Class / Patent application number | Description | Number of patent applications / Date published |
416002000 | HAVING FRANGIBLE OR FUSIBLE PART OR CONNECTION | 12 |
20100054937 | BLADE - A fan blade for a gas turbine engine has an aerofoil part and a root part. The root part includes a root former; the root former | 03-04-2010 |
20100054938 | BLADE AND A METHOD FOR MAKING A BLADE - International regulations for aerofoils within gas turbine engines require the safe containment of a released aerofoil. The blade fragments must be contained within an engine casing. Smaller fragments will generally be easier to contain within the casing and therefore reduce the weight of that casing. However introducing lines of weakness may result in cavities and holes which are subject to moisture ingress and problems associated therewith. By providing a root section which incorporates a core having shear surfaces, blades can be designed which in normal use are subject to compressive loads and remain operational, but when subject to impact loads or bending forces create tension forces which cause fragmentation along the shear surfaces after initial energy losses by slippage. By providing the shear surfaces in cores their location is encapsulated avoiding problems with moisture ingress. | 03-04-2010 |
20110085906 | FAN RETENTION SHAFT - A fan retention shaft is provided for retaining a fan within a gas turbine engine in the event of fan shaft failure. The fan retention shaft has a first shaft which in use extends from the engine and a second shaft to which in use the fan is attached, the second shaft being coaxial with the first shaft and the first and second shafts defining an annular passage between them. An energy absorbing medium is disposed within the annular passage. The fan retention shaft has a retaining formation for preventing the first shaft and the second shaft from moving axially with respect to one another. The retaining formation is configured to release the first shaft and the second shaft from their relative axial positions when a threshold axial load is applied to the fan retention shaft. The energy absorbing medium is arranged to absorb kinetic energy from the second shaft as the second shaft moves axially with respect to the first shaft. | 04-14-2011 |
20120020789 | TURBINE WHEEL HAVING DE-TUNED BLADES AND INCLUDING A DAMPER DEVICE - A turbine wheel including: a plurality of first and second blades, at least one of the first blades being adjacent to at least one of the second blades; a disk presenting an axis of rotation and a periphery having the blades mounted thereat, each of the blades including a head solid with a root engaged in a housing that opens to the periphery of the disk, each of the blades including a keying mechanism including a respective shelf arranged between the head and the root of the blade, the shelves of the first blades presenting an azimuth length different from the azimuth length of the shelves of the second blades; and a damper device arranged at least between the adjacent blades, the damper device being arranged between the shelves of the blades and the periphery of the disk. | 01-26-2012 |
20130052012 | METALLIC FAN BLADE PLATFORM - A platform is provided for use between adjacent fan blades joined to a rotor disk to provide an inner flowpath boundary. The platform includes: a metallic arcuate body with opposed forward and aft ends and opposed lateral edges; and a pair of frangible wings that extend from the lateral edges laterally and radially beyond the body. | 02-28-2013 |
20140064964 | METALLIC FOAM MATERIAL - Tip rub in gas turbine engines is a well-known phenomenon, and may lead to increased tip clearances, with consequent detrimental effects on the engine's performance and blade flutter margins. Heavy or repeated rubbing may cause blade tip over temperature leading to cracking and fatigue failure. The invention provides a tip for a gas turbine engine rotor blade, which under contact with the casing surface interacts with the casing surface so as to reduce the contact force and thereby reduce the energy transferred to the blade. The tip may be designed to ablate under contact with the casing surface, or to cut or abrade the casing surface, or to crush or compress of deflect under contact with the casing surface. In a preferred embodiment, the tip comprises fibre-reinforced metallic foam material. | 03-06-2014 |
20140140845 | AN AXIAL TURBINE FOR A TIDAL POWER PLANT AND A METHOD FOR THE ASSEMBLY THEREOF - An axial turbine for a tidal power plant, including a hub with a rotor blade holder and a rotor blade with a blade fastening section having a longitudinal axis including a fastening stub, a radial fixing and an anti-rotation element. The fastening stub includes a contact surface supported against a complementarily shaped fixing surface on the rotor blade holder whose envelope is rotationally symmetrical to the longitudinal axis. The radial fixing secures the rotor blade fastening section against a withdrawal movement relative to the rotor blade holder in the direction of the longitudinal axis. The anti-rotation element is connected with a complementarily shaped rotational stop on the rotor blade holder with an effective area of the anti-rotation element being a component of the blade fastening section arranged separate from the radial fixing, and the radial fixing comprises fastening means that has a predetermined breaking point of the blade fastening section. | 05-22-2014 |
20150330246 | TEST BLADE - A test blade for use in a blade-release test in which the blade is mounted on a rotatable hub and at least a portion of the blade is released therefrom by the action of a controlled explosion. The blade has a root portion for mounting on said rotatable hub and the root portion comprises a radially inner surface having a channel extending at least partly along or proximal the camber line. The channel is for receiving at least one explosive charge and at least one detonator which may be contained within a charge carrier. | 11-19-2015 |
20160176509 | Propeller blade for an aircraft engine | 06-23-2016 |
20160177731 | BLADE | 06-23-2016 |
20160177779 | BLADE | 06-23-2016 |
20160201503 | FRANGIBLE AIRFOIL | 07-14-2016 |