A method of manufacturing a hollow aerofoil component (100) for a gas turbine engine (10) comprises using a capping panel (200) to cover a pocket (310) in a pocketed aerofoil body (300). During manufacture, a mandrel (400) is provided to support the capping panel (200) in the correct position. This ensures that the outer surface of the capping panel (200) is located as accurately as possible. This means that the capping panel (200) can be made to be as thin as possible, which in turn reduces weight and material wastage. Remotely detectable elements (700) may be provided to the mandrel (400) to enable the location of the pocket (310) to be accurately determined from outside the aerofoil (100).

A method of manufacturing a hollow aerofoil component (100) for a gas turbine engine (10) comprises using a capping panel (200) to cover a pocket (310) in a pocketed aerofoil body (300). During manufacture, a mandrel (400) is provided to support the capping panel (200) in the correct position. This ensures that the outer surface of the capping panel (200) is located as accurately as possible. This means that the capping panel (200) can be made to be as thin as possible, which in turn reduces weight and material wastage. Remotely detectable elements (700) may be provided to the mandrel (400) to enable the location of the pocket (310) to be accurately determined from outside the aerofoil (100).

The invention relates to a method of joining substrates. It is the object of the invention in this respect to join substrates of substrate materials together without having to exert an increased effort for a coating with additional coating processes to be carried out and to be able to achieve a good quality of the join connection in so doing. In the method in accordance with the invention a pretreatment of at least one join surface of a substrate to be joined is carried out in low pressure oxygen plasma prior to the actual joining. On the joining, a contact force acts on the substrates to be joined in the range 2 kPa to 5 MPa and in this process a heat treatment is carried out at an elevated temperature of at least 100° C. and at under pressure conditions of a maximum of 10 mbar, preferably <10.sup.−3 mbar.

The invention relates to a method of joining substrates. It is the object of the invention in this respect to join substrates of substrate materials together without having to exert an increased effort for a coating with additional coating processes to be carried out and to be able to achieve a good quality of the join connection in so doing. In the method in accordance with the invention a pretreatment of at least one join surface of a substrate to be joined is carried out in low pressure oxygen plasma prior to the actual joining. On the joining, a contact force acts on the substrates to be joined in the range 2 kPa to 5 MPa and in this process a heat treatment is carried out at an elevated temperature of at least 100° C. and at under pressure conditions of a maximum of 10 mbar, preferably <10.sup.−3 mbar.

Embodiments of golf club face plates with internal cell lattices are presented herein. Other examples and related methods are also disclosed herein.

A method is provided for interconnecting the batteries in a battery pack in a manner that is designed to minimize damage and contamination of the contact surfaces of the interconnect and the battery terminal, thereby minimizing connection resistance and increasing interconnect reliability.

Provided is a combined type RFeB-based magnet, including: a first unit magnet; a second unit magnet; and an interface material that bonds the first unit magnet and the second unit magnet, in which the first unit magnet and the second unit magnet are RFeB-based magnets containing a light rare earth element R.sup.L that is at least one element selected from the group consisting of Nd and Pr, Fe, and B, in which the interface material contains at least one compound selected from the group consisting of a carbide, a hydroxide, and an oxide of the light rare earth element R.sup.L, and in which an amount of a heavy rare earth element R.sup.H that is at least one element selected from the group consisting of Dy, Tb and Ho in the second unit magnet is more than that in the first unit magnet.

Provided is a combined type RFeB-based magnet, including: a first unit magnet; a second unit magnet; and an interface material that bonds the first unit magnet and the second unit magnet, in which the first unit magnet and the second unit magnet are RFeB-based magnets containing a light rare earth element R.sup.L that is at least one element selected from the group consisting of Nd and Pr, Fe, and B, in which the interface material contains at least one compound selected from the group consisting of a carbide, a hydroxide, and an oxide of the light rare earth element R.sup.L, and in which an amount of a heavy rare earth element R.sup.H that is at least one element selected from the group consisting of Dy, Tb and Ho in the second unit magnet is more than that in the first unit magnet.

A manifold with a circular cross-section having a deviation angle of 180 degrees for a tube bundle heat exchanger for large product pressures has a first and second flange on each inlet and outlet. The manifold has two manifold halves respectively made of a single piece, and each half comprises a joining point on an end facing away from a flange. The manifold halves are connected together on the associated joining point. Extension of the passage cross-section of each manifold half is formed by rotationally symmetrical through openings, from which at least one of the flanges and at least one of the joining points extends in the respective coaxial arrangement on rotational axes. First and second axes of through openings of the first manifold halves and third and fourth axes of through openings of the second manifold halves extend on a common plane representing a meridian plane for each flange.

The electrode (10) includes an electrically conductive surface (14) with a galvanic pellicle, or carbon nanotube mat (18), secured to the conductive surface (14). The pellicle (18) has a first surface (20) and an opposed outer surface (22) and defines an uncompressed thickness dimension (24) as a longest length of a straight axis (26) extending from the first surface (20) to the outer surface (22) of an uncompressed section (28) of the galvanic pellicle (18). Uncompressed sections (28) of the pellicle are defined between connected areas (30) and continuous connected areas (32) of the pellicle (18). Any point (35) within any uncompressed section (28) is no more distant from one of a nearest connected area (30) and/or a nearest segment (34) of a continuous connected area (32) than about ten times the uncompressed thickness dimension (24) of the pellicle (18), thereby achieving significantly reduced contact resistance.