| Patent application number | Description | Published |
|---|
| 20080292451 | Securing arrangement - A securing arrangement | 11-27-2008 |
| 20090097963 | Vane and a Vane assembly for a gas turbine engine - A fan outlet guide vane for a gas turbine engine comprises a generally radially-extending internal structural member and at least one surface member securable in use to the internal structural member so as to define an aerofoil. The gas turbine engine includes an annular first structure and an annular second structure, the second structure being radially outward of the first structure so as to define a duct between them, and in use the internal structural member of the vane is secured between the first structure and the second structure. In a preferred embodiment, the surface member or surface members are secured only to the internal structural member, and not to the first or second structures. | 04-16-2009 |
| 20090214327 | Fan track liner assembly - A fan track liner within a rotor blade assembly | 08-27-2009 |
| 20090269197 | Fan Assembly - A fan assembly for a gas turbine, the assembly comprising: a fan surrounded by a fan casing; a resilient, radially flexible containment material wrapped around the outside of the fan casing for containing a fan blade which has breached the casing during a fan blade-off event, and a retaining cable arrangement for resisting separation of a first portion of the casing from a second portion of the casing as a result of said breach occurring between the first and second portion; wherein the cable arrangement comprises: a retaining cable on the outside of the containment material, secured between the first and second portion of the casing, the retaining cable being sufficiently radially compliant for radial deflection to accommodate radial flexing of the containment material caused by impact of said fan blade inbetween the first and second portion; and a locking arrangement operable to subsequently lock the retaining cable between the front and rear portions of the casing whereby separation of the front and rear portions is resisted by tension in the locked cable. | 10-29-2009 |
| 20100189552 | Fan assembly - A fan assembly | 07-29-2010 |
| 20100266384 | GAS TURBINE ENGINE CASING ASSEMBLY - High bypass ratio turbofan propulsion engines are designed with a two-step approach to surviving foreign object damage to the fan assembly. First, a containment system encircling the fan assembly to capture any part of a released fan blade in the event of damage occurring, and two in order to cope with the vibrations resulting from a rotating unbalanced fan assembly the support structure for the bearing of the rotating assembly is constructed with frangible parts to introduce a snubber gap to permit the rotating, unbalanced fan assembly and bearing to orbit thereby to reduce the resulting vibrations. However, in the case of very wide chord fan assemblies, the largest acceptable snubber gap is insufficient to reduce the induced vibrations. The present solution is to incorporate into the containment system, and behind a fan track liner encircling the fan blades, at least one severance member having a cutting edge that will impact the tips of the blades of an orbiting fan assembly thereby to trim the mass distribution of the fan blades in order to reduce the vibrations caused by the out of balance forces. | 10-21-2010 |
| 20110146299 | ANNULUS FILLER ASSEMBLY FOR A ROTOR OF A TURBOMACHINE - An annulus filler assembly for a rotor of a turbomachine, the assembly comprising: an annulus lid ( | 06-23-2011 |
| Patent application number | Description | Published |
|---|
| 20090269203 | AEROENGINE FAN ASSEMBLY - A fan assembly of a gas turbine engine, the fan assembly includes an array of radially extending blades defining gaps therebetween and an annulus filler located within at least one gap. The annulus filler includes at least two individual bodies arranged circumferentially adjacent one another with at least one adjacent a blade, one of the bodies includes a flexible wall arranged to centrifuge outwardly against the other body thereby urging both bodies against the blades and securing them during engine operation. | 10-29-2009 |
| 20100290910 | ANNULUS FILLER - An annulus filler for mounting to a rotor disc of a gas turbine engine bridges the gap between adjacent disc blades. The annulus filler has a lid defining part of an airflow surface for air drawn through the engine; a separate support connectable to the lid and to the rotor disc with an engagement portion of the support extending radially past a substantially adjacent region of the lid; and a retainer configured to interconnect the lid and the support by engaging each engagement portion of the support and adjacent regions of the lid, the retainer defining another part of the airflow surface. The annulus filler can be configured to allow mounting to the rotor disc, where the support is connected to the rotor disc without the lid, and then the lid is mounted to the support such that each engagement portion remains visible from the lid's radially outermost side. | 11-18-2010 |
| 20100322772 | ANNULUS FILLER FOR A GAS TURBINE ENGINE - An annulus filler for mounting to a rotor disc of a gas turbine engine is provided to bridge the gap between adjacent blades. A first part is connectable to the rotor disc between adjacent blades. There is a separate second part that engages with the first part after connecting the rotor blades to the rotor disc. When installed, the filler is spaced from each blade by a respective clearance gap (G), and an operational configuration in which it contacts each of said blades. Engagement of the second part with the first part is effective to urge the first part from said installation configuration to said operational configuration and thus into blade contact. The first part may have a mounting region for connection to the rotor disc and allow, in said first step of said procedure, the mounting region to remain visible from a radially outer viewpoint. | 12-23-2010 |
| 20110038731 | ROTOR ASSEMBLY FOR A GAS TURBINE - A rotor assembly, for a gas turbine, has a plurality of rotor discs interconnected by an axially extending rim. The outside of the rim has a circumferential array of dovetail slots and the underside of the rim has a circumferential channel which extends radially part way into the slots, the respective discs thus being interconnected axially across the channel by an array of circumferentially spaced connecting portions. There is an array of blades, each blade having a blade root secured in a respective one of the dovetail slots. | 02-17-2011 |
