| 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 |
