Abstract: A method (400) for coating a tip (106) of an aerofoil (100) is provided. The method (400) includes depositing a layer of nickel-based gamma/gamma prime chemistry (112) on the tip (106) of the aerofoil (100). The method (400) further includes depositing plurality of abrasive particles (114) on the layer of nickel-based gamma/gamma prime chemistry (112) to form a coating matrix (116). The method (400) further includes heating the tip (106) of the aerofoil (100) at a predetermined temperature in order to perform heat treatment of the coating matrix (116) and increase the strength of the coating (110) on the tip (106) of the aerofoil (100).

Abstract: Systems and methods are disclosed for secure online transaction. The method includes receiving a plurality of transaction data associated with an authenticated registered user from a point of sale (POS) terminal. The plurality of transaction data is processed to identify sensitive information. The sensitive information is substituted with cryptographically generated tokens at a reader head of the POS terminal, wherein the tokens are randomly generated numbers, randomly generated character sequences, pseudorandom numbers, or a combination thereof. The cryptographically generated tokens are encrypted, via an encryption protocol, to generate encrypted tokens at the reader head of the POS terminal. The encrypted tokens are transmitted to one or more processing servers for data aggregation and payment settlement.

Abstract: Systems and methods are disclosed for data aggregation and efficient routing of the aggregated data for the settlement of payments. The method includes receiving, in real-time, transactions associated with an account of a registered user. The outstanding amount associated with transactions is aggregated based on a first preset time period. The payments for the aggregated outstanding amount are transmitted from a settlement account to an account of a merchant based on the first preset time period and/or a pre-determined total outstanding amount threshold. The transmitted payments are aggregated based on a second preset time period. The amount equivalent to the aggregated transmitted payments is transmitted from the account associated with the registered user to the settlement account based on the second preset time period. A user interface is then generated in devices of the registered user and merchant.

Abstract: Systems and methods are disclosed for data aggregation and efficient routing of the aggregated data for the settlement of payments. The method includes receiving, in real-time, transactions associated with an account of a registered user. The outstanding amount associated with transactions is aggregated based on a first preset time period. The payments for the aggregated outstanding amount are transmitted from a settlement account to an account of a merchant based on the first preset time period and/or a pre-determined total outstanding amount threshold. The transmitted payments are aggregated based on a second preset time period. The amount equivalent to the aggregated transmitted payments is transmitted from the account associated with the registered user to the settlement account based on the second preset time period. A user interface is then generated in devices of the registered user and merchant.

Abstract: A method of manufacturing a coated turbine vane (34) comprises manufacturing a turbine vane (34) having a platform (44) and an aerofoil (42) extending from the platform (44), a curved transition (60) connects the platform (44) to the aerofoil (42) and a recess (64) is provided in the curved transition (60) from the platform (44) to the aerofoil (42). A bond coating (70) is deposited on the platform (44), the aerofoil (42), the curved transition (60) and the recess (64). A ceramic thermal barrier coating (72) is deposited on the platform (44), the recess (64) and the curved transition (60) by plasma spraying. The recess (64) reduces the size of the step due to the ceramic thermal barrier coating (72) and hence improves the aerodynamics of the turbine vane (34).

Abstract: A gas turbine engine component includes a rotor blade having a squealer tip comprising a projecting lip, the rotor blade further having a raised rim running along both edges of each projecting kip of the squealer tip, and an abrasive coating formed of hard particles embedded in a retaining matrix covering a tip region of the rotor blade within an area bounded by the raised rim. The raised rim has a height of between 50% and 75% of a mean diameter of the hard particles.

Abstract: A method of manufacturing a coated turbine vane (34) comprises manufacturing a turbine vane (34) having a platform (44) and an aerofoil (42) extending from the platform (44), a curved transition (60) connects the platform (44) to the aerofoil (42) and a recess (64) is provided in the curved transition (60) from the platform (44) to the aerofoil (42). A bond coating (70) is deposited on the platform (44), the aerofoil (42), the curved transition (60) and the recess (64). A ceramic thermal barrier coating (72) is deposited on the platform (44), the recess (64) and the curved transition (60) by plasma spraying. The recess (64) reduces the size of the step due to the ceramic thermal barrier coating (72) and hence improves the aerodynamics of the turbine vane (34).

Abstract: A method of inspecting an object, the method comprising: receiving a first image of a first part of a first surface of the object from a camera arrangement; controlling relative movement between the camera arrangement and the object through a predetermined distance; receiving a second image of a second part of the first surface of the object from the camera arrangement, the second part being different to the first part; generating a third image using at least the first image and the second image; and determining a parameter associated with an abrasive surface coating on the object using the third image.

Abstract: A method of inspecting an object, the method comprising: receiving a first image of a first part of a first surface of the object from a camera arrangement; controlling relative movement between the camera arrangement and the object through a predetermined distance; receiving a second image of a second part of the first surface of the object from the camera arrangement, the second part being different to the first part; generating a third image using at least the first image and the second image; and determining a parameter associated with an abrasive surface coating on the object using the third image.

Abstract: The invention is an extendable, retractable and swiveling arm of the Cobra Hitch that can easily attaches a vehicle to its trailer, without the stressful task of lining up the tow ball with the trailer tongue. The arm is extendable and retractable, swivels left and right and can be manual or remote control operated. An improved hitch is provided for connecting a truck and trailer through a hitch arm which is adjustable in length and, and retractable once engaged to bring the truck and trailer into a position suitable for towing.

Abstract: A gas turbine engine component having a raised rim located along one or more edges of a tip region of the component, and an abrasive coating formed of hard particles embedded in a retaining matrix covering the tip region within an area bounded by the raised rim.

Abstract: An arrangement for vapor phase coating an internal surface of hollow articles comprises a part plate, at least one spud site and at least one manifold. The part plate defines a portion of a chamber for supplying a vapor coating. Each spud site has a tube and a first moldable sealant is arranged around the tube. Each manifold has at least one supply tube extending from the manifold to supply vapor into a respective hollow article. Each manifold has a feed tube extending from the manifold to supply vapor into the manifold. The tube of each spud site is inserted into the feed tube of the respective manifold and an end of the feed tube remote from the manifold locates in the first moldable sealant. A second moldable sealant is arranged around the at least one supply tube of the respective manifold and between the respective manifold and hollow article.

Abstract: The present invention provides an agitator for agitating a liquid (e.g. an electrolyte solution) containing particles (e.g. abrasive particles) within a tank. The agitator comprises an agitator body having an upper surface and a lower surface with at least one aperture extending through the agitator body. There is a one-way valve for allowing liquid flow through at least one aperture from the upper surface to the lower surface and for blocking liquid flow through at least one aperture from the lower surface to the upper surface.

Abstract: The present invention provides a blade tip for a rotary blade, the blade tip comprising a first portion and a radially-recessed second portion. A radially outermost surface of the first portion comprises a first abrasive coating e.g. a composite material comprising cubic boron nitride embedded in a matrix of nickel alloy. A radially outermost surface of the second portion comprises a second abrasive coating which has a greater resistance to oxidation than the first abrasive coating. The increased oxidation resistance of the second abrasive coating is achieved by providing a radially outer protective layer and/or using a material having a greater inherent oxidation resistance.

Abstract: An erosion testing assembly adapted to test an abradable surface of a component, the testing assembly including: a shroud attachable to the component; the shroud being adapted to receive an erosion gun. The present disclosure also relates to a method of testing an abradable surface of a component, wherein the method includes: attaching a shroud to the component; connecting an erosion gun to the shroud; and testing the abradable surface with the erosion gun. The present disclosure may also relate to a method of testing an abradable surface of a component, wherein the method includes: using the component; and testing a portion of the abradable surface with an erosion gun after use of the component.

Abstract: A seal is provided between first and second relatively movable members. The seal comprises a liner attached to the first relatively movable member which liner is abraded by the second relatively movable member. The abradable liner comprises a metallic, open porous structure formed by fusing a metallic feedstock with an energy beam to build up sequential deposits of the fused feedstock.

Abstract: A method of producing an integral self supporting coating test piece from particulate material including the steps of (i) producing a reusable mould having a depression which conforms to the desired shape and volume of said coating test piece, the reusable mould including silicone rubber, (ii) roughening the surface of the reusable mould, (iii) heat treating the reusable mould, (iv) thermally spraying particulate material into the depression in the reusable, mould, and (v) removing the reusable mould from the solidified coating test piece.

Abstract: An apparatus (10) to test the adhesion strength and/or cohesive strength of a coating (12) comprises a first member (14) having an aperture (16) and a second member (18) locatable in the aperture (16) in the first member (14). A temperature sensor (20) is arranged to measure the temperature of the first member (14). A third member (22) and a fourth member (24) are mounted on the first member (14). The third member (22) has a first strain gauge (26) to measure the strain in a first direction and the fourth member (24) has a second strain gauge (28) to measure the strain in a second direction perpendicular to the first direction.

Abstract: A master component is provided for use in checking for any variation in the performance of a gas turbine test facility. The master component replaces a standard component, which is typically a turbine blade, vane or segment in the test facility. The master component is attached to the test facility in the same manner as the standard component. The flow rate through the master component is substantially the same as the flow rate through the standard component for a given inlet and outlet temperature and pressure. The flow through the master component is simpler than the flow through the standard component. This means that the flow through the master component is less likely to vary over time. As such, the master component is more suitable for use in checking for any variation in the performance of a test facility.

Abstract: A master component is provided for use in checking for any variation in the performance of a gas turbine test facility. The master component replaces a standard component, which is typically a turbine blade, vane or segment in the test facility. The master component is attached to the test facility in the same manner as the standard component. The flow rate through the master component is substantially the same as the flow rate through the standard component for a given inlet and outlet temperature and pressure. The flow through the master component is simpler than the flow through the standard component. This means that the flow through the master component is less likely to vary over time. As such, the master component is more suitable for use in checking for any variation in the performance of a test facility.