20120248707 | ASSEMBLY COMPRISING A ROTATABLE COMPONENT - An assembly, for example in a gas turbine engine, includes a rotatable component supported by a bearing in a support structure. A sealing arrangement includes a non-rotating sealing ring which makes sealing contact with sealing features on the rotatable component. The non-rotating sealing ring is radially displaceable with respect to the support structure by means of ribs which engage axially facing support faces of the support structure. The non-rotating sealing ring is radially located by an outer, non-rotating, race of the bearing, by means of a locating surface on a locating body of the non-rotating sealing ring. As a result of this arrangement, the running clearance at the sealing arrangement can be maintained, despite radial displacement of the rotatable component with respect to the support structure, and despite thermal and mechanical deflections of the support structure. | 10-04-2012 |