A method of eliminating dissimilar metal welds has been disclosed. The method includes the steps of providing a first part having a first alloy composition; providing a second part having a second alloy composition different from the first part; connecting a containment structure to the first part; pouring a powder into the containment structure such that the powder is in contact with the first part; positioning a portion of the second part in the containment structure such that the second part compresses the powder between the first and second parts; and performing hot isostatic pressing (HIP) to consolidate the powder and join the first and second parts together.

A field of rotary blades, and more particularly to a method of fabricating a leading edge shield for protecting such a blade. The method includes at least steps of performing initial plastic deformation on at least one sheet from a pressure side sheet and a suction side sheet, using additive fabrication to add a reinforcement with a fiber insert on at least one of the pressure and suction side sheets, closing the pressure and suction side sheets around a core after the initial plastic deformation and after adding the reinforcement, performing subsequent plastic deformation by pressing the pressure and suction side sheets against an outside surface of the core after the sheets have been closed around the core, and extracting the core.

A method of attaching a cladding element to a base element. A first inner side of the cladding element is positioned spaced apart from a second inner side of the base element to define a slot therebetween, and one or more heating elements are located in the slot. A non-oxidizing atmosphere is provided in the slot, and the heating element is energized, to heat at least portions of the cladding element and the base element to a hot working temperature. While at the hot working temperature, the first and second inner sides are engaged with each other, and one or both are moved relative to the other, for plastic deformation of the first and second inner sides, to subject the portions of the cladding element and the base element to shear stresses. The portions are allowed to cool, for recrystallization thereof.

An imaging system using ultraviolet light or a manufacturing apparatus including the imaging system is provided. An imaging system includes an imaging element and a light source, which operates the imaging element with light that is emitted from the light source and reflected or transmitted by an object. A pixel included in the imaging element includes a photoelectric conversion element and a charge holding part. The light source has a function of emitting ultraviolet light to an object. The photoelectric conversion element is irradiated with the ultraviolet light reflected or transmitted by the object. The photoelectric conversion element has a function of changing the potential of the charge holding part when irradiated with the ultraviolet light and retaining the potential when not irradiated with the ultraviolet light.

Embodiments of a thermal compression bonding (TCB) process cooling manifold, a TCB process system, and a method for TCB using the cooling manifold are disclosed. In some embodiments, the cooling manifold comprises a pre-mixing chamber that is separated from a mixing chamber by a baffle. The baffle may comprise at least one concentric pattern formed through the baffle such that the primary cooling fluid in the pre-mixing chamber is substantially evenly distributed to the mixing chamber. The pre-mixing chamber may be coupled to a source of primary cooling fluid. The mixing chamber may have an input configured to accept the primary cooling fluid and an output to output the primary cooling fluid.

The invention relates to an apparatus for especially thermally joining micro-electromechanical parts (2, 3) in a process chamber (8), comprising a bottom support plate (11) for holding at least one first (2) of the parts (2, 3) to be joined, and a pressing device (15) for applying pressure to at least one second (3) of the parts (2, 3) to be joined in relation to the at least one first part (2). The pressing device (15) is equipped with an expandable membrane (19) provided for entering in contact with the at least one second part (3). Fluid pressure, in particular gas pressure, can be applied to said membrane (19) on the side thereof facing away from the parts (2, 3) to be joined.

A method of forming a weld on a work piece is disclosed. The method may include creating an internal cavity along the work piece and extending a conduit having an exit orifice into the internal cavity such that the exit orifice may be positioned adjacent to the weld to be formed. The method may further include supplying a purge gas to the conduit, the purge gas being carried through the conduit and pushed out of the exit orifice so as to displace undesirable gasses away from the weld to be formed and then subsequently forming the weld.

A bonding and indexing method is provided, having a first index head to move a substrate in an indexing direction from a first position to a second position; a second index head to move the substrate in an indexing direction from the second position to a third position; and the first and/or second index head has a bonding element to effect a bonding process between the substrate and an element disposed against the substrate so that bonding and movement in the indexing direction is implemented simultaneously by the first index head and/or bonding and movement in the indexing direction is implemented simultaneously by the second index head.

A turbine airfoil for a gas turbine engine includes a pressure sidewall extending along a spanwise direction, and from a leading edge of the airfoil towards the trailing edge of the airfoil. The turbine airfoil additionally includes a suction sidewall also extending along the spanwise direction, and from the leading edge towards the trailing edge. The pressure sidewall and suction sidewall define a cooling air cavity therebetween, and one or both of the pressure sidewall and suction sidewall define a trailing edge cooling channel extending from the cooling air cavity substantially to the trailing edge. Additionally, one or both of the pressure sidewall and suction sidewall include a plurality of pressure drop members extending partially into the trailing edge cooling channel for reducing an amount of cooling air flowing therethrough from the cooling air cavity.

A turbine airfoil for a gas turbine engine includes a pressure sidewall extending along a spanwise direction, and from a leading edge of the airfoil towards the trailing edge of the airfoil. The turbine airfoil additionally includes a suction sidewall also extending along the spanwise direction, and from the leading edge towards the trailing edge. The pressure sidewall and suction sidewall define a cooling air cavity therebetween, and one or both of the pressure sidewall and suction sidewall define a trailing edge cooling channel extending from the cooling air cavity substantially to the trailing edge. Additionally, one or both of the pressure sidewall and suction sidewall include a plurality of pressure drop members extending partially into the trailing edge cooling channel for reducing an amount of cooling air flowing therethrough from the cooling air cavity.