Patent application number | Description | Published |
20100054945 | Aerofoil - Composite aerofoils for gas turbine engines are commonly provided with a metal protection strip along the leading edge, to prevent erosion of the leading edge in use and to protect against impacts from foreign bodies. A problem with such strips is that they can cause serious damage to other parts of the engine if they become detached from the aerofoil. The invention provides an aerofoil having such a protection strip, characterised in that the protection strip includes one or more weakening features to reduce the ability of the protection member to withstand a compressive force applied along its length. The weakening features encourage the protection member to break up under impact, or if it becomes detached from the aerofoil, so that damage to other parts of the engine is minimised. | 03-04-2010 |
20100259272 | SENSOR ARRANGEMENT - Utilisation of electrostatic sensor elements is known in relation to obtaining images from a surface such as that of a patient with regard to anomalies including carcinomas. Electrostatic sensor elements, by their nature, are susceptible to creating spurious results in terms of their location with respect to the surface of the subject to be viewed. By providing a visual camera within an array of electrostatic sensor elements the electrostatic charge distribution image is provided by the camera. The image can be overlaid and married with the visual image in a proportionate ratio. In such circumstances an improved final image is provided with inherent visual references to allow analysis of the combined rich display image. A visual camera such as a CCD is used as it is substantially of the same size as the electrostatic sensor elements. | 10-14-2010 |
20110000183 | ASSEMBLY PROVIDING CONTAMINANT REMOVAL - An assembly for the removal of contaminants from a contact zone between respective contact surfaces | 01-06-2011 |
20110150372 | BEARING ASSEMBLY - The present invention relates to a bearing assembly ( | 06-23-2011 |
20110217170 | VARIABLE SHAPE ROTOR BLADE - A rotor blade comprising a core blade section; and a trailing edge section, the trailing edge section being attached to the core blade section along a join interface. The trailing edge section comprises a shape memory material which is actuable so as to cause selective deformation of the trailing edge section between a first condition in which a trailing edge of the trailing edge section follows a substantially smooth profile and a second condition in which the trailing edge is perturbed. The direction of the perturbation may be oblique or perpendicular to the direction of flow over the blade in use. The rotor blade may be a fan or propeller for a gas turbine engine. | 09-08-2011 |
20120205835 | APPARATUS FOR FORMING A COMPOSITE COMPONENT | 08-16-2012 |
20120263595 | ANNULUS FILLER SYSTEM - An annulus filler system bridges the gap between two adjacent blades attached to a rim of the rotor disc of a gas turbine engine. The system includes an annulus filler having a lid which extends between the adjacent blades and defines an airflow surface for air being drawn through the engine. The filler also has a support body extending beneath the lid and terminating in an elongate foot which, in use, extends along a groove provided in the rim of the disc. The groove has a neck which prevents withdrawal of the foot through the neck in a radially outward direction of the disc. The system further includes a sleeve which, after installation of the filler, is slidably locatable into a gap between the foot and sides of the groove. | 10-18-2012 |
20120263596 | ANNULUS FILLER SYSTEM - An annulus filler system bridges the gap between two adjacent blades attached to a rim of the rotor disc of a gas turbine engine. The system includes an annulus filler having a lid which extends between the adjacent blades and defines an airflow surface for air being drawn through the engine. The filler also has a support body extending beneath the lid and terminating in an elongate foot which, in use, extends along a groove provided in the rim of the disc. The groove has a neck which prevents withdrawal of the foot through the neck in a radially outward direction of the disc. The system further includes a sleeve which, after installation of the filler, is slidably locatable into a gap between the foot and sides of the groove. | 10-18-2012 |
20120328365 | JOINT ASSEMBLY - A joint assembly includes a first component with a flange containing a plurality of spaced through-holes; a second component with a joining portion having an end surface which faces the flange and containing a plurality of spaced elongate cavities; and a plurality of fixation devices. Each cavity extends into the joining portion from the end surface in alignment with one of the through-holes. Each fixation device includes: a bolt which extends through a respective through-hole and the corresponding cavity, and includes a nut which is embedded within the joining portion at the corresponding cavity to receive the bolt such that on tightening the nut and bolt a clamping force is exerted across the flange and the end surface to join the first and second components together. Under axial loads less than that causing bolt failure, each fixation device is deformable to remove the clamping force. | 12-27-2012 |
20130026147 | METHOD OF TREATING AN AEROFOIL - A method of imparting deep compressive residual stress to an aerofoil, the method involves determining a stress map for the aerofoil for stress generated by Foreign Object (FOD) impact, a stress map for the aerofoil of high cycle fatigue, a stress map for the aerofoil of low cycle fatigue and determining a combined stress map by combining the stress map of FOD impact, the stress map of high cycle fatigue and the stress map of low cycle fatigue. A zone is then defined on the aerofoil from the combined stress map for receiving the deep residual compressive stress, and compressive residual stress imparted to the defined zone. | 01-31-2013 |