Abstract: Some techniques are described herein for a setup component of a controller to add accessories to a new ecosystem (e.g., a grouping of one or more accessories and one or more controllers and/or a grouping of one or more accessories to an application) that are already added to another ecosystem. Such techniques can include the setup component maintaining a list of accessories for which the setup component has added to the other ecosystem. Using the list, the setup component adds the accessories in the list to the new ecosystem through communications with the accessories and an application corresponding to the new ecosystem.

Abstract: Some techniques are described herein for initially setting up an accessory with a controller. Such techniques have a setup component of a controller establish a relationship with the accessory and facilitate establishment of relationships between applications of the controller and the accessory. In some examples, the setup component causes an accessory management credential to be installed on the accessory so that the accessory can be configured by the setup component to establish a relationship with an application in communication with the setup component. In some examples, such communication between the application and the accessory occurs without further interactions with the setup component.

Abstract: A method of manufacturing a hollow aerofoil component for a gas turbine engine includes using a capping panel to cover a pocket in a pocketed aerofoil body. An activation material is placed between the capping panel and the pocketed aerofoil body, and the temperature of the assembly is raised to a bonding temperature. The capping panel and pocketed aerofoil assembly are thereby joined together using activated diffusion bonding to form the hollow aerofoil component.

Abstract: An alloy mix suitable for the repair of nickel-based alloy components is disclosed. The alloy mix contains a mixture of two alloy powders. The constituents of the first powder, in percentages by weight are:______________________________________ Al 2-3 Co 9-11 Cr 8-10 Fe 0-1.8 Hf 1.0-1.5 Ta 1.-1.5 Ti 1.25-1.75 W 6-8 B 2.8-3.4 Y 0.001-0.02 Ni Remainder ______________________________________and the constituents of the second powder, in percentages by weight, are: ______________________________________ C .13-.17 Al 5.25-5.75 B 0.01-0.02 Co 9.0-11.0 Cr 8-10 Hf 1.3-1.7 Ta 2.25-2.75 Ti 1.25-1.75 W 9.5-10.5 Zr 0.03-0.

Abstract: A rotating or moving metal component such as a blade for a gas turbine engine is made from a composite bar of titanium alloy with the sides of the bar having a surface layer of e.g. nickel which is less likely to ignite in particle form or by frictional heating when present in oxygen or air. After the surface layer has been bonded to the titanium alloy it is then parted to provide sections which extend perpendicularly to the plane of the surface layers. Each parted section may then be machined into a blade with the nickel portion forming the tip of the blade. Alternatively, each parted section may itself form the blade tip by attachment on its titanium alloy side to a blade stem.

Abstract: A nickel based alloy is devised, for the purpose of using it as a brazing foil to join parts of a nickel based superalloy component together to make a whole, or for using it as a powder bound by an acrylic or water based binder, to build up damaged surfaces of a nickel based superalloy. In each case, the finished product has the mechanical strength characteristics of the base metal.

Abstract: Superalloy components which have defects such as pits, machining errors or any other `lack of metal` condition can be repaired using a braze stabilized sinter process. The invention includes filling the defect with a mixture of base super-alloy powder mixed with a low temperature braze alloy. A higher temperature alloy is overlayed and the component subjected to a vacuum furnace cycle that includes a dwell between the melting points of the two braze alloys. This dwell allows the lower temperature alloy to melt and isothermally solidify by the process of diffusion. This effectively `stabilizes` the sinter which is porous. On further heating, the higher temperature braze alloy melts and flows into the interstices of the sinter, forming a pore-free solid mass. The higher temperature braze alloy can also be diffused by holding at elevated temperatures. This increases the remelt temperature of the repair should further thermal cycling be required.