Abstract: A cabin lining element for an aircraft cabin which is arranged in the interior of an aircraft fuselage structure, having a fuselage structure side and a cabin side. The cabin lining element comprises an electrically contactable heating lacquer layer at least in regions on its fuselage structure side. A rib is provided for an aircraft fuselage structure, having at least one foot portion on the outer skin facing side and a cabin facing side head portion. The rib comprises an electrically contactable heating lacquer layer at least in regions on a side of the head portion facing the cabin.

Abstract: A cladding element having a heating layer in a sandwich construction. In the case of a cladding element in a sandwich construction for an interior space of an aircraft, the cladding element includes a core layer and a first cover layer. The first cover layer forms a visible side of the cladding element. An electrically heating layer extends at least across a sub-face of the first cover layer and serves for generating heat for emission through the first cover layer is disposed between the core layer and the first cover layer.

Abstract: A cabin lining element for an aircraft cabin which is arranged in the interior of an aircraft fuselage structure, having a fuselage structure side and a cabin side. The cabin lining element comprises an electrically contactable heating lacquer layer at least in regions on its fuselage structure side. A rib is provided for an aircraft fuselage structure, having at least one foot portion on the outer skin facing side and a cabin facing side head portion. The rib comprises an electrically contactable heating lacquer layer at least in regions on a side of the head portion facing the cabin. As a result of the heating lacquer layer, it is possible to omit insulation which otherwise surrounds the rib heads and, as a consequence, to enlarge the width of the cabin.

Abstract: The invention relates to a dishwashing additive or detergent composition comprising a silicate source and a ring-containing organic acid; wherein the additive composition comprises between 20 mg and 5000 mg of silicate source and/or between 50 mg and 10,000 mg of ring-containing organic acid compound; and wherein the composition comprises a ratio of between 1 part silicate source to 4 parts ring-containing organic acid compound and 4 parts silicate source to 1 part ring-containing organic acid compound. The composition provides aluminium and aluminium alloy protection benefits. The invention further relates to packages and devices containing the compositions and to methods of washing dishes in an automatic dishwasher using the compositions.

Abstract: An internal cladding part for cladding a fuselage structure of an aircraft is disclosed having a first cover layer that extends in a planar manner, a second cover layer that extends in a planar manner, a core layer which is disposed between the first and the second cover layer and is connected to the first and the second cover layer and defines a receptacle cavity, and an insulation structure having a porous insulation core and an evacuated film sheath that encases the insulation core in a gas-tight manner. The insulation structure is disposed in the receptacle cavity between the first and the second cover layer.

Abstract: An internal cladding part for cladding a fuselage structure of an aircraft is disclosed having a first cover layer that extends in a planar manner, a second cover layer that extends in a planar manner, a core layer which is disposed between the first and the second cover layer and is connected to the first and the second cover layer and defines a receptacle cavity, and an insulation structure having a porous insulation core and an evacuated film sheath that encases the insulation core in a gas-tight manner. The insulation structure is disposed in the receptacle cavity between the first and the second cover layer.

Abstract: An automatic dishwashing product comprising a bleaching agent and a compound in accordance with formula (1) or a salt or tautomer thereof, wherein A and B are independently selected from the group consisting of H, OR1, and NHR2, wherein R1 and R2 are independently selected from the group consisting of H and C1-C4 alkyl, with the proviso that A and B are not both H and are not both OH.

Abstract: An internal cladding part for cladding a fuselage structure of an aircraft is disclosed having a first cover layer that extends in a planar manner, a second cover layer that extends in a planar manner, a core layer which is disposed between the first and the second cover layer and is connected to the first and the second cover layer and defines a receptacle cavity, and an insulation structure having a porous insulation core and an evacuated film sheath that encases the insulation core in a gas-tight manner. The insulation structure is disposed in the receptacle cavity between the first and the second cover layer.

Abstract: A cabin lining element for an aircraft cabin which is arranged in the interior of an aircraft fuselage structure, having a fuselage structure side and a cabin side. The cabin lining element comprises an electrically contactable heating lacquer layer at least in regions on its fuselage structure side. A rib is provided for an aircraft fuselage structure, having at least one foot portion on the outer skin facing side and a cabin facing side head portion. The rib comprises an electrically contactable heating lacquer layer at least in regions on a side of the head portion facing the cabin. As a result of the heating lacquer layer, it is possible to omit insulation which otherwise surrounds the rib heads and, as a consequence, to enlarge the width of the cabin.

Abstract: An internal cladding part for cladding a fuselage structure of an aircraft is disclosed having a first cover layer that extends in a planar manner, a second cover layer that extends in a planar manner, a core layer which is disposed between the first and the second cover layer and is connected to the first and the second cover layer and defines a receptacle cavity, and an insulation structure having a porous insulation core and an evacuated film sheath that encases the insulation core in a gas-tight manner. The insulation structure is disposed in the receptacle cavity between the first and the second cover layer.

Abstract: A cladding element having a heating layer in a sandwich construction. In the case of a cladding element in a sandwich construction for an interior space of an aircraft, the cladding element includes a core layer and a first cover layer. The first cover layer forms a visible side of the cladding element. An electrically heating layer extends at least across a sub-face of the first cover layer and serves for generating heat for emission through the first cover layer is disposed between the core layer and the first cover layer.

Abstract: The invention relates to a motor housing for an electric motor with a stator as well as to an electric motor with a housing, whereby at least one multifunctional opening is arranged in the lower housing section and whereby electronics can be arranged in the housing, characterized in that, in order to cool the electronics, the multifunctional opening has a baffle by means of which an air flow can be directed towards the electronics, and, as an alternative, it has an offset on the side facing the upper housing section in order to mechanically connect the stator to the lower housing section.

Abstract: A fastening system is provided with a wall ring as fastening device, a ventilator and a holding means, wherein the fastening device is provided in radial direction around the ventilator and the ventilator is connected to the fastening device via the holding means. The fastening device encompasses a first fastening geometry. The fastening system comprises the fastening device and additionally encompasses a holding device, wherein the fastening device encompasses at least one further, second fastening geometry for fastening the holding device to the fastening device. The fastening device and thus the wall ring axial ventilator can be fastened in a common manner to a unit via the first fastening geometry. The second fastening geometry serves to fasten the holding device to the fastening device, so that the wall ring axial ventilator can be fastened to a different design of a unit than a lamella heat exchanger.

Abstract: The invention relates to a radial blower, with at least one axial air inlet port (1) and with a radial air outlet port (2). The radial blower has a housing subassembly and a fan subassembly with an electric motor (3) and a fan wheel (4). The housing subassembly has at least one holding part (5) arranged in the region of the axial air inlet port (1) for supporting reception of a carrying part (6), and two shell parts (71, 72) releasably connectable to one another. The holding part (5) is fastened between the shell parts. The electric motor (3) of the fan subassembly is an electronically commutated direct current motor. Control electronics (19) are arranged in a terminal box (13) for the reception of motor connections (12). The terminal box is fastened, to the underside of a lower shell part (72) of the housing subassembly.

Abstract: The invention relates to a motor housing for an electric motor with a stator as well as to an electric motor with a housing, whereby at least one multifunctional opening is arranged in the lower housing section and whereby electronics can be arranged in the housing, characterized in that, in order to cool the electronics, the multifunctional opening has a baffle by means of which an air flow can be directed towards the electronics, and, as an alternative, it has an offset on the side facing the upper housing section in order to mechanically connect the stator to the lower housing section.

Abstract: An insulation package for thermal and acoustic insulation of a vehicle cabin has a cutout to allow a fastening device to pass through. An insulating element that is disposed in an area of the insulation package surrounding the cutout has an opening corresponding to the cutout for allowing a fastening device to pass through. At least part of the insulating element is aligned perpendicularly to an axis of the passthrough in the cutout and conformed so as to create a gap between a fastening device that has passed through and the insulation package. In this way, condensed water may be prevented from passing through the cutout in the insulation package and into the aircraft cabin.