Patent application number | Description | Published |
20090004303 | Perfume Compositions - Perfume ingredients and essential oils in synergistic combinations improve well-being by down-regulating arousal. This could lead to enhanced quality of life and reduced stress. The perfume compositions of the invention comprise one or more materials from each of the following groups: Group A: the essential oils lavender, lavandin, bergamot, chamomile, clary sage; Group B: 2-phenoxyethanol, 1-(2,3,8,8-tetramethyl-1,2,3,4,5,6,7,8-octahydronaphthalen-2-yl)ethanone, benzophenone, cyclopentadecanolide, alpha-ionone, beta-ionone, para-methylacetophenone, [4-isopropylcyclohexyl]methanol. The ratio of the weight percentage based on the composition of group A materials to Group B materials lies within the range 1:9 to 9:1. | 01-01-2009 |
20110130323 | Fragrance Compositions - A fragrance composition and use thereof by inhalation to promote activated, pleasant moods. The fragrance composition comprises at least 75% by weight of perfume materials including at least 10% by weight of at least three specific materials from a group identified as Group IMP and optionally up to 90% of specific materials selected from groups identified as HMR, HMI, HMP, RMP and GEN, the amounts of materials from said Groups falling within specified relationships. | 06-02-2011 |
20140194338 | Fragrance Compositions - A fragrance composition and use thereof by inhalation to promote activated, pleasant moods. The fragrance composition comprises at least 75% by weight of perfume materials including at least 10% by weight of at least three specific materials from a group identified as Group IMP and optionally up to 90% of specific materials selected from groups identified as HMR, HMI, HMP, RMP and GEN, the amounts of materials from said Groups falling within specified relationships. | 07-10-2014 |
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 |
Patent application number | Description | Published |
20100047541 | Composite material repair - A repaired composite material component | 02-25-2010 |
20100271291 | SENSOR ARRANGEMENT - Utilisation of electrostatic sensor elements in an array to provide an electrostatic image is known. Problems can arise with respect to cross talk between electrostatic sensor elements and as a result of external electrical sources. By providing a differential input amplifier and taking output signals from adjacent or adjoining sensor elements to providing a differential signal it is possible to improve images. Furthermore, the differential input amplifier incorporates decoupling devices such as capacitors to reduce noise within the output and input signals and the aspect ratio of the sensor in terms of depth to width can also aid reduction in noise levels. | 10-28-2010 |
20100278476 | COMPONENT MONITORING ARRANGEMENT - Fibre substrates act as a conduit for light along which response signals are transmitted to a controller in the form of an electronic device associated with a component. The processed signals are stored in a local memory to provide a component history and a prediction of future performance and life. Service and repair history may be added to the component device memory to enable a complete history to be stored with the component. A controller may transmit data to an external controller or display through typically a wireless connection. Power to the component electronics may be provided by an induction loop or transformer. | 11-04-2010 |
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 |
20110150378 | BEARING ASSEMBLY - The present invention relates to a bearing assembly ( | 06-23-2011 |
20120060594 | STRAIN INDICATOR FOR A GAS TURBINE ENGINE COMPONENT - A component for use in a gas turbine engine comprises an indicator operable to provide a visual indication when strain over a threshold value has been experienced by the component by transitioning from a rest state to an indication state on occurrence of strain above the threshold value. | 03-15-2012 |
20120224949 | TURBOMACHINE CASING ASSEMBLY - A turbomachine casing assembly including a first casing element locatable radially outward of one or more rotating aerofoil elements of a turbomachine, a second casing element located radially distal to the first casing element is provided. A void is provided between a radially proximal face of the first casing element and a radially proximal face of the second casing element, at the first end of the first casing element. The first end of the first casing element is located against a corresponding first end of the second casing element by an energy absorbing element, with the first casing element; including a cantilever. The cantilever is arranged in a region extending along the first casing element from the first end; and having a pivot axis at a mid portion thereof. | 09-06-2012 |
20130064661 | AEROFOIL ASSEMBLY - This invention relates to a stator aerofoil for a gas turbine engine, comprising: a body portion; at least one panel which forms at least part of one of either the pressure or section surface of the aerofoil; at least one internal chamber which is bounded by the body portion and panel; and, at least one elastomeric component within the at least one internal chamber, wherein the elastomeric component at least partially defines a cell within the internal chamber, wherein the cell is in fluid communication with the exterior of the aerofoil. | 03-14-2013 |
20130074572 | MANDREL FOR FORMING A COMPONENT - A mandrel includes a support structure; main sectors carried by the support structure and each having a main forming surface; and intermediate sectors carried by the support structure and each having an intermediate forming surface. The main sectors and intermediate sectors are alternately arranged around the axis. The main sectors are moveable relative to the support structure between a radially inner main retracted position, and a radially outer main forming position. The intermediate sectors are moveable relative to the support structure between a radially inner intermediate retracted position, and a radially outer intermediate forming position. The mandrel further includes drive means for moving the main sectors and intermediate sectors from their respective retracted positions to their respective forming positions. The drive means is configured such that each main sector reaches its main forming position before the adjacent intermediate sectors reach their respective intermediate forming positions. | 03-28-2013 |
20140026583 | FLUID MANAGEMENT APPARATUS AND METHOD - A fluid management apparatus and method, the apparatus including: a fluid conduit for the passage of a dispersion containing particulate matter; a laser arranged to provide laser light inside the fluid conduit; wherein, in use, the laser light heats the particulate matter sufficiently to generate incandescence; one or more sensors for detecting the incandescence of the particulate matter so as to determine a characteristic of the dispersion; and an electromagnetic wave generator operable to provide electromagnetic waves inside the fluid conduit at a position downstream of the laser light so as to vaporise at least a portion of the dispersion. | 01-30-2014 |